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id="siteSub" class="noprint">From Wikipedia, the free encyclopedia</div> </div> <div id="contentSub"><div id="mw-content-subtitle"></div></div> <div id="mw-content-text" class="mw-body-content"><div class="mw-content-ltr mw-parser-output" lang="en" dir="ltr"><div class="shortdescription nomobile noexcerpt noprint searchaux" style="display:none">Term in fluid mechanics</div> <p>In <a href="/wiki/Fluid_mechanics" title="Fluid mechanics">fluid mechanics</a> the term <b>static pressure</b> refers to a term in <a href="/wiki/Bernoulli%27s_equation" class="mw-redirect" title="Bernoulli's equation">Bernoulli's equation</a> written words as <i>static pressure + <a href="/wiki/Dynamic_pressure" title="Dynamic pressure">dynamic pressure</a> = total pressure</i>. Since <a href="/wiki/Pressure" title="Pressure">pressure</a> measurements at any single point in a fluid always give the static pressure value, the 'static' is often dropped. In the design and operation of <a href="/wiki/Aircraft" title="Aircraft">aircraft</a>, <i>static pressure</i> is the <a href="/wiki/Air_pressure" class="mw-redirect" title="Air pressure">air pressure</a> in the aircraft's <a href="/wiki/Pitot-static_system#Static_pressure" class="mw-redirect" title="Pitot-static system">static pressure system</a>. </p> <meta property="mw:PageProp/toc" /> <div class="mw-heading mw-heading2"><h2 id="Static_pressure_in_fluid_dynamics">Static pressure in fluid dynamics</h2><span class="mw-editsection"><span class="mw-editsection-bracket">[</span><a href="/w/index.php?title=Static_pressure&action=edit&section=1" title="Edit section: Static pressure in fluid dynamics"><span>edit</span></a><span class="mw-editsection-bracket">]</span></span></div> <p>The concept of <a href="/wiki/Pressure" title="Pressure">pressure</a> is central to the study of fluids. A pressure can be identified for every point in a body of fluid, regardless of whether the fluid is in motion. Pressure can be <a href="/wiki/Pressure_measurement" title="Pressure measurement">measured</a> using an <a href="/wiki/Barometer#Aneroid_barometers" title="Barometer">aneroid</a>, <a href="/wiki/Pressure_measurement#Bourdon_gauge" title="Pressure measurement">Bourdon tube</a>, mercury column, or various other methods. </p><p>The concepts of <i>total pressure</i> and <i><a href="/wiki/Dynamic_pressure" title="Dynamic pressure">dynamic pressure</a></i> arise from <a href="/wiki/Bernoulli%27s_equation" class="mw-redirect" title="Bernoulli's equation">Bernoulli's equation</a> and are significant in the study of all fluid flows. These two pressures are not pressures in the usual sense - they cannot be measured using a <a href="/wiki/Pressure_sensor" class="mw-redirect" title="Pressure sensor">pressure sensor</a>. To avoid potential ambiguity when referring to <a href="/wiki/Pressure" title="Pressure">pressure</a> in fluid dynamics, many authors use the term <i>static pressure</i> to distinguish it from <i>total pressure</i> and <i>dynamic pressure</i>; the term <i>static pressure</i> is identical to the term <i>pressure</i>, and can be identified for every point in a fluid flow field. The static pressure can be measured in flowing fluid using a hole or tube which is perpendicular to the flow. </p><p>In <i>Aerodynamics</i>, L.J. Clancy<sup id="cite_ref-1" class="reference"><a href="#cite_note-1"><span class="cite-bracket">[</span>1<span class="cite-bracket">]</span></a></sup> writes: "To distinguish it from the total and dynamic pressures, the actual pressure of the fluid, which is associated not with its motion but with its state, is often referred to as the static pressure, but where the term pressure alone is used it refers to this static pressure." </p><p><a href="/wiki/Bernoulli%27s_equation" class="mw-redirect" title="Bernoulli's equation">Bernoulli's equation</a> is foundational to the dynamics of <a href="/wiki/Incompressible_fluid" class="mw-redirect" title="Incompressible fluid">incompressible fluids</a>. In many fluid flow situations of interest, changes in elevation are insignificant and can be ignored. With this simplification, Bernoulli's equation for incompressible flows can be expressed as<sup id="cite_ref-2" class="reference"><a href="#cite_note-2"><span class="cite-bracket">[</span>2<span class="cite-bracket">]</span></a></sup><sup