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aircraft</title> <meta name="description" content="Search results for: commercial aircraft"> <meta name="keywords" content="commercial aircraft"> <meta name="viewport" content="width=device-width, initial-scale=1, minimum-scale=1, maximum-scale=1, user-scalable=no"> <meta charset="utf-8"> <link href="https://cdn.waset.org/favicon.ico" type="image/x-icon" rel="shortcut icon"> <link href="https://cdn.waset.org/static/plugins/bootstrap-4.2.1/css/bootstrap.min.css" rel="stylesheet"> <link href="https://cdn.waset.org/static/plugins/fontawesome/css/all.min.css" rel="stylesheet"> <link href="https://cdn.waset.org/static/css/site.css?v=150220211555" rel="stylesheet"> </head> <body> <header> <div class="container"> <nav class="navbar navbar-expand-lg navbar-light"> <a class="navbar-brand" href="https://waset.org"> <img src="https://cdn.waset.org/static/images/wasetc.png" alt="Open Science Research Excellence" title="Open Science Research Excellence" /> </a> <button class="d-block d-lg-none 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action="https://publications.waset.org/abstracts/search"> <div id="custom-search-input"> <div class="input-group"> <i class="fas fa-search"></i> <input type="text" class="search-query" name="q" placeholder="Author, Title, Abstract, Keywords" value="commercial aircraft"> <input type="submit" class="btn_search" value="Search"> </div> </div> </form> </div> </div> <div class="row mt-3"> <div class="col-sm-3"> <div class="card"> <div class="card-body"><strong>Commenced</strong> in January 2007</div> </div> </div> <div class="col-sm-3"> <div class="card"> <div class="card-body"><strong>Frequency:</strong> Monthly</div> </div> </div> <div class="col-sm-3"> <div class="card"> <div class="card-body"><strong>Edition:</strong> International</div> </div> </div> <div class="col-sm-3"> <div class="card"> <div class="card-body"><strong>Paper Count:</strong> 2784</div> </div> </div> </div> <h1 class="mt-3 mb-3 text-center" style="font-size:1.6rem;">Search results for: commercial aircraft</h1> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">2724</span> Diagnostic Investigation of Aircraft Performance at Different Winglet Cant Angles </h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=M.%20Dinesh">M. Dinesh</a>, <a href="https://publications.waset.org/abstracts/search?q=V.%20Kenny%20Mark"> V. Kenny Mark</a>, <a href="https://publications.waset.org/abstracts/search?q=Dharni%20Vasudhevan%20Venkatesan"> Dharni Vasudhevan Venkatesan</a>, <a href="https://publications.waset.org/abstracts/search?q=B.%20Santhosh%20Kumar"> B. Santhosh Kumar</a>, <a href="https://publications.waset.org/abstracts/search?q=R.%20Sree%20Radesh"> R. Sree Radesh</a>, <a href="https://publications.waset.org/abstracts/search?q=V.%20R.%20Sanal%20Kumar"> V. R. Sanal Kumar </a> </p> <p class="card-text"><strong>Abstract:</strong></p> Comprehensive numerical studies have been carried out to examine the best aerodynamic performance of subsonic aircraft at different winglet cant angles using a validated 3D k-蠅 SST model. In the parametric analytical studies, NACA series of airfoils are selected. Basic design of the winglet is selected from the literature and flow features of the entire wing including the winglet tip effects have been examined with different cant angles varying from 150 to 600 at different angles of attack up to 140. We have observed, among the cases considered in this study that a case with 150 cant angle the aerodynamics performance of the subsonic aircraft during takeoff was found better up to an angle of attack of 2.80 and further its performance got diminished at higher angles of attack. Analyses further revealed that increasing the winglet cant angle from 150 to 600 at higher angles of attack could negate the performance deterioration and additionally it could enhance the peak CL/CD on the order of 3.5%. The investigated concept of variable-cant-angle winglets appears to be a promising alternative for improving the aerodynamic efficiency of aircraft. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=aerodynamic%20efficiency" title="aerodynamic efficiency">aerodynamic efficiency</a>, <a href="https://publications.waset.org/abstracts/search?q=cant%20angle" title=" cant angle"> cant angle</a>, <a href="https://publications.waset.org/abstracts/search?q=drag%20reduction" title=" drag reduction"> drag reduction</a>, <a href="https://publications.waset.org/abstracts/search?q=flexible%20winglets" title=" flexible winglets "> flexible winglets </a> </p> <a href="https://publications.waset.org/abstracts/18421/diagnostic-investigation-of-aircraft-performance-at-different-winglet-cant-angles" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/18421.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">522</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">2723</span> The Usage of Thermal Regions as a Air Navigation Rule for Unmanned Aircraft Systems</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Resul%20Fikir">Resul Fikir</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Unmanned Aircraft Systems (UAS) become indispensable parts of modern airpower as force multiplier .One of the main advantages of UAS is long endurance. UAS have to take extra payloads to accomplish different missions but these payloads decrease endurance of aircraft because of increasing drug. There are continuing researches to increase the capability of UAS. There are some vertical thermal air currents, which can cause climb and increase endurance, in nature. Birds and gliders use thermals to gain altitude with no effort. UAS have wide wing which can use of thermals like birds and gliders. Thermal regions, which is area of 2-3 NM, exist all around the world. It is free and clean source. This study analyses if thermal regions can be adopted and implemented as an assistant tool for UAS route planning. First and second part of study will contain information about the thermal regions and current applications about UAS in aviation and climbing performance with a real example. Continuing parts will analyze the contribution of thermal regions to UAS endurance. Contribution is important because planning declaration of UAS navigation rules will be in 2015. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=unmanned%20aircraft%20systems" title="unmanned aircraft systems">unmanned aircraft systems</a>, <a href="https://publications.waset.org/abstracts/search?q=Air4All" title=" Air4All"> Air4All</a>, <a href="https://publications.waset.org/abstracts/search?q=thermals" title=" thermals"> thermals</a>, <a href="https://publications.waset.org/abstracts/search?q=gliders" title=" gliders"> gliders</a> </p> <a href="https://publications.waset.org/abstracts/3264/the-usage-of-thermal-regions-as-a-air-navigation-rule-for-unmanned-aircraft-systems" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/3264.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">400</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">2722</span> Computer Simulation Studies of Aircraft Wing Architectures on Vibration Responses</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Shengyong%20Zhang">Shengyong Zhang</a>, <a href="https://publications.waset.org/abstracts/search?q=Mike%20Mikulich"> Mike Mikulich</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Vibration is a crucial limiting consideration in the analysis and design of airplane wing structures to avoid disastrous failures due to the propagation of existing cracks in the material. In this paper, we build CAD models of aircraft wings to capture the design intent with configurations. Subsequent FEA vibration analysis is performed to study the natural vibration properties and impulsive responses of the resulting user-defined wing models. This study reveals the variations of the wing鈥檚 vibration characteristics with respect to changes in its structural configurations. Integrating CAD modelling and FEA vibration analysis enables designers to improve wing architectures for implementing design requirements in the preliminary design stage. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=aircraft%20wing" title="aircraft wing">aircraft wing</a>, <a href="https://publications.waset.org/abstracts/search?q=CAD%20modelling" title=" CAD modelling"> CAD modelling</a>, <a href="https://publications.waset.org/abstracts/search?q=FEA" title=" FEA"> FEA</a>, <a href="https://publications.waset.org/abstracts/search?q=vibration%20analysis" title=" vibration analysis"> vibration analysis</a> </p> <a href="https://publications.waset.org/abstracts/139170/computer-simulation-studies-of-aircraft-wing-architectures-on-vibration-responses" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/139170.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">165</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">2721</span> Characteristics and Flight Test Analysis of a Fixed-Wing UAV with Hover Capability</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Ferit%20%C3%87ak%C4%B1c%C4%B1">Ferit 脟ak谋c谋</a>, <a href="https://publications.waset.org/abstracts/search?q=M.%20Kemal%20Leblebicio%C4%9Flu"> M. Kemal Leblebicio臒lu</a> </p> <p class="card-text"><strong>Abstract:</strong></p> In this study, characteristics and flight test analysis of a fixed-wing unmanned aerial vehicle (UAV) with hover capability is analyzed. The base platform is chosen as a conventional airplane with throttle, ailerons, elevator and rudder control surfaces, that inherently allows level flight. Then this aircraft is mechanically modified by the integration of vertical propellers as in multi rotors in order to provide hover capability. The aircraft is modeled using basic aerodynamical principles and linear models are constructed utilizing small perturbation theory for trim conditions. Flight characteristics are analyzed by benefiting from linear control theory鈥檚 state space approach. Distinctive features of the aircraft are discussed based on analysis results with comparison to conventional aircraft platform types. A hybrid control system is proposed in order to reveal unique flight characteristics. The main approach includes design of different controllers for different modes of operation and a hand-over logic that makes flight in an enlarged flight envelope viable. Simulation tests are performed on mathematical models that verify asserted algorithms. Flight tests conducted in real world revealed the applicability of the proposed methods in exploiting fixed-wing and rotary wing characteristics of the aircraft, which provide agility, survivability and functionality. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=flight%20test" title="flight test">flight test</a>, <a href="https://publications.waset.org/abstracts/search?q=flight%20characteristics" title=" flight characteristics"> flight characteristics</a>, <a href="https://publications.waset.org/abstracts/search?q=hybrid%20aircraft" title=" hybrid aircraft"> hybrid aircraft</a>, <a href="https://publications.waset.org/abstracts/search?q=unmanned%20aerial%20vehicle" title=" unmanned aerial vehicle"> unmanned aerial vehicle</a> </p> <a href="https://publications.waset.org/abstracts/46302/characteristics-and-flight-test-analysis-of-a-fixed-wing-uav-with-hover-capability" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/46302.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">329</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">2720</span> Design Improvement of Aircraft Turbofan Engine Following Bird Ingestion Testing</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Ahmed%20H.%20Elkholy">Ahmed H. Elkholy</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Aircraft gas turbine engines are subject to damage by airborne foreign objects such as birds and garbage dumps. In order to assess their effect on engine performance, a complete foreign object damage (FOD) test was carried out and a component failure analysis was used to verify airworthiness standards (AWS) requirements for engine certification as set by international regulations. Ingestion damage due to 1.8 Kg (4 lb.) bird strike on an engine is presented in some detail. Based on the observed damage, improvements to the engine design were suggested in two different locations: the front bearing housing and the low compressor shaft. When these improvements were implemented, the engine showed an acceptable containment capability that meets AWS requirements. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=aircraft%20engine" title="aircraft engine">aircraft engine</a>, <a href="https://publications.waset.org/abstracts/search?q=airworthiness%20standards" title=" airworthiness standards"> airworthiness standards</a>, <a href="https://publications.waset.org/abstracts/search?q=bird%20ingestion" title=" bird ingestion"> bird ingestion</a>, <a href="https://publications.waset.org/abstracts/search?q=foreign%20object%20damage" title=" foreign object damage"> foreign object damage</a> </p> <a href="https://publications.waset.org/abstracts/31666/design-improvement-of-aircraft-turbofan-engine-following-bird-ingestion-testing" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/31666.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">421</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">2719</span> Applications for Additive Manufacturing Technology for Reducing the Weight of Body Parts of Gas Turbine Engines</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Liubov%20Magerramova">Liubov Magerramova</a>, <a href="https://publications.waset.org/abstracts/search?q=Mikhail%20Petrov"> Mikhail Petrov</a>, <a href="https://publications.waset.org/abstracts/search?q=Vladimir%20Isakov"> Vladimir Isakov</a>, <a href="https://publications.waset.org/abstracts/search?q=Liana%20Shcherbinina"> Liana Shcherbinina</a>, <a href="https://publications.waset.org/abstracts/search?q=Suren%20Gukasyan"> Suren Gukasyan</a>, <a href="https://publications.waset.org/abstracts/search?q=Daniil%20Povalyukhin"> Daniil Povalyukhin</a>, <a href="https://publications.waset.org/abstracts/search?q=Olga%20Klimova-Korsmik"> Olga Klimova-Korsmik</a>, <a href="https://publications.waset.org/abstracts/search?q=Darya%20Volosevich"> Darya Volosevich</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Aircraft engines are developing along the path of increasing resource, strength, reliability, and safety. The building of gas turbine engine body parts is a complex design and technological task. Particularly complex in the design and manufacturing are the casings of the input stages of helicopter gearboxes and central drives of aircraft engines. Traditional technologies, such as precision casting or isothermal forging, are characterized by significant limitations in parts production. For parts like housing, additive technologies guarantee spatial freedom and limitless or flexible design. This article presents the results of computational and experimental studies. These investigations justify the applicability of additive technologies (AT) to reduce the weight of aircraft housing gearbox parts by up to 32%. This is possible due to geometrical optimization compared to the classical, less flexible manufacturing methods and as-casted aircraft parts with over-insured values of safety factors. Using an example of the body of the input stage of an aircraft gearbox, visualization of the layer-by-layer manufacturing of a part based on thermal deformation was demonstrated. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=additive%20technologies" title="additive technologies">additive technologies</a>, <a href="https://publications.waset.org/abstracts/search?q=gas%20turbine%20engines" title=" gas turbine engines"> gas turbine engines</a>, <a href="https://publications.waset.org/abstracts/search?q=topological%20optimization" title=" topological optimization"> topological optimization</a>, <a href="https://publications.waset.org/abstracts/search?q=synthesis%20process" title=" synthesis process"> synthesis process</a> </p> <a href="https://publications.waset.org/abstracts/163290/applications-for-additive-manufacturing-technology-for-reducing-the-weight-of-body-parts-of-gas-turbine-engines" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/163290.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">115</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">2718</span> Detectability of Malfunction in Turboprop Engine</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Tomas%20Vampola">Tomas Vampola</a>, <a href="https://publications.waset.org/abstracts/search?q=Michael%20Val%C3%A1%C5%A1ek"> Michael Val谩拧ek</a> </p> <p class="card-text"><strong>Abstract:</strong></p> On the basis of simulation-generated failure states of structural elements of a turboprop engine suitable for the busy-jet class of aircraft, an algorithm for early prediction of damage or reduction in functionality of structural elements of the engine is designed and verified with real data obtained at dynamometric testing facilities of aircraft engines. Based on an expanding database of experimentally determined data from temperature and pressure sensors during the operation of turboprop engines, this strategy is constantly modified with the aim of using the minimum number of sensors to detect an inadmissible or deteriorated operating mode of specific structural elements of an aircraft engine. The assembled algorithm for the early prediction of reduced functionality of the aircraft engine significantly contributes to the safety of air traffic and to a large extent, contributes to the economy of operation with positive effects on the reduction of the energy demand of operation and the elimination of adverse effects on the environment. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=detectability%20of%20malfunction" title="detectability of malfunction">detectability of malfunction</a>, <a href="https://publications.waset.org/abstracts/search?q=dynamometric%20testing" title=" dynamometric testing"> dynamometric testing</a>, <a href="https://publications.waset.org/abstracts/search?q=prediction%20of%20damage" title=" prediction of damage"> prediction of damage</a>, <a href="https://publications.waset.org/abstracts/search?q=turboprop%20engine" title=" turboprop engine"> turboprop engine</a> </p> <a href="https://publications.waset.org/abstracts/166484/detectability-of-malfunction-in-turboprop-engine" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/166484.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">94</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">2717</span> Running the Athena Vortex Lattice Code in JAVA through the Java Native Interface</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Paul%20Okonkwo">Paul Okonkwo</a>, <a href="https://publications.waset.org/abstracts/search?q=Howard%20Smith"> Howard Smith</a> </p> <p class="card-text"><strong>Abstract:</strong></p> This paper describes a methodology to integrate the Athena Vortex Lattice Aerodynamic Software for automated operation in a multivariate optimisation of the Blended Wing Body Aircraft. The Athena Vortex Lattice code developed at the Massachusetts Institute of Technology allows for the aerodynamic analysis of aircraft using the vortex lattice method. Ordinarily, the Athena Vortex Lattice operation requires a text file containing the aircraft geometry to be loaded into the AVL solver in order to determine the aerodynamic forces and moments. However, automated operation will be required to enable integration into a multidisciplinary optimisation framework. Automated AVL operation within the JAVA design environment will nonetheless require a modification and recompilation of AVL source code into an executable file capable of running on windows and other platforms without the 鈥揦11 libraries. This paper describes the procedure for the integrating the FORTRAN written AVL software for automated operation within the multivariate design synthesis optimisation framework for the conceptual design of the BWB aircraft. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=aerodynamics" title="aerodynamics">aerodynamics</a>, <a href="https://publications.waset.org/abstracts/search?q=automation" title=" automation"> automation</a>, <a href="https://publications.waset.org/abstracts/search?q=optimisation" title=" optimisation"> optimisation</a>, <a href="https://publications.waset.org/abstracts/search?q=AVL" title=" AVL"> AVL</a>, <a href="https://publications.waset.org/abstracts/search?q=JNI" title=" JNI"> JNI</a> </p> <a href="https://publications.waset.org/abstracts/22131/running-the-athena-vortex-lattice-code-in-java-through-the-java-native-interface" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/22131.