id="cite_ref-3" class="reference"><a href="#cite_note-3"><span class="cite-bracket">[</span>3<span class="cite-bracket">]</span></a></sup><sup id="cite_ref-4" class="reference"><a href="#cite_note-4"><span class="cite-bracket">[</span>4<span class="cite-bracket">]</span></a></sup> </p> <dl><dd><span class="mwe-math-element"><span class="mwe-math-mathml-inline mwe-math-mathml-a11y" style="display: none;"><math xmlns="http://www.w3.org/1998/Math/MathML" alttext="{\displaystyle P+{\frac {1}{2}}\rho v^{2}=P_{0},}"> <semantics> <mrow class="MJX-TeXAtom-ORD"> <mstyle displaystyle="true" scriptlevel="0"> <mi>P</mi> <mo>+</mo> <mrow class="MJX-TeXAtom-ORD"> <mfrac> <mn>1</mn> <mn>2</mn> </mfrac> </mrow> <mi>ρ</mi> <msup> <mi>v</mi> <mrow class="MJX-TeXAtom-ORD"> <mn>2</mn> </mrow> </msup> <mo>=</mo> <msub> <mi>P</mi> <mrow class="MJX-TeXAtom-ORD"> <mn>0</mn> </mrow> </msub> <mo>,</mo> </mstyle> </mrow> <annotation encoding="application/x-tex">{\displaystyle P+{\frac {1}{2}}\rho v^{2}=P_{0},}</annotation> </semantics> </math></span><img src="https://wikimedia.org/api/rest_v1/media/math/render/svg/8ffd8603d073b9cf61a0515f0994456dd4d6acdc" class="mwe-math-fallback-image-inline mw-invert skin-invert" aria-hidden="true" style="vertical-align: -1.838ex; width:16.26ex; height:5.176ex;" alt="{\displaystyle P+{\frac {1}{2}}\rho v^{2}=P_{0},}" /></span></dd></dl> <p>where: </p> <ul><li><span class="mwe-math-element"><span class="mwe-math-mathml-inline mwe-math-mathml-a11y" style="display: none;"><math xmlns="http://www.w3.org/1998/Math/MathML" alttext="{\displaystyle P\;}"> <semantics> <mrow class="MJX-TeXAtom-ORD"> <mstyle displaystyle="true" scriptlevel="0"> <mi>P</mi> <mspace width="thickmathspace"></mspace> </mstyle> </mrow> <annotation encoding="application/x-tex">{\displaystyle P\;}</annotation> </semantics> </math></span><img src="https://wikimedia.org/api/rest_v1/media/math/render/svg/27575f9e8fb516e2e56157dc85557683cf06eb73" class="mwe-math-fallback-image-inline mw-invert skin-invert" aria-hidden="true" style="vertical-align: -0.338ex; width:2.391ex; height:2.176ex;" alt="{\displaystyle P\;}" /></span> is static pressure,</li> <li><span class="mwe-math-element"><span class="mwe-math-mathml-inline mwe-math-mathml-a11y" style="display: none;"><math xmlns="http://www.w3.org/1998/Math/MathML" alttext="{\displaystyle {\frac {1}{2}}\rho v^{2}}"> <semantics> <mrow class="MJX-TeXAtom-ORD"> <mstyle displaystyle="true" scriptlevel="0"> <mrow class="MJX-TeXAtom-ORD"> <mfrac> <mn>1</mn> <mn>2</mn> </mfrac> </mrow> <mi>ρ</mi> <msup> <mi>v</mi> <mrow class="MJX-TeXAtom-ORD"> <mn>2</mn> </mrow> </msup> </mstyle> </mrow> <annotation encoding="application/x-tex">{\displaystyle {\frac {1}{2}}\rho v^{2}}</annotation> </semantics> </math></span><img src="https://wikimedia.org/api/rest_v1/media/math/render/svg/4b3b9a0d4952ff4255f64c3e8bb52608f6dc1b39" class="mwe-math-fallback-image-inline mw-invert skin-invert" aria-hidden="true" style="vertical-align: -1.838ex; width:5.382ex; height:5.176ex;" alt="{\displaystyle {\frac {1}{2}}\rho v^{2}}" /></span> is <a href="/wiki/Dynamic_pressure" title="Dynamic pressure">dynamic pressure</a>, usually denoted by <span class="mwe-math-element"><span class="mwe-math-mathml-inline mwe-math-mathml-a11y" style="display: none;"><math xmlns="http://www.w3.org/1998/Math/MathML" alttext="{\displaystyle q\;}"> <semantics> <mrow class="MJX-TeXAtom-ORD"> <mstyle displaystyle="true" scriptlevel="0"> <mi>q</mi> <mspace width="thickmathspace"></mspace> </mstyle> </mrow> <annotation encoding="application/x-tex">{\displaystyle q\;}</annotation> </semantics> </math></span><img src="https://wikimedia.org/api/rest_v1/media/math/render/svg/57ea4f873b421aba4bbb9330389fe1cab3f374fb" class="mwe-math-fallback-image-inline mw-invert skin-invert" aria-hidden="true" style="vertical-align: -0.671ex; width:1.715ex; height:2.009ex;" alt="{\displaystyle q\;}" /></span>,</li> <li><span class="mwe-math-element"><span class="mwe-math-mathml-inline mwe-math-mathml-a11y" style="display: none;"><math xmlns="http://www.w3.org/1998/Math/MathML" alttext="{\displaystyle \rho \,}"> <semantics> <mrow class="MJX-TeXAtom-ORD"> <mstyle displaystyle="true" scriptlevel="0"> <mi>ρ</mi> <mspace width="thinmathspace"></mspace> </mstyle> </mrow> <annotation encoding="application/x-tex">{\displaystyle \rho \,}</annotation> </semantics> </math></span><img src="https://wikimedia.org/api/rest_v1/media/math/render/svg/a1d651c28959a0f15127c097ff4488b123d9e708" class="mwe-math-fallback-image-inline mw-invert skin-invert" aria-hidden="true" style="vertical-align: -0.838ex; width:1.589ex; height:2.176ex;" alt="{\displaystyle \rho \,}" /></span> is the <a href="/wiki/Density" title="Density">density</a> of the fluid,</li> <li><span class="mwe-math-element"><span class="mwe-math-mathml-inline mwe-math-mathml-a11y" style="display: none;"><math xmlns="http://www.w3.org/1998/Math/MathML" alttext="{\displaystyle v\,}"> <semantics> <mrow class="MJX-TeXAtom-ORD"> <mstyle displaystyle="true" scriptlevel="0"> <mi>v</mi> <mspace width="thinmathspace"></mspace> </mstyle> </mrow> <annotation encoding="application/x-tex">{\displaystyle v\,}</annotation> </semantics> </math></span><img src="https://wikimedia.org/api/rest_v1/media/math/render/svg/8b67d1fd725a759a151374b793113d7a78a65da4" class="mwe-math-fallback-image-inline mw-invert skin-invert" aria-hidden="true" style="vertical-align: -0.338ex; width:1.515ex; height:1.676ex;" alt="{\displaystyle v\,}" /></span> is the <a href="/wiki/Flow_velocity" title="Flow velocity">flow velocity</a>, and</li> <li><span class="mwe-math-element"><span class="mwe-math-mathml-inline mwe-math-mathml-a11y" style="display: none;"><math xmlns="http://www.w3.org/1998/Math/MathML" alttext="{\displaystyle P_{0}\;}"> <semantics> <mrow class="MJX-TeXAtom-ORD"> <mstyle displaystyle="true" scriptlevel="0"> <msub> <mi>P</mi> <mrow class="MJX-TeXAtom-ORD"> <mn>0</mn> </mrow> </msub> <mspace width="thickmathspace"></mspace> </mstyle> </mrow> <annotation encoding="application/x-tex">{\displaystyle P_{0}\;}</annotation> </semantics> </math></span><img src="https://wikimedia.org/api/rest_v1/media/math/render/svg/74ad5707df690e9d00b055c9544dbad8c015edc1" class="mwe-math-fallback-image-inline mw-invert skin-invert" aria-hidden="true" style="vertical-align: -0.671ex; width:3.192ex; height:2.509ex;" alt="{\displaystyle P_{0}\;}" /></span> is total pressure which is constant along any <a href="/wiki/Streamlines,_streaklines,_and_pathlines" title="Streamlines, streaklines, and pathlines">streamline</a>. It is also known as the <a href="/wiki/Stagnation_pressure" title="Stagnation pressure">stagnation pressure</a>.</li></ul> <p>Every point in a steadily flowing fluid, regardless of the fluid speed at that point, has its own static pressure <span class="mwe-math-element"><span class="mwe-math-mathml-inline mwe-math-mathml-a11y" style="display: none;"><math xmlns="http://www.w3.org/1998/Math/MathML" alttext="{\displaystyle P}"> <semantics> <mrow class="MJX-TeXAtom-ORD"> <mstyle displaystyle="true" scriptlevel="0"> <mi>P</mi> </mstyle> </mrow> <annotation encoding="application/x-tex">{\displaystyle P}</annotation> </semantics> </math></span><img src="https://wikimedia.org/api/rest_v1/media/math/render/svg/b4dc73bf40314945ff376bd363916a738548d40a" class="mwe-math-fallback-image-inline mw-invert skin-invert" aria-hidden="true" style="vertical-align: -0.338ex; width:1.745ex; height:2.176ex;" alt="{\displaystyle P}" /></span>, dynamic pressure <span class="mwe-math-element"><span class="mwe-math-mathml-inline mwe-math-mathml-a11y" style="display: none;"><math xmlns="http://www.w3.org/1998/Math/MathML" alttext="{\displaystyle q}"> <semantics> <mrow class="MJX-TeXAtom-ORD"> <mstyle displaystyle="true" scriptlevel="0"> <mi>q</mi> </mstyle> </mrow> <annotation encoding="application/x-tex">{\displaystyle q}</annotation> </semantics> </math></span><img src="https://wikimedia.org/api/rest_v1/media/math/render/svg/06809d64fa7c817ffc7e323f85997f783dbdf71d" class="mwe-math-fallback-image-inline mw-invert skin-invert" aria-hidden="true" style="vertical-align: -0.671ex; width:1.07ex; height:2.009ex;" alt="{\displaystyle q}" /></span>, and total pressure <span class="mwe-math-element"><span class="mwe-math-mathml-inline mwe-math-mathml-a11y" style="display: none;"><math xmlns="http://www.w3.org/1998/Math/MathML" alttext="{\displaystyle P_{0}}"> <semantics> <mrow class="MJX-TeXAtom-ORD"> <mstyle displaystyle="true" scriptlevel="0"> <msub> <mi>P</mi> <mrow class="MJX-TeXAtom-ORD"> <mn>0</mn> </mrow> </msub> </mstyle> </mrow> <annotation encoding="application/x-tex">{\displaystyle P_{0}}</annotation> </semantics> </math></span><img src="https://wikimedia.org/api/rest_v1/media/math/render/svg/671bd891701e0d6cfa6da0114a5dd64233b58709" class="mwe-math-fallback-image-inline mw-invert skin-invert" aria-hidden="true" style="vertical-align: -0.671ex; width:2.547ex; height:2.509ex;" alt="{\displaystyle P_{0}}" /></span>. Static pressure and dynamic pressure are likely to vary significantly throughout the fluid but total pressure is constant along each streamline. In <a href="/wiki/Conservative_vector_field#Vorticity" title="Conservative vector field">irrotational flow</a>, total pressure is the same on all streamlines and is therefore constant throughout the flow.