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">565</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">2716</span> Oblique Wing: Future Generation Transonic Aircraft</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Mushfiqul%20Alam">Mushfiqul Alam</a>, <a href="https://publications.waset.org/abstracts/search?q=Kashyapa%20Narenathreyas"> Kashyapa Narenathreyas</a> </p> <p class="card-text"><strong>Abstract:</strong></p> The demand for efficient transonic transport has been growing every day and may turn out to be the most pressed innovation in coming years. Oblique wing configuration was proposed as an alternative to conventional wing configuration for supersonic and transonic passenger aircraft due to its aerodynamic advantages. This paper re-demonstrates the aerodynamic advantages of oblique wing configuration using open source CFD code. The aerodynamic data were generated using Panel Method. Results show that Oblique Wing concept with elliptical wing planform offers a significant reduction in drag at transonic and supersonic speeds and approximately twice the lift distribution compared to conventional operating aircrafts. The paper also presents a preliminary conceptual aircraft sizing which can be used for further experimental analysis. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=aerodynamics" title="aerodynamics">aerodynamics</a>, <a href="https://publications.waset.org/abstracts/search?q=asymmetric%20sweep" title=" asymmetric sweep"> asymmetric sweep</a>, <a href="https://publications.waset.org/abstracts/search?q=oblique%20wing" title=" oblique wing"> oblique wing</a>, <a href="https://publications.waset.org/abstracts/search?q=swing%20wing" title=" swing wing"> swing wing</a> </p> <a href="https://publications.waset.org/abstracts/5127/oblique-wing-future-generation-transonic-aircraft" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/5127.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">555</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">2715</span> Aerodynamic Devices Development for Model Aircraft Control and Wind-Driven Bicycle</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Yuta%20Moriyama">Yuta Moriyama</a>, <a href="https://publications.waset.org/abstracts/search?q=Tsuyoshi%20Yamazaki"> Tsuyoshi Yamazaki</a>, <a href="https://publications.waset.org/abstracts/search?q=Etsuo%20Morishita"> Etsuo Morishita</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Several aerodynamic devices currently attract engineers and research students. The plasma actuator is one of them, and it is very effective to control the flow. The actuator recovers a separated flow to an attached one. The actuator is also inversely applied to a spoiler. The model aircraft might be controlled by this actuator. We develop a model aircraft with the plasma actuator. Another interesting device is the Wells turbine which rotates in one direction. The present authors propose a bicycle with the Wells turbine in the wheels. Power reduction is measured when the turbine is driven by an electric motor at the exit of a wind tunnel. Several Watts power reduction might be possible. This means that the torque of the bike can be augmented by the turbine in the cross wind. These devices are tested in the wind tunnel with a three-component balance and the aerodynamic forces and moment are obtained. In this paper, we introduce these devices and their aerodynamic characteristics. The control force and moment of the plasma actuator are clarified and the power reduction of the bicycle is quantified. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=aerodynamics" title="aerodynamics">aerodynamics</a>, <a href="https://publications.waset.org/abstracts/search?q=model%20aircraft" title=" model aircraft"> model aircraft</a>, <a href="https://publications.waset.org/abstracts/search?q=plasma%20actuator" title=" plasma actuator"> plasma actuator</a>, <a href="https://publications.waset.org/abstracts/search?q=Wells%20turbine" title=" Wells turbine"> Wells turbine</a> </p> <a href="https://publications.waset.org/abstracts/92167/aerodynamic-devices-development-for-model-aircraft-control-and-wind-driven-bicycle" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/92167.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">246</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">2714</span> Aircraft Line Maintenance Equipped with Decision Support System</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=B.%20Sudarsan%20Baskar">B. Sudarsan Baskar</a>, <a href="https://publications.waset.org/abstracts/search?q=S.%20Pooja%20Pragati"> S. Pooja Pragati</a>, <a href="https://publications.waset.org/abstracts/search?q=S.%20Raj%20Kumar"> S. Raj Kumar</a> </p> <p class="card-text"><strong>Abstract:</strong></p> The cost effectiveness in aircraft maintenance is of high privilege in the recent days. The cost effectiveness can be effectively made when line maintenance activities are incorporated at airports during Turn around time (TAT). The present work outcomes the shortcomings that affect the dispatching of the aircrafts, aiming at high fleet operability and low maintenance cost. The operational and cost constraints have been discussed and a suggestive alternative mechanism is proposed. The possible allocation of all deferred maintenance tasks to a set of all deferred maintenance tasks to a set of suitable airport resources have termed as alternative and is discussed in this paper from the data鈥檚 collected from the kingfisher airlines. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=decision%20support%20system" title="decision support system">decision support system</a>, <a href="https://publications.waset.org/abstracts/search?q=aircraft%20maintenance%20planning" title=" aircraft maintenance planning"> aircraft maintenance planning</a>, <a href="https://publications.waset.org/abstracts/search?q=maintenance-cost" title=" maintenance-cost"> maintenance-cost</a>, <a href="https://publications.waset.org/abstracts/search?q=RUL%28remaining%20useful%20life%29" title=" RUL(remaining useful life)"> RUL(remaining useful life)</a>, <a href="https://publications.waset.org/abstracts/search?q=logistics" title=" logistics"> logistics</a>, <a href="https://publications.waset.org/abstracts/search?q=supply%20chain%20management" title=" supply chain management"> supply chain management</a> </p> <a href="https://publications.waset.org/abstracts/26299/aircraft-line-maintenance-equipped-with-decision-support-system" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/26299.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">502</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">2713</span> Application of the Total Least Squares Estimation Method for an Aircraft Aerodynamic Model Identification</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Zaouche%20Mohamed">Zaouche Mohamed</a>, <a href="https://publications.waset.org/abstracts/search?q=Amini%20Mohamed"> Amini Mohamed</a>, <a href="https://publications.waset.org/abstracts/search?q=Foughali%20Khaled"> Foughali Khaled</a>, <a href="https://publications.waset.org/abstracts/search?q=Aitkaid%20Souhila"> Aitkaid Souhila</a>, <a href="https://publications.waset.org/abstracts/search?q=Bouchiha%20Nihad%20Sarah"> Bouchiha Nihad Sarah</a> </p> <p class="card-text"><strong>Abstract:</strong></p> The aerodynamic coefficients are important in the evaluation of an aircraft performance and stability-control characteristics. These coefficients also can be used in the automatic flight control systems and mathematical model of flight simulator. The study of the aerodynamic aspect of flying systems is a reserved domain and inaccessible for the developers. Doing tests in a wind tunnel to extract aerodynamic forces and moments requires a specific and expensive means. Besides, the glaring lack of published documentation in this field of study makes the aerodynamic coefficients determination complicated. This work is devoted to the identification of an aerodynamic model, by using an aircraft in virtual simulated environment. We deal with the identification of the system, we present an environment framework based on Software In the Loop (SIL) methodology and we use Microsoft<sup>TM</sup> Flight Simulator (FS-2004) as the environment for plane simulation. We propose The Total Least Squares Estimation technique (TLSE) to identify the aerodynamic parameters, which are unknown, variable, classified and used in the expression of the piloting law. In this paper, we define each aerodynamic coefficient as the mean of its numerical values. All other variations are considered as modeling uncertainties that will be compensated by the robustness of the piloting control. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=aircraft%20aerodynamic%20model" title="aircraft aerodynamic model">aircraft aerodynamic model</a>, <a href="https://publications.waset.org/abstracts/search?q=total%20least%20squares%20estimation" title=" total least squares estimation"> total least squares estimation</a>, <a href="https://publications.waset.org/abstracts/search?q=piloting%20the%20aircraft" title=" piloting the aircraft"> piloting the aircraft</a>, <a href="https://publications.waset.org/abstracts/search?q=robust%20control" title=" robust control"> robust control</a>, <a href="https://publications.waset.org/abstracts/search?q=Microsoft%20Flight%20Simulator" title=" Microsoft Flight Simulator"> Microsoft Flight Simulator</a>, <a href="https://publications.waset.org/abstracts/search?q=MQ-1%20predator" title=" MQ-1 predator"> MQ-1 predator</a> </p> <a href="https://publications.waset.org/abstracts/44416/application-of-the-total-least-squares-estimation-method-for-an-aircraft-aerodynamic-model-identification" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/44416.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">287</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">2712</span> Design and Analysis of Universal Multifunctional Leaf Spring Main Landing Gear for Light Aircraft</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Meiyuan%20Zheng">Meiyuan Zheng</a>, <a href="https://publications.waset.org/abstracts/search?q=Jingwu%20He"> Jingwu He</a>, <a href="https://publications.waset.org/abstracts/search?q=Yuexi%20Xiong"> Yuexi Xiong</a> </p> <p class="card-text"><strong>Abstract:</strong></p> A universal multi-function leaf spring main landing gear was designed for light aircraft. The main landing gear combined with the leaf spring, skidding, and wheels enables it to have a good takeoff and landing performance on various grounds such as the hard, snow, grass and sand grounds. Firstly, the characteristics of different landing sites were studied in this paper in order to analyze the load of the main landing gear on different types of grounds. Based on this analysis, the structural design optimization along with the strength and stiffness characteristics of the main landing gear has been done, which enables it to have good takeoff and landing performance on different types of grounds given the relevant regulations and standards. Additionally, the impact of the skidding on the aircraft during the flight was also taken into consideration. Finally, a universal multi-function leaf spring type of the main landing gear suitable for light aircraft has been developed. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=landing%20gear" title="landing gear">landing gear</a>, <a href="https://publications.waset.org/abstracts/search?q=multi-function" title=" multi-function"> multi-function</a>, <a href="https://publications.waset.org/abstracts/search?q=leaf%20spring" title=" leaf spring"> leaf spring</a>, <a href="https://publications.waset.org/abstracts/search?q=skidding" title=" skidding"> skidding</a> </p> <a href="https://publications.waset.org/abstracts/73736/design-and-analysis-of-universal-multifunctional-leaf-spring-main-landing-gear-for-light-aircraft" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/73736.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">267</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">2711</span> Computational Design, Simulation, and Wind Tunnel Testing of a Stabilator for a Fixed Wing Aircraft</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Kartik%20Gupta">Kartik Gupta</a>, <a href="https://publications.waset.org/abstracts/search?q=Umar%20Khan"> Umar Khan</a>, <a href="https://publications.waset.org/abstracts/search?q=Mayur%20Parab"> Mayur Parab</a>, <a href="https://publications.waset.org/abstracts/search?q=Dhiraj%20Chaudhari"> Dhiraj Chaudhari</a>, <a href="https://publications.waset.org/abstracts/search?q=Afzal%20Ansari"> Afzal Ansari</a> </p> <p class="card-text"><strong>Abstract:</strong></p> The report focuses on the study related to the Design and Simulation of a stabilator (an all-movable horizontal stabilizer) for a fixed-wing aircraft. The project involves the development of a computerized direct optimization procedure for designing an aircraft all-movable stabilator. This procedure evaluates various design variables to synthesize an optimal stabilator that meets specific requirements, including performance, control, stability, strength, and flutter velocity constraints. The work signifies the CFD (Computational Fluid Dynamics) analysis of the airfoils used in the stabilator along with the CFD analysis of the Stabilizer and Stabilator of an aircraft named Thorp- T18 in software like XFLR5 and ANSYS-Fluent. A comparative analysis between a Stabilizer and Stabilator of equal surface area and under the same environmental conditions was done, and the percentage of drag reduced by the Stabilator for the same amount of lift generated as the Stabilizer was also calculated lastly, Wind tunnel testing was performed on a scale down model of the Stabilizer and Stabilator and the results of the Wind tunnel testing were compared with the results of CFD. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=wind%20tunnel%20testing" title="wind tunnel testing">wind tunnel testing</a>, <a href="https://publications.waset.org/abstracts/search?q=CFD" title=" CFD"> CFD</a>, <a href="https://publications.waset.org/abstracts/search?q=stabilizer" title=" stabilizer"> stabilizer</a>, <a href="https://publications.waset.org/abstracts/search?q=stabilator" title=" stabilator"> stabilator</a> </p> <a href="https://publications.waset.org/abstracts/184409/computational-design-simulation-and-wind-tunnel-testing-of-a-stabilator-for-a-fixed-wing-aircraft" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/184409.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">60</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">2710</span> Integrating the Athena Vortex Lattice Code into a Multivariate Design Synthesis Optimisation Platform in JAVA</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Paul%20Okonkwo">Paul Okonkwo</a>, <a href="https://publications.waset.org/abstracts/search?q=Howard%20Smith"> Howard Smith</a> </p> <p class="card-text"><strong>Abstract:</strong></p> This paper describes a methodology to integrate the Athena Vortex Lattice Aerodynamic Software for automated operation in a multivariate optimisation of the Blended Wing Body Aircraft. The Athena Vortex Lattice code developed at the Massachusetts Institute of Technology by Mark Drela allows for the aerodynamic analysis of aircraft using the vortex lattice method. Ordinarily, the Athena Vortex Lattice operation requires a text file containing the aircraft geometry to be loaded into the AVL solver in order to determine the aerodynamic forces and moments. However, automated operation will be required to enable integration into a multidisciplinary optimisation framework. Automated AVL operation within the JAVA design environment will nonetheless require a modification and recompilation of AVL source code into an executable file capable of running on windows and other platforms without the 鈥揦11 libraries. This paper describes the procedure for the integrating the FORTRAN written AVL software for automated operation within the multivariate design synthesis optimisation framework for the conceptual design of the BWB aircraft. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=aerodynamics" title="aerodynamics">aerodynamics</a>, <a href="https://publications.waset.org/abstracts/search?q=automation" title=" automation"> automation</a>, <a href="https://publications.waset.org/abstracts/search?q=optimisation" title=" optimisation"> optimisation</a>, <a href="https://publications.waset.org/abstracts/search?q=AVL" title=" AVL"> AVL</a>, <a href="https://publications.waset.org/abstracts/search?q=JNI" title=" JNI"> JNI</a> </p> <a href="https://publications.waset.org/abstracts/22130/integrating-the-athena-vortex-lattice-code-into-a-multivariate-design-synthesis-optimisation-platform-in-java" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/22130.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">582</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">2709</span> In-Flight Aircraft Performance Model Enhancement Using Adaptive Lookup Tables</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Georges%20Ghazi">Georges Ghazi</a>, <a href="https://publications.waset.org/abstracts/search?q=Magali%20Gelhaye"> Magali Gelhaye</a>, <a href="https://publications.waset.org/abstracts/search?q=Ruxandra%20Botez"> Ruxandra Botez</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Over the years, the Flight Management System (FMS) has experienced a continuous improvement of its many features, to the point of becoming the pilot鈥檚 primary interface for flight planning operation on the airplane. With the assistance of the FMS, the concept of distance and time has been completely revolutionized, providing the crew members with the determination of the optimized route (or flight plan) from the departure airport to the arrival airport. To accomplish this function, the FMS needs an accurate Aircraft Performance Model (APM) of the aircraft. In general, APMs that equipped most modern FMSs are established before the entry into service of an individual aircraft, and results from the combination of a set of ordinary differential equations and a set of performance databases. Unfortunately, an aircraft in service is constantly exposed to dynamic loads that degrade its flight characteristics. These degradations endow two main origins: airframe deterioration (control surfaces rigging, seals missing or damaged, etc.) and engine performance degradation (fuel consumption increase for a given thrust). Thus, after several years of service, the performance databases and the APM associated to a specific aircraft are no longer representative enough of the actual aircraft performance. It is important to monitor the trend of the performance deterioration and correct the uncertainties of the aircraft model in order to improve the accuracy the flight management system predictions. The basis of this research lies in the new ability to continuously update an Aircraft Performance Model (APM) during flight using an adaptive lookup table technique. This methodology was developed and applied to the well-known Cessna Citation X business aircraft. For the purpose of this study, a level D Research Aircraft Flight Simulator (RAFS) was used as a test aircraft. According to Federal Aviation Administration the level D is the highest certification level for the flight dynamics modeling. Basically, using data available in the Flight Crew Operating Manual (FCOM), a first APM describing the variation of the engine fan speed and aircraft fuel flow w.r.t flight conditions was derived. This model was next improved using the proposed methodology. To do that, several cruise flights were performed using the RAFS. An algorithm was developed to frequently sample the aircraft sensors measurements during the flight and compare the model prediction with the actual measurements. Based on these comparisons, a correction was performed on the actual APM in order to minimize the error between the predicted data and the measured data. In this way, as the aircraft flies, the APM will be continuously enhanced, making the FMS more and more precise and the prediction of trajectories more realistic and more reliable. The results obtained are very encouraging. Indeed, using the tables initialized with the FCOM data, only a few iterations were needed to reduce the fuel flow prediction error from an average relative error of 12% to 0.3%. Similarly, the FCOM prediction regarding the engine fan speed was reduced from a maximum error deviation of 5.0% to 0.2% after only ten flights. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=aircraft%20performance" title="aircraft performance">aircraft performance</a>, <a href="https://publications.waset.org/abstracts/search?q=cruise" title=" cruise"> cruise</a>, <a href="https://publications.waset.org/abstracts/search?q=trajectory%20optimization" title=" trajectory optimization"> trajectory optimization</a>, <a href="https://publications.waset.org/abstracts/search?q=adaptive%20lookup%20tables" title=" adaptive lookup tables"> adaptive lookup tables</a>, <a href="https://publications.waset.org/abstracts/search?q=Cessna%20Citation%20X" title=" Cessna Citation X"> Cessna Citation X</a> </p> <a href="https://publications.waset.org/abstracts/87528/in-flight-aircraft-performance-model-enhancement-using-adaptive-lookup-tables" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/87528.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">264</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">2708</span> Calculation of the Supersonic Air Intake with the Optimization of the Shock Wave System </h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Elena%20Vinogradova">Elena Vinogradova</a>, <a href="https://publications.waset.org/abstracts/search?q=Aleksei%20Pleshakov"> Aleksei Pleshakov</a>, <a href="https://publications.waset.org/abstracts/search?q=Aleksei%20Yakovlev"> Aleksei Yakovlev</a> </p> <p class="card-text"><strong>Abstract:</strong></p> During the flight of a supersonic aircraft under various conditions (altitude, Mach, etc.), it becomes necessary to coordinate the operating modes of the air intake and engine. On the supersonic aircraft, it鈥檚 been done by changing various control factors (the angle of rotation of the wedge panels and etc.). This paper investigates the possibility of using modern optimization methods to determine the optimal position of the supersonic air intake wedge panels in order to maximize the total pressure recovery coefficient. Modern software allows us to conduct auto-optimization, which determines the optimal position of the control elements of the investigated product to achieve its maximum efficiency. In this work, the flow in the supersonic aircraft inlet has investigated and optimized the operation of the flaps of the supersonic inlet in an aircraft in a 2-D setting. This work has done using ANSYS CFX software. The supersonic aircraft inlet is a flat adjustable external compression inlet. The braking surface is made in the form of a three-stage wedge. The IOSO NM software package was chosen for optimization. Change in the position of the panels of the input device is carried out by changing the angle between the first and second steps of the three-stage wedge. The position of the rest of the panels is changed automatically. Within the framework of the presented work, the position of the moving air intake panel was optimized under fixed flight conditions of the aircraft under a certain engine operating mode. As a result of the numerical modeling, the distribution of total pressure losses was obtained for various cases of the engine operation, depending on the incoming flow velocity and the flight altitude of the aircraft. The results make it possible to obtain the maximum total pressure recovery coefficient under given conditions. Also, the initial geometry was set with a certain angle between the first and second wedge panels. Having performed all the calculations, as well as the subsequent optimization of the aircraft input device, it can be concluded that the initial angle was set sufficiently close to the optimal angle. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=optimal%20angle" title="optimal angle">optimal angle</a>, <a href="https://publications.waset.org/abstracts/search?q=optimization" title=" optimization"> optimization</a>, <a href="https://publications.waset.org/abstracts/search?q=supersonic%20air%20intake" title=" supersonic air intake"> supersonic air intake</a>, <a href="https://publications.waset.org/abstracts/search?q=total%20pressure%20recovery%20coefficient" title=" total pressure recovery coefficient"> total pressure recovery coefficient</a> </p> <a href="https://publications.waset.org/abstracts/135524/calculation-of-the-supersonic-air-intake-with-the-optimization-of-the-shock-wave-system" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/135524.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">242</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">2707</span> Noise of Aircraft Flyovers Affects Reading Saccades</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Svea%20Missfeldt">Svea Missfeldt</a>, <a href="https://publications.waset.org/abstracts/search?q=Rainer%20H%C3%B6ger"> Rainer H枚ger</a> </p> <p class="card-text"><strong>Abstract:</strong></p> A number of studies show that aircraft noise around airports negatively affects the reading comprehension of children attending schools in the neighbourhood. Yet little is known about the underlying mechanisms. Explanatory approaches discuss the attention capturing effect of noise sources which occupy mental capacity. Research suggests that attentional capacities are especially demanded when different modalities are involved at the same time. To explore whether aircraft noise affects reading processes in specific manners, students read texts in variable sound conditions while their eye movements were recorded. Besides noise caused by aircraft flyovers, which represent moving sound sources, saccades were also recorded under the condition of white noise, a natural sound setting and silence for comparison. Data showed an increase in regressive saccades when the sound of moving sources was presented. Interestingly, this effect was significantly high when the aircrafts moved in the opposite of the reading direction. Especially the latter result is not compatible with the hypothesis of a general impairment of cognitive processes by noise where the direction of movement should not have an influence. Reading is assumed to be based on two different attentional mechanisms: overt and covert attention, where the latter supports control and pre-planning of eye movements during reading. We believe that covert attention is affected by moving sound sources, resulting in an enhanced number of backwardly directed saccades. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=aircraft%20noise" title="aircraft noise">aircraft noise</a>, <a href="https://publications.waset.org/abstracts/search?q=attentional%20processes" title=" attentional processes"> attentional processes</a>, <a href="https://publications.waset.org/abstracts/search?q=cognition" title=" cognition"> cognition</a>, <a href="https://publications.waset.org/abstracts/search?q=eye%20movements" title=" eye movements"> eye movements</a>, <a href="https://publications.waset.org/abstracts/search?q=reading%20saccades" title=" reading saccades"> reading saccades</a> </p> <a href="https://publications.waset.org/abstracts/41983/noise-of-aircraft-flyovers-affects-reading-saccades" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/41983.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">328</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">2706</span> Effects of Inlet Distorted Flows on the Performance of an Axial Compressor</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Asad%20Islam">Asad Islam</a>, <a href="https://publications.waset.org/abstracts/search?q=Khalid%20Parvez"> Khalid Parvez</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Compressor fans in modern aircraft engines are of considerate importance, as they provide majority of thrust required by the aircraft. Their challenging environment is frequently subjected to non-uniform inflow conditions. These conditions could be either due to the flight operating requirements such as take-off and landing, wake interference from aircraft fuselage or cross-flow wind conditions. So, in highly maneuverable flights regimes of fighter aircrafts affects the overall performance of an engine. Since the flow in compressor of an aircraft application is highly sensitive because of adverse pressure gradient due to different flow orientations of the aircraft. Therefore, it is prone to unstable operations. This paper presents the study that focuses on axial compressor response to inlet flow orientations for the range of angles as 0 to 15 degrees. For this purpose, NASA Rotor-37 was taken and CFD mesh was developed. The compressor characteristics map was generated for the design conditions of pressure ratio of 2.106 with the rotor operating at rotational velocity of 17188.7 rpm using CFD simulating environment of ANSYS-CFX庐. The grid study was done to see the effects of mesh upon computational solution. Then, the mesh giving the best results, (when validated with the available experimental NASA鈥檚 results); was used for further distortion analysis. The flow in the inlet nozzle was given angle orientations ranging from 0 to 15 degrees. The CFD results are analyzed and discussed with respect to stall margin and flow separations due to induced distortions. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=axial%20compressor" title="axial compressor">axial compressor</a>, <a href="https://publications.waset.org/abstracts/search?q=distortions" title=" distortions"> distortions</a>, <a href="https://publications.waset.org/abstracts/search?q=angle" title=" angle"> angle</a>, <a href="https://publications.waset.org/abstracts/search?q=CFD" title=" CFD"> CFD</a>, <a href="https://publications.waset.org/abstracts/search?q=ANSYS-CFX%C2%AE" title=" ANSYS-CFX庐"> ANSYS-CFX庐</a>, <a href="https://publications.waset.org/abstracts/search?q=bladegen%C2%AE" title=" bladegen庐"> bladegen庐</a> </p> <a href="https://publications.waset.org/abstracts/46801/effects-of-inlet-distorted-flows-on-the-performance-of-an-axial-compressor" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/46801.