<sup id="cite_ref-5" class="reference"><a href="#cite_note-5"><span class="cite-bracket">[</span>5<span class="cite-bracket">]</span></a></sup> </p><p>The simplified form of Bernoulli's equation can be summarised in the following memorable word equation:<sup id="cite_ref-NASABernoulli_6-0" class="reference"><a href="#cite_note-NASABernoulli-6"><span class="cite-bracket">[</span>6<span class="cite-bracket">]</span></a></sup><sup id="cite_ref-7" class="reference"><a href="#cite_note-7"><span class="cite-bracket">[</span>7<span class="cite-bracket">]</span></a></sup><sup id="cite_ref-8" class="reference"><a href="#cite_note-8"><span class="cite-bracket">[</span>8<span class="cite-bracket">]</span></a></sup> </p> <dl><dd><i>static pressure + dynamic pressure = total pressure</i>.</dd></dl> <p>This simplified form of Bernoulli's equation is fundamental to an understanding of the design and operation of ships, low speed aircraft, and airspeed indicators for low speed aircraft – that is aircraft whose maximum speed will be less than about 30% of the <a href="/wiki/Speed_of_sound" title="Speed of sound">speed of sound</a>. </p><p>As a consequence of the widespread understanding of the term <i><a class="mw-selflink selflink">static pressure</a></i> in relation to Bernoulli's equation, many authors<sup id="cite_ref-9" class="reference"><a href="#cite_note-9"><span class="cite-bracket">[</span>9<span class="cite-bracket">]</span></a></sup> in the field of fluid dynamics also use <i>static pressure</i> rather than <i>pressure</i> in applications not directly related to <a href="/wiki/Bernoulli%27s_principle" title="Bernoulli's principle">Bernoulli's equation</a>. </p><p>The <a href="/wiki/British_Standards_Institution" class="mw-redirect" title="British Standards Institution">British Standards Institution</a>, in its Standard<sup id="cite_ref-10" class="reference"><a href="#cite_note-10"><span class="cite-bracket">[</span>10<span class="cite-bracket">]</span></a></sup> <i>Glossary of Aeronautical Terms</i>, gives the following definition: </p> <dl><dd><i>4412 <b>Static pressure</b> The pressure at a point on a body moving with the fluid.</i></dd></dl> <div class="mw-heading mw-heading2"><h2 id="Static_pressure_in_design_and_operation_of_aircraft">Static pressure in design and operation of aircraft</h2><span class="mw-editsection"><span class="mw-editsection-bracket">[</span><a href="/w/index.php?title=Static_pressure&action=edit&section=2" title="Edit section: Static pressure in design and operation of aircraft"><span>edit</span></a><span class="mw-editsection-bracket">]</span></span></div> <p>An aircraft's <a href="/wiki/Pitot-static_system#Static_pressure" class="mw-redirect" title="Pitot-static system">static pressure system</a> is the key input to its <a href="/wiki/Altimeter" title="Altimeter">altimeter</a> and, along with the <a href="/wiki/Pitot-static_system#Pitot_pressure" class="mw-redirect" title="Pitot-static system">pitot pressure system</a>, also drives the <a href="/wiki/Airspeed_indicator" title="Airspeed indicator">airspeed indicator</a>.<sup id="cite_ref-11" class="reference"><a href="#cite_note-11"><span class="cite-bracket">[</span>11<span class="cite-bracket">]</span></a></sup> </p><p>The static pressure system is open to the aircraft's exterior through a small opening called the <a href="/wiki/Pitot-static_system#Pitot-static_pressure" class="mw-redirect" title="Pitot-static system">static port</a>, which allows sensing the ambient atmospheric pressure at the <a href="/wiki/Altitude#Altitude_in_Aviation" title="Altitude">altitude</a> at which the aircraft is flying. In flight, the air pressure varies slightly at different positions around the aircraft's exterior, so designers must select the static ports' locations carefully. Wherever they are located, the air pressure that the ports observe will generally be affected by the aircraft's instantaneous <a href="/wiki/Angle_of_attack" title="Angle of attack">angle of attack</a>.