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">456</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">2705</span> Numerical Crashworthiness Investigations of a Full-Scale Composite Fuselage Section</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Redouane%20Lombarkia">Redouane Lombarkia</a> </p> <p class="card-text"><strong>Abstract:</strong></p> To apply a new material model developed and validated for plain weave fabric CFRP composites usually used in stanchions in sub-cargo section in aircrafts. This work deals with the development of a numerical model of the fuselage section of commercial aircraft based on the pure explicit finite element method FEM within Abaqus/Explicit commercial code. The aim of this work is the evaluation of the energy absorption capabilities of a full-scale composite fuselage section, including sub-cargo stanchions, Drop tests were carried out from a free fall height of about 5 m and impact velocity of about 6 m鈭晄. To asses, the prediction efficiency of the proposed numerical modeling procedure, a comparison with literature existed experimental results was performed. We demonstrate the efficiency of the proposed methodology to well capture crash damage mechanisms compared to experimental results <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=crashworthiness" title="crashworthiness">crashworthiness</a>, <a href="https://publications.waset.org/abstracts/search?q=fuselage%20section" title=" fuselage section"> fuselage section</a>, <a href="https://publications.waset.org/abstracts/search?q=finite%20elements%20method%20%28FEM%29" title=" finite elements method (FEM)"> finite elements method (FEM)</a>, <a href="https://publications.waset.org/abstracts/search?q=stanchions" title=" stanchions"> stanchions</a>, <a href="https://publications.waset.org/abstracts/search?q=specific%20energy%20absorption%20SEA" title=" specific energy absorption SEA"> specific energy absorption SEA</a> </p> <a href="https://publications.waset.org/abstracts/159813/numerical-crashworthiness-investigations-of-a-full-scale-composite-fuselage-section" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/159813.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">95</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">2704</span> Aerodynamic Brake Study of Reducing Braking Distance for High-Speed Trains</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Phatthara%20Surachon">Phatthara Surachon</a>, <a href="https://publications.waset.org/abstracts/search?q=Tosaphol%20Ratniyomchai"> Tosaphol Ratniyomchai</a>, <a href="https://publications.waset.org/abstracts/search?q=Thanatchai%20Kulworawanichpong"> Thanatchai Kulworawanichpong</a> </p> <p class="card-text"><strong>Abstract:</strong></p> This paper presents an aerodynamic brake study of reducing braking distance for high-speed trains (HST) using aerodynamic brakes as inspiration from the applications on the commercial aircraft wings. In case of emergency, both braking distance and stopping time are longer than the usual situation. Therefore, the passenger safety and the HST driving control management are definitely obtained by reducing the time and distance of train braking during emergency situation. Due to the limited study and implementation of the aerodynamic brake in HST, the possibility in use and the effectiveness of the aerodynamic brake to the train dynamic movement during braking are analyzed and considered. Regarding the aircraft鈥檚 flaps that applied in the HST, the areas of the aerodynamic brake acted as an additional drag force during train braking are able to vary depending on the operating angle and the required dynamic braking force. The HST with a varying speed of 200 km/h to 350 km/h is taken as a case study of this paper. The results show that the stopping time and the brake distance are effectively reduced by the aerodynamic brakes. The mechanical brake and its maintenance are effectively getting this benefit by extending its lifetime for longer use. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=high-speed%20train" title="high-speed train">high-speed train</a>, <a href="https://publications.waset.org/abstracts/search?q=aerodynamic%20brake" title=" aerodynamic brake"> aerodynamic brake</a>, <a href="https://publications.waset.org/abstracts/search?q=brake%20distance" title=" brake distance"> brake distance</a>, <a href="https://publications.waset.org/abstracts/search?q=drag%20force" title=" drag force "> drag force </a> </p> <a href="https://publications.waset.org/abstracts/122559/aerodynamic-brake-study-of-reducing-braking-distance-for-high-speed-trains" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/122559.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">198</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">2703</span> Improved Thermal Comfort in Cabin Aircraft with in-Seat Microclimate Conditioning Module</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Mathieu%20Le%20Cam">Mathieu Le Cam</a>, <a href="https://publications.waset.org/abstracts/search?q=Tejaswinee%20Darure"> Tejaswinee Darure</a>, <a href="https://publications.waset.org/abstracts/search?q=Mateusz%20Pawlucki"> Mateusz Pawlucki</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Climate control of cabin aircraft is traditionally conditioned as a single unit by the environmental control system. Cabin temperature is controlled by the crew while passengers of the aircraft have control on the gaspers providing fresh air from the above head area. The small nozzles are difficult to reach and adjust to meet the passenger鈥檚 needs in terms of flow and direction. More dedicated control over the near environment of each passenger can be beneficial in many situations. The European project COCOON, funded under Clean Sky 2, aims at developing and demonstrating a microclimate conditioning module (MCM) integrated into a standard economy 3-seat row. The system developed will lead to improved passenger comfort with more control on their personal thermal area. This study focuses on the assessment of thermal comfort of passengers in the cabin aircraft through simulation on the TAITherm modelling platform. A first analysis investigates thermal comfort and sensation of passengers in varying cabin environmental conditions: from cold to very hot scenarios, with and without MCM installed in the seats. The modelling platform is also used to evaluate the impact of different physiologies of passengers on their thermal comfort as well as different seat locations. Under the current cabin conditions, a passenger of a 50th percentile body size is feeling uncomfortably cool due to the high velocity cabin air ventilation. The simulation shows that the in-seat MCM developed in COCOON project improves the thermal comfort of the passenger. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=cabin%20aircraft" title="cabin aircraft">cabin aircraft</a>, <a href="https://publications.waset.org/abstracts/search?q=in-seat%20HVAC" title=" in-seat HVAC"> in-seat HVAC</a>, <a href="https://publications.waset.org/abstracts/search?q=microclimate%20conditioning%20module" title=" microclimate conditioning module"> microclimate conditioning module</a>, <a href="https://publications.waset.org/abstracts/search?q=thermal%20comfort" title=" thermal comfort"> thermal comfort</a> </p> <a href="https://publications.waset.org/abstracts/132315/improved-thermal-comfort-in-cabin-aircraft-with-in-seat-microclimate-conditioning-module" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/132315.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">200</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">2702</span> Commercial Law Between Custom and Islamic Law</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Mohamed%20Zakareia%20Ghazy%20Aly%20Belal">Mohamed Zakareia Ghazy Aly Belal</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Commercial law is the set of legal rules that apply to business and regulates the trade of trade. The meaning of this is that the commercial law regulates certain relations only that arises as a result of carrying out certain businesses. which are business, as it regulates the activity of a specific sect, the sect of merchants, and the commercial law as other branches of the law has characteristics that distinguish it from other laws and various, and various sources from which its basis is derived from It is the objective or material source. the historical source, the official source and the interpretative source, and we are limited to official sources and explanatory sources. so what do you see what these sources are, and what is their degree and strength in taking it in commercial disputes. The first topic / characteristics of commercial law. Commercial law has become necessary for the world of trade and economics, which cannot be dispensed with, given the reasons that have been set as legal rules for commercial field. In fact, it is sufficient to refer to the stability and stability of the environment, and in exchange for the movement and the speed in which the commercial environment is in addition to confidence and credit. the characteristic of speed and the characteristic of trust, and credit are the ones that justify the existence of commercial law. Business is fast, while civil business is slow, stable and stability. The person concludes civil transactions in his life only a little. And before doing any civil action. he must have a period of thinking and scrutiny, and the investigation is the person who wants the husband, he must have a period of thinking and scrutiny. as if the person who wants to acquire a house to live with with his family, he must search and investigate Discuss the price before the conclusion of a purchase contract. In the commercial field, transactions take place very quickly because the time factor has an important role in concluding deals and achieving profits. This is because the merchant in contracting about a specific deal would cause a loss to the merchant due to the linkage of the commercial law with the fluctuations of the economy and the market. The merchant may also conclude more than one deal in one and short time. And that is due to the absence of commercial law from the formalities and procedures that hinder commercial transactions. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=law" title="law">law</a>, <a href="https://publications.waset.org/abstracts/search?q=commercial%20law" title=" commercial law"> commercial law</a>, <a href="https://publications.waset.org/abstracts/search?q=business" title=" business"> business</a>, <a href="https://publications.waset.org/abstracts/search?q=commercial%20field" title=" commercial field"> commercial field</a> </p> <a href="https://publications.waset.org/abstracts/167000/commercial-law-between-custom-and-islamic-law" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/167000.