<sup id="cite_ref-12" class="reference"><a href="#cite_note-12"><span class="cite-bracket">[</span>12<span class="cite-bracket">]</span></a></sup> The difference between that observed pressure and the actual atmospheric pressure (at altitude) causes a small <a href="/wiki/Position_error" title="Position error">position error</a> in the instruments' indicated altitude and airspeed.<sup id="cite_ref-13" class="reference"><a href="#cite_note-13"><span class="cite-bracket">[</span>13<span class="cite-bracket">]</span></a></sup><sup id="cite_ref-14" class="reference"><a href="#cite_note-14"><span class="cite-bracket">[</span>14<span class="cite-bracket">]</span></a></sup> A designer's objective in locating the static port is to minimize the resulting position error across the aircraft's operating range of weight and airspeed. </p><p>Many authors describe the atmospheric pressure at the altitude at which the aircraft is flying as the <i><a href="/wiki/Freestream" title="Freestream">freestream</a> static pressure</i>. At least one author takes a different approach in order to avoid a need for the expression <i>freestream static pressure</i>. Gracey has written "The static pressure is the atmospheric pressure at the flight level of the aircraft".<sup id="cite_ref-15" class="reference"><a href="#cite_note-15"><span class="cite-bracket">[</span>15<span class="cite-bracket">]</span></a></sup><sup id="cite_ref-16" class="reference"><a href="#cite_note-16"><span class="cite-bracket">[</span>16<span class="cite-bracket">]</span></a></sup> Gracey then refers to the air pressure at any point close to the aircraft as the <i>local static pressure</i>. </p> <div class="mw-heading mw-heading2"><h2 id="Static_pressure_in_fluid_statics">Static pressure in fluid statics</h2><span class="mw-editsection"><span class="mw-editsection-bracket">[</span><a href="/w/index.php?title=Static_pressure&action=edit&section=3" title="Edit section: Static pressure in fluid statics"><span>edit</span></a><span class="mw-editsection-bracket">]</span></span></div> <p>The term <i><a href="/wiki/Hydrostatics#Hydrostatic_pressure" title="Hydrostatics">(hydro)static pressure</a></i> is sometimes used in <a href="/wiki/Fluid_statics" class="mw-redirect" title="Fluid statics">fluid statics</a> to refer to the pressure of a fluid at a nominated depth in the fluid. In fluid statics the fluid is stationary everywhere and the concepts of dynamic pressure and total pressure are not applicable. Consequently, there is little risk of ambiguity in using the term <i>pressure</i>, but some authors<sup id="cite_ref-17" class="reference"><a href="#cite_note-17"><span class="cite-bracket">[</span>17<span class="cite-bracket">]</span></a></sup> choose to use <i>static pressure</i> in some situations. </p> <div class="mw-heading mw-heading2"><h2 id="See_also">See also</h2><span class="mw-editsection"><span class="mw-editsection-bracket">[</span><a href="/w/index.php?title=Static_pressure&action=edit&section=4" title="Edit section: See also"><span>edit</span></a><span class="mw-editsection-bracket">]</span></span></div> <ul><li><a href="/wiki/Pascal%27s_law" title="Pascal's law">Pascal's law</a></li> <li><a href="/wiki/Stagnation_pressure" title="Stagnation pressure">Stagnation pressure</a></li> <li><a href="/wiki/Standard_conditions_for_temperature_and_pressure" class="mw-redirect" title="Standard conditions for temperature and pressure">Standard conditions for temperature and pressure</a></li></ul> <div class="mw-heading mw-heading2"><h2 id="Notes">Notes</h2><span class="mw-editsection"><span class="mw-editsection-bracket">[</span><a href="/w/index.php?title=Static_pressure&action=edit&section=5" title="Edit section: Notes"><span>edit</span></a><span class="mw-editsection-bracket">]</span></span></div> <style data-mw-deduplicate="TemplateStyles:r1239543626">.mw-parser-output .reflist{margin-bottom:0.5em;list-style-type:decimal}@media screen{.mw-parser-output .reflist{font-size:90%}}.mw-parser-output .reflist .references{font-size:100%;margin-bottom:0;list-style-type:inherit}.mw-parser-output .reflist-columns-2{column-width:30em}.mw-parser-output .reflist-columns-3{column-width:25em}.mw-parser-output .reflist-columns{margin-top:0.3em}.mw-parser-output .reflist-columns ol{margin-top:0}.mw-parser-output .reflist-columns li{page-break-inside:avoid;break-inside:avoid-column}.mw-parser-output .reflist-upper-alpha{list-style-type:upper-alpha}.mw-parser-output .reflist-upper-roman{list-style-type:upper-roman}.mw-parser-output .reflist-lower-alpha{list-style-type:lower-alpha}.mw-parser-output .reflist-lower-greek{list-style-type:lower-greek}.mw-parser-output .reflist-lower-roman{list-style-type:lower-roman}</style><div class="reflist reflist-columns references-column-width reflist-columns-2"> <ol class="references"> <li id="cite_note-1"><span class="mw-cite-backlink"><b><a href="#cite_ref-1">^</a></b></span> <span class="reference-text">Clancy, L.J., <i>Aerodynamics</i>, page 21</span> </li> <li id="cite_note-2"><span class="mw-cite-backlink"><b><a href="#cite_ref-2">^</a></b></span> <span class="reference-text">Clancy, L.J., <i>Aerodynamics</i>, equation 3.13</span> </li> <li id="cite_note-3"><span class="mw-cite-backlink"><b><a href="#cite_ref-3">^</a></b></span> <span class="reference-text">Hurt, H.H. Jr, (1960), <i>Aerodynamics for Naval Aviators</i>, page 9, A National Flight Shop Reprint, Florida</span> </li> <li id="cite_note-4"><span class="mw-cite-backlink"><b><a href="#cite_ref-4">^</a></b></span> <span class="reference-text">Anderson, J.D. Jr, <i>Fundamentals of Aerodynamics</i>, 4th edition – page 212, McGraw-Hill, New York. <style data-mw-deduplicate="TemplateStyles:r1238218222">.mw-parser-output cite.citation{font-style:inherit;word-wrap:break-word}.mw-parser-output .citation q{quotes:"\"""\"""'""'"}.mw-parser-output .citation:target{background-color:rgba(0,127,255,0.133)}.mw-parser-output .id-lock-free.id-lock-free a{background:url("//upload.wikimedia.org/wikipedia/commons/6/65/Lock-green.svg")right 0.1em center/9px no-repeat}.mw-parser-output .id-lock-limited.id-lock-limited a,.mw-parser-output .id-lock-registration.id-lock-registration a{background:url("//upload.wikimedia.org/wikipedia/commons/d/d6/Lock-gray-alt-2.svg")right 0.1em center/9px no-repeat}.mw-parser-output .id-lock-subscription.id-lock-subscription a{background:url("//upload.wikimedia.org/wikipedia/commons/a/aa/Lock-red-alt-2.svg")right 0.1em center/9px no-repeat}.mw-parser-output .cs1-ws-icon a{background:url("//upload.wikimedia.org/wikipedia/commons/4/4c/Wikisource-logo.svg")right 0.1em center/12px no-repeat}body:not(.skin-timeless):not(.skin-minerva) .mw-parser-output .id-lock-free a,body:not(.skin-timeless):not(.skin-minerva) .mw-parser-output .id-lock-limited a,body:not(.skin-timeless):not(.skin-minerva) .mw-parser-output .id-lock-registration a,body:not(.skin-timeless):not(.skin-minerva) .mw-parser-output .id-lock-subscription a,body:not(.skin-timeless):not(.skin-minerva) .mw-parser-output .cs1-ws-icon a{background-size:contain;padding:0 1em 0 0}.mw-parser-output .cs1-code{color:inherit;background:inherit;border:none;padding:inherit}.mw-parser-output .cs1-hidden-error{display:none;color:var(--color-error,#d33)}.mw-parser-output .cs1-visible-error{color:var(--color-error,#d33)}.mw-parser-output .cs1-maint{display:none;color:#085;margin-left:0.3em}.mw-parser-output .cs1-kern-left{padding-left:0.2em}.mw-parser-output .cs1-kern-right{padding-right:0.2em}.mw-parser-output .citation .mw-selflink{font-weight:inherit}@media screen{.mw-parser-output .cs1-format{font-size:95%}html.skin-theme-clientpref-night .mw-parser-output .cs1-maint{color:#18911f}}@media screen and (prefers-color-scheme:dark){html.skin-theme-clientpref-os .mw-parser-output .cs1-maint{color:#18911f}}</style><a href="/wiki/ISBN_(identifier)" class="mw-redirect" title="ISBN (identifier)">ISBN</a> <a href="/wiki/Special:BookSources/978-0-07-295046-5" title="Special:BookSources/978-0-07-295046-5">978-0-07-295046-5</a></span> </li> <li id="cite_note-5"><span class="mw-cite-backlink"><b><a href="#cite_ref-5">^</a></b></span> <span class="reference-text">A.M. Kuethe and J.D. Schetzer (1959), <i>Foundations of Aerodynamics</i>, Section 3.5 (2nd edition), John Wiley & Sons, Inc. New York <link rel="mw-deduplicated-inline-style" href="mw-data:TemplateStyles:r1238218222" /><a href="/wiki/ISBN_(identifier)" class="mw-redirect" title="ISBN (identifier)">ISBN</a> <a