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">70</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">2701</span> Enhanced Flight Dynamics Model to Simulate the Aircraft Response to Gust Encounters</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Castells%20Pau">Castells Pau</a>, <a href="https://publications.waset.org/abstracts/search?q=Poetsch%20Christophe"> Poetsch Christophe</a> </p> <p class="card-text"><strong>Abstract:</strong></p> The effect of gust and turbulence encounters on aircraft is a wide field of study which allows different approaches, from high-fidelity multidisciplinary simulations to more simplified models adapted to industrial applications. The typical main goal is to predict the gust loads on the aircraft in order to ensure a safe design and achieve certification. Another topic widely studied is the gust loads reduction through an active control law. The impact of gusts on aircraft handling qualities is of interest as well in the analysis of in-service events so as to evaluate the aircraft response and the performance of the flight control laws. Traditionally, gust loads and handling qualities are addressed separately with different models adapted to the specific needs of each discipline. In this paper, an assessment of the differences between both models is presented and a strategy to better account for the physics of gust encounters in a typical flight dynamics model is proposed based on the model used for gust loads analysis. The applied corrections aim to capture the gust unsteady aerodynamics and propagation as well as the effect of dynamic flexibility at low frequencies. Results from the gust loads model at different flight conditions and measures from real events are used for validation. An assessment of a possible extension of steady aerodynamic nonlinearities to low frequency range is also addressed. The proposed corrections provide meaningful means to evaluate the performance and possible adjustments of the flight control laws. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=flight%20dynamics" title="flight dynamics">flight dynamics</a>, <a href="https://publications.waset.org/abstracts/search?q=gust%20loads" title=" gust loads"> gust loads</a>, <a href="https://publications.waset.org/abstracts/search?q=handling%20qualities" title=" handling qualities"> handling qualities</a>, <a href="https://publications.waset.org/abstracts/search?q=unsteady%20aerodynamics" title=" unsteady aerodynamics"> unsteady aerodynamics</a> </p> <a href="https://publications.waset.org/abstracts/93208/enhanced-flight-dynamics-model-to-simulate-the-aircraft-response-to-gust-encounters" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/93208.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">147</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">2700</span> A Study on Shock Formation over a Transonic Aerofoil</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=M.%20Fowsia">M. Fowsia</a>, <a href="https://publications.waset.org/abstracts/search?q=Dominic%20Xavier%20Fernando"> Dominic Xavier Fernando</a>, <a href="https://publications.waset.org/abstracts/search?q=Vinojitha"> Vinojitha</a>, <a href="https://publications.waset.org/abstracts/search?q=Rahamath%20Juliyana"> Rahamath Juliyana</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Aerofoil is a primary element to be designed during the initial phase of creating any new aircraft. It is the component that forms the cross-section of the wing. The wing is used to produce lift force that balances the weight which is acting downwards. The lift force is created due to pressure difference over the top and bottom surface which is caused due to velocity variation. At sub-sonic velocities, for a real fluid, we obtain a smooth flow of air over both the surfaces. In this era of high speed travel, commercial aircraft that can travel faster than speed of sound barrier is required. However transonic velocities cause the formation of shock waves which can cause flow separation over the top and bottom surfaces. In the transonic range, shock waves move across the top and bottom surfaces of the aerofoil, until both the shock waves merge into a single shock wave that is formed near the leading edge of theaerofoil. In this paper, a transonic aerofoil is designed and its aerodynamic properties at different velocities in the Transonic range (M = 0.8; 0.9; 1; 1.1; 1.2) are studied with the help of CFD. The Pressure and Velocity distributions over the top and bottom surfaces of aerofoil are studied and the variations of shock patterns, at different velocities, are analyzed. The analysis can be used to determine the effect of drag divergence on the lift created by the aerofoil. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=transonic%20aerofoil" title="transonic aerofoil">transonic aerofoil</a>, <a href="https://publications.waset.org/abstracts/search?q=cfd" title=" cfd"> cfd</a>, <a href="https://publications.waset.org/abstracts/search?q=drag%20divergence" title=" drag divergence"> drag divergence</a>, <a href="https://publications.waset.org/abstracts/search?q=shock%20formation" title=" shock formation"> shock formation</a>, <a href="https://publications.waset.org/abstracts/search?q=viscous%20flow" title=" viscous flow"> viscous flow</a> </p> <a href="https://publications.waset.org/abstracts/16576/a-study-on-shock-formation-over-a-transonic-aerofoil" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/16576.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">530</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">2699</span> Inflation and Deflation of Aircraft's Tire with Intelligent Tire Pressure Regulation System</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Masoud%20Mirzaee">Masoud Mirzaee</a>, <a href="https://publications.waset.org/abstracts/search?q=Ghobad%20Behzadi%20Pour"> Ghobad Behzadi Pour</a> </p> <p class="card-text"><strong>Abstract:</strong></p> An aircraft tire is designed to tolerate extremely heavy loads for a short duration. The number of tires increases with the weight of the aircraft, as it is needed to be distributed more evenly. Generally, aircraft tires work at high pressure, up to 200 psi (14 bar; 1,400 kPa) for airliners and higher for business jets. Tire assemblies for most aircraft categories provide a recommendation of compressed nitrogen that supports the aircraft鈥檚 weight on the ground, including a mechanism for controlling the aircraft during taxi, takeoff; landing; and traction for braking. Accurate tire pressure is a key factor that enables tire assemblies to perform reliably under high static and dynamic loads. Concerning ambient temperature change, considering the condition in which the temperature between the origin and destination airport was different, tire pressure should be adjusted and inflated to the specified operating pressure at the colder airport. This adjustment superseding the normal tire over an inflation limit of 5 percent at constant ambient temperature is required because the inflation pressure remains constant to support the load of a specified aircraft configuration. On the other hand, without this adjustment, a tire assembly would be significantly under/over-inflated at the destination. Due to an increase of human errors in the aviation industry, exorbitant costs are imposed on the airlines for providing consumable parts such as aircraft tires. The existence of an intelligent system to adjust the aircraft tire pressure based on weight, load, temperature, and weather conditions of origin and destination airports, could have a significant effect on reducing the aircraft maintenance costs, aircraft fuel and further improving the environmental issues related to the air pollution. An intelligent tire pressure regulation system (ITPRS) contains a processing computer, a nitrogen bottle with 1800 psi, and distribution lines. Nitrogen bottle鈥檚 inlet and outlet valves are installed in the main wheel landing gear鈥檚 area and are connected through nitrogen lines to main wheels and nose wheels assy. Controlling and monitoring of nitrogen will be performed by a computer, which is adjusted according to the calculations of received parameters, including the temperature of origin and destination airport, the weight of cargo loads and passengers, fuel quantity, and wind direction. Correct tire inflation and deflation are essential in assuring that tires can withstand the centrifugal forces and heat of normal operations, with an adequate margin of safety for unusual operating conditions such as rejected takeoff and hard landings. ITPRS will increase the performance of the aircraft in all phases of takeoff, landing, and taxi. Moreover, this system will reduce human errors, consumption materials, and stresses imposed on the aircraft body. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=avionic%20system" title="avionic system">avionic system</a>, <a href="https://publications.waset.org/abstracts/search?q=improve%20efficiency" title=" improve efficiency"> improve efficiency</a>, <a href="https://publications.waset.org/abstracts/search?q=ITPRS" title=" ITPRS"> ITPRS</a>, <a href="https://publications.waset.org/abstracts/search?q=human%20error" title=" human error"> human error</a>, <a href="https://publications.waset.org/abstracts/search?q=reduced%20cost" title=" reduced cost"> reduced cost</a>, <a href="https://publications.waset.org/abstracts/search?q=tire%20pressure" title=" tire pressure"> tire pressure</a> </p> <a href="https://publications.waset.org/abstracts/133861/inflation-and-deflation-of-aircrafts-tire-with-intelligent-tire-pressure-regulation-system" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/133861.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">249</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">2698</span> Computational Analysis of Cavity Effect over Aircraft Wing</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=P.%20Booma%20Devi">P. Booma Devi</a>, <a href="https://publications.waset.org/abstracts/search?q=Dilip%20A.