href="/wiki/Special:BookSources/0-471-50952-3" title="Special:BookSources/0-471-50952-3">0-471-50952-3</a></span> </li> <li id="cite_note-NASABernoulli-6"><span class="mw-cite-backlink"><b><a href="#cite_ref-NASABernoulli_6-0">^</a></b></span> <span class="reference-text"><link rel="mw-deduplicated-inline-style" href="mw-data:TemplateStyles:r1238218222" /><cite class="citation web cs1"><a rel="nofollow" class="external text" href="https://wright.nasa.gov/airplane/bern.html">"Bernoulli's Equation"</a>. <i>nasa.gov</i>. <a href="/wiki/Glenn_Research_Center" title="Glenn Research Center">NASA Glenn Research Center</a><span class="reference-accessdate">. Retrieved <span class="nowrap">3 May</span> 2022</span>.</cite><span title="ctx_ver=Z39.88-2004&rft_val_fmt=info%3Aofi%2Ffmt%3Akev%3Amtx%3Ajournal&rft.genre=unknown&rft.jtitle=nasa.gov&rft.atitle=Bernoulli%27s+Equation&rft_id=https%3A%2F%2Fwright.nasa.gov%2Fairplane%2Fbern.html&rfr_id=info%3Asid%2Fen.wikipedia.org%3AStatic+pressure" class="Z3988"></span></span> </li> <li id="cite_note-7"><span class="mw-cite-backlink"><b><a href="#cite_ref-7">^</a></b></span> <span class="reference-text">Clancy, L.J., <i>Aerodynamics</i>, Section 3.5</span> </li> <li id="cite_note-8"><span class="mw-cite-backlink"><b><a href="#cite_ref-8">^</a></b></span> <span class="reference-text">"The total pressure is composed of two parts, the static pressure and the dynamic pressure". Streeter, V.L., <i>Fluid Mechanics</i> 4th edition – page 404</span> </li> <li id="cite_note-9"><span class="mw-cite-backlink"><b><a href="#cite_ref-9">^</a></b></span> <span class="reference-text">For example: Abbott, I.H. and Von Doenhoff, A.E. (1949) <i>Theory of Wing Sections</i>, Navier-Stokes equations - section 5.4. Dover Publications, Inc., New York. Standard Book Number 486-60586-8</span> </li> <li id="cite_note-10"><span class="mw-cite-backlink"><b><a href="#cite_ref-10">^</a></b></span> <span class="reference-text">British Standard BS 185: Part 1: 1950 <i>Glossary of Aeronautical Terms</i></span> </li> <li id="cite_note-11"><span class="mw-cite-backlink"><b><a href="#cite_ref-11">^</a></b></span> <span class="reference-text">Lombardo, D.A., <i>Aircraft Systems</i>, 2nd edition – chapter 2</span> </li> <li id="cite_note-12"><span class="mw-cite-backlink"><b><a href="#cite_ref-12">^</a></b></span> <span class="reference-text">"It is virtually impossible to find a position where the static pressure is always exactly the same as the pressure in the free airstream away from the aircraft". Kermode, A.C., <i>Mechanics of Flight</i>, 10th edition – page 65</span> </li> <li id="cite_note-13"><span class="mw-cite-backlink"><b><a href="#cite_ref-13">^</a></b></span> <span class="reference-text">Kermode, A.C., <i>Mechanics of Flight</i>, 10th Edition – page 65</span> </li> <li id="cite_note-14"><span class="mw-cite-backlink"><b><a href="#cite_ref-14">^</a></b></span> <span class="reference-text">"Of these errors the error in detection of static pressure is generally the most serious and has the special name,<i>position error</i>." Dommasch, D.O., Sherby, S.S., and Connolly, T.F. (1967) <i>Airplane Aerodynamics</i>, 4th edition – page 51, Pitman Publishing Corp., New York</span> </li> <li id="cite_note-15"><span class="mw-cite-backlink"><b><a href="#cite_ref-15">^</a></b></span> <span class="reference-text">Gracey, William, <a rel="nofollow" class="external text" href="https://ntrs.nasa.gov/api/citations/19800015804/downloads/19800015804.pdf"><i>Measurement of aircraft speed and altitude</i></a> NASA, RP-1046, page 1</span> </li> <li id="cite_note-16"><span class="mw-cite-backlink"><b><a href="#cite_ref-16">^</a></b></span> <span class="reference-text">Gracey, William, <i>Measurement of Aircraft Speed and Altitude</i>, page 1</span> </li> <li id="cite_note-17"><span class="mw-cite-backlink"><b><a href="#cite_ref-17">^</a></b></span> <span class="reference-text">For example: "The pressure in cases where no motion is occurring is referred to as static pressure." Curtis D. Johnson, <a rel="nofollow" class="external text" href="http://zone.ni.com/devzone/cda/ph/p/id/190">Process Control Instrumentation Technology</a>, Prentice Hall (1997) <a rel="nofollow" class="external text" href="https://web.archive.org/web/20080119225401/http://zone.ni.com/devzone/cda/ph/p/id/190">Archived</a> January 19, 2008, at the <a href="/wiki/Wayback_Machine" title="Wayback Machine">Wayback Machine</a></span> </li> </ol></div> <div class="mw-heading mw-heading2"><h2 id="References">References</h2><span class="mw-editsection"><span class="mw-editsection-bracket">[</span><a href="/w/index.php?title=Static_pressure&action=edit&section=6" title="Edit section: References"><span>edit</span></a><span class="mw-editsection-bracket">]</span></span></div> <p><b>Aircraft design and operation</b> </p> <ul><li><link rel="mw-deduplicated-inline-style" href="mw-data:TemplateStyles:r1238218222" /><cite id="CITEREFGracey1958" class="citation cs2">Gracey, William (1958), <a rel="nofollow" class="external text" href="https://ntrs.nasa.gov/api/citations/19930092348/downloads/19930092348.pdf"><i>Measurement of static pressure on aircraft</i></a> <span class="cs1-format">(PDF)</span>, Langley Research Center: NACA, TR-1364<span class="reference-accessdate">, retrieved <span class="nowrap">2023-04-07</span></span></cite><span title="ctx_ver=Z39.88-2004&rft_val_fmt=info%3Aofi%2Ffmt%3Akev%3Amtx%3Abook&rft.genre=book&rft.btitle=Measurement+of+static+pressure+on+aircraft&rft.place=Langley+Research+Center&rft.pub=NACA&rft.date=1958&rft.aulast=Gracey&rft.aufirst=William&rft_id=https%3A%2F%2Fntrs.nasa.gov%2Fapi%2Fcitations%2F19930092348%2Fdownloads%2F19930092348.pdf&rfr_id=info%3Asid%2Fen.wikipedia.org%3AStatic+pressure" class="Z3988"></span>.</li> <li><link rel="mw-deduplicated-inline-style" href="mw-data:TemplateStyles:r1238218222" /><cite id="CITEREFGracey1980" class="citation cs2">Gracey, William (1980), <a rel="nofollow" class="external text" href="https://ntrs.nasa.gov/api/citations/19800015804/downloads/19800015804.pdf"><i>Measurement of aircraft speed and altitude</i></a> <span class="cs1-format">(PDF)</span>, Langley Research Center: NASA, RP-1046<span class="reference-accessdate">, retrieved <span class="nowrap">2023-04-07</span></span></cite><span title="ctx_ver=Z39.88-2004&rft_val_fmt=info%3Aofi%2Ffmt%3Akev%3Amtx%3Abook&rft.genre=book&rft.btitle=Measurement+of+aircraft+speed+and+altitude&rft.place=Langley+Research+Center&rft.pub=NASA&rft.date=1980&rft.aulast=Gracey&rft.aufirst=William&rft_id=https%3A%2F%2Fntrs.nasa.gov%2Fapi%2Fcitations%2F19800015804%2Fdownloads%2F19800015804.pdf&rfr_id=info%3Asid%2Fen.wikipedia.org%3AStatic+pressure" class="Z3988"></span>.</li> <li><link rel="mw-deduplicated-inline-style" href="mw-data:TemplateStyles:r1238218222" /><cite id="CITEREFGracey1981" class="citation cs2">Gracey, William (1981), <i>Measurement of Aircraft Speed and Altitude</i>, New York: John Wiley & Sons, <a href="/wiki/ISBN_(identifier)" class="mw-redirect" title="ISBN (identifier)">ISBN</a> <a href="/wiki/Special:BookSources/978-0-471-08511-9" title="Special:BookSources/978-0-471-08511-9"><bdi>978-0-471-08511-9</bdi></a></cite><span title="ctx_ver=Z39.88-2004&rft_val_fmt=info%3Aofi%2Ffmt%3Akev%3Amtx%3Abook&rft.genre=book&rft.btitle=Measurement+of+Aircraft+Speed+and+Altitude&rft.place=New+York&rft.pub=John+Wiley+%26+Sons&rft.date=1981&rft.isbn=978-0-471-08511-9&rft.aulast=Gracey&rft.aufirst=William&rfr_id=info%3Asid%2Fen.wikipedia.org%3AStatic+pressure" class="Z3988"></span></li> <li>Kermode, A.C. (1972) <i>Mechanics of Flight</i>, Longman Group Limited, London <link rel="mw-deduplicated-inline-style" href="mw-data:TemplateStyles:r1238218222" /><a href="/wiki/ISBN_(identifier)" class="mw-redirect" title="ISBN (identifier)">ISBN</a> <a href="/wiki/Special:BookSources/0-582-23740-8" title="Special:BookSources/0-582-23740-8">0-582-23740-8</a></li> <li>Lombardo, D.A., <i>Aircraft Systems</i>, 2nd edition, McGraw-Hill (1999), New York <link rel="mw-deduplicated-inline-style" href="mw-data:TemplateStyles:r1238218222" /><a href="/wiki/ISBN_(identifier)" class="mw-redirect" title="ISBN (identifier)">ISBN</a> <a href="/wiki/Special:BookSources/0-07-038605-6" title="Special:BookSources/0-07-038605-6">0-07-038605-6</a></li></ul> <p><b>Fluid dynamics</b> </p> <ul><li><a href="/wiki/L._J._Clancy" class="mw-redirect" title="L. J. Clancy">L. J. Clancy</a> (1975), <i>Aerodynamics</i>, Pitman Publishing Limited, London <link rel="mw-deduplicated-inline-style" href="mw-data:TemplateStyles:r1238218222" /><a href="/wiki/ISBN_(identifier)" class="mw-redirect" title="ISBN (identifier)">ISBN</a> <a href="/wiki/Special:BookSources/0-273-01120-0" title="Special:BookSources/0-273-01120-