%20Shah"> Dilip A. Shah</a> </p> <p class="card-text"><strong>Abstract:</strong></p> This paper seeks the potentials of studying aerodynamic characteristics of inward cavities called dimples, as an alternative to the classical vortex generators. Increasing stalling angle is a greater challenge in wing design. But our examination is primarily focused on increasing lift. In this paper, enhancement of lift is mainly done by introduction of dimple or cavity in a wing. In general, aircraft performance can be enhanced by increasing aerodynamic efficiency that is lift to drag ratio of an aircraft wing. Efficiency improvement can be achieved by improving the maximum lift co-efficient or by reducing the drag co-efficient. At the time of landing aircraft, high angle of attack may lead to stalling of aircraft. To avoid this kind of situation, increase in the stalling angle is warranted. Hence, improved stalling characteristic is the best way to ease landing complexity. Computational analysis is done for the wing segment made of NACA 0012. Simulation is carried out for 30 m/s free stream velocity over plain airfoil and different types of cavities. The wing is modeled in CATIA V5R20 and analyses are carried out using ANSYS CFX. Triangle and square shapes are used as cavities for analysis. Simulations revealed that cavity placed on wing segment shows an increase of maximum lift co-efficient when compared to normal wing configuration. Flow separation is delayed at downstream of the wing by the presence of cavities up to a particular angle of attack. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=lift" title="lift">lift</a>, <a href="https://publications.waset.org/abstracts/search?q=drag%20reduce" title=" drag reduce"> drag reduce</a>, <a href="https://publications.waset.org/abstracts/search?q=square%20dimple" title=" square dimple"> square dimple</a>, <a href="https://publications.waset.org/abstracts/search?q=triangle%20dimple" title=" triangle dimple"> triangle dimple</a>, <a href="https://publications.waset.org/abstracts/search?q=enhancement%20of%20stall%20angle" title=" enhancement of stall angle"> enhancement of stall angle</a> </p> <a href="https://publications.waset.org/abstracts/51224/computational-analysis-of-cavity-effect-over-aircraft-wing" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/51224.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">347</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">2697</span> Retrospective Analysis of Injuries to Flight Attendants in a Commercial Airliner</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=B.%20K.%20Umesh%20Kumar">B. K. Umesh Kumar</a>, <a href="https://publications.waset.org/abstracts/search?q=Waleed%20Al%20Shukaili"> Waleed Al Shukaili</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Air travel is one of the safest modes of travel. Inflight injuries occur due to various factors such as air turbulence, spillage of hot liquids, and fall of improperly stowed overhead baggage. Injuries occur not only to passengers but also to the flight attendants who are handling the passengers throughout the flight. A retrospective study of all records of crew safety report by the captain of the aircraft for all the flights from 01 Mar 2015 to 31 Mar 2019 in a National Carrier of Middle Eastern country, were analyzed. There was one injury to Flight attendant every 1200 flights. Commonest aircraft involved was Boeing. Inflight phase had 82% of all injuries. 63% of accidents involved female Attendants. Commonest age group involved was from 25-30 years. Cart and container injuries were the commonest and accounted for nearly 62% of the total injuries followed by turbulence. Back injuries were the commonest injuries followed by ankle, shoulder, and burns. Mean days of absence from work seen in shoulder injuries 40 days followed by injuries to back, which accounted for 38 Days. Reduction in injuries to flight attendants can be brought about by proper selection of crew, reduction in cart load. Proper maintenance of cart and container plays a major role in prevention of occupational accidents. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=flight%20attendants" title="flight attendants">flight attendants</a>, <a href="https://publications.waset.org/abstracts/search?q=in-flight%20injuries" title=" in-flight injuries"> in-flight injuries</a>, <a href="https://publications.waset.org/abstracts/search?q=types%20of%20injuries" title=" types of injuries"> types of injuries</a>, <a href="https://publications.waset.org/abstracts/search?q=work%20related%20injury%20prevention" title=" work related injury prevention"> work related injury prevention</a> </p> <a href="https://publications.waset.org/abstracts/128217/retrospective-analysis-of-injuries-to-flight-attendants-in-a-commercial-airliner" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/128217.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">124</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">2696</span> Comprehensive Studies on the Aerodynamic Characteristics of Subsonic Scarf Inlets</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=M.%20Jegannath">M. Jegannath</a>, <a href="https://publications.waset.org/abstracts/search?q=V.%20Akshaya"> V. Akshaya</a>, <a href="https://publications.waset.org/abstracts/search?q=B.%20Arunkumar"> B. Arunkumar</a>, <a href="https://publications.waset.org/abstracts/search?q=G.%20Lakshmi%20Soundharya"> G. Lakshmi Soundharya</a>, <a href="https://publications.waset.org/abstracts/search?q=V.%20Thenmozhi"> V. Thenmozhi</a>, <a href="https://publications.waset.org/abstracts/search?q=S.%20Varun"> S. Varun</a>, <a href="https://publications.waset.org/abstracts/search?q=V.%20R.%20S.%20Kumar"> V. R. S. Kumar</a> </p> <p class="card-text"><strong>Abstract:</strong></p> For scarf inlet design, the primary variable of interest is the circumferential extent over which the extended lower lip is formed. In this paper, an attempt has been made to optimize the aerodynamic shape of a subsonic scarf inlet with aerodynamically shaped center-body with a particular value of the circumferential extent. The parametric analytical studies have been carried out using a Spalart-Allmaras turbulence model. From our preliminary studies, we concluded that for a particular value of circumferential extent, there will be an exact shape of the center-body with certain geometric orientation for the existence of an aerodynamically efficient scarf inlet for modern aircraft engines. This numerical study is a pointer towards for the design optimization of scarf inlets for modern aircraft engines. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=aerodynamics%20of%20scarf%20inlets" title="aerodynamics of scarf inlets">aerodynamics of scarf inlets</a>, <a href="https://publications.waset.org/abstracts/search?q=inlet%20design" title=" inlet design"> inlet design</a>, <a href="https://publications.waset.org/abstracts/search?q=modern%20aircraft%20inlets" title=" modern aircraft inlets"> modern aircraft inlets</a>, <a href="https://publications.waset.org/abstracts/search?q=subsonic%20scarf%20inlet" title=" subsonic scarf inlet"> subsonic scarf inlet</a> </p> <a href="https://publications.waset.org/abstracts/77913/comprehensive-studies-on-the-aerodynamic-characteristics-of-subsonic-scarf-inlets" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/77913.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">317</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">2695</span> Jet-Stream Airsail: Study of the Shape and the Behavior of the Connecting Cable</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Christopher%20Frank">Christopher Frank</a>, <a href="https://publications.waset.org/abstracts/search?q=Yoshiki%20Miyairi"> Yoshiki Miyairi</a> </p> <p class="card-text"><strong>Abstract:</strong></p> A jet-stream airsail concept takes advantage of aerology in order to fly without propulsion. Weather phenomena, especially jet streams, are relatively permanent high winds blowing from west to east, located at average altitudes and latitudes in both hemispheres. To continuously extract energy from the jet-stream, the system is composed of a propelled plane and a wind turbine interconnected by a cable. This work presents the aerodynamic characteristics and the behavior of the cable that links the two subsystems and transmits energy from the turbine to the aircraft. Two ways of solving this problem are explored: numerically and analytically. After obtaining the optimal shape of the cross-section of the cable, its behavior is analyzed as a 2D problem solved numerically and analytically. Finally, a 3D extension could be considered by adding lateral forces. The results of this work can be further used in the design process of the overall system: aircraft-turbine. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=jet-stream" title="jet-stream">jet-stream</a>, <a href="https://publications.waset.org/abstracts/search?q=cable" title=" cable"> cable</a>, <a href="https://publications.waset.org/abstracts/search?q=tether" title=" tether"> tether</a>, <a href="https://publications.waset.org/abstracts/search?q=aerodynamics" title=" aerodynamics"> aerodynamics</a>, <a href="https://publications.waset.org/abstracts/search?q=aircraft" title=" aircraft"> aircraft</a>, <a href="https://publications.waset.org/abstracts/search?q=airsail" title=" airsail"> airsail</a>, <a href="https://publications.waset.org/abstracts/search?q=wind" title=" wind"> wind</a> </p> <a href="https://publications.waset.org/abstracts/11611/jet-stream-airsail-study-of-the-shape-and-the-behavior-of-the-connecting-cable" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/11611.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">370</span> </span> </div> </div> <ul class="pagination"> <li class="page-item"><a class="page-link" href="https://publications.waset.org/abstracts/search?q=commercial%20aircraft&page=2" rel="prev">&lsaquo;</a></li> <li class="page-item"><a class="page-link" href="https://publications.waset.org/abstracts/search?q=commercial%20aircraft&page=1">1</a></li> <li class="page-item"><a class="page-link" href="https://publications.waset.org/abstracts/search?q=commercial%20aircraft&page=2">2</a></li> <li class="page-item active"><span class="page-link">3</span></li> <li class="page-item"><a class="page-link" href="https://publications.waset.org/abstracts/search?q=commercial%20aircraft&page=4">4</a></li> <li class="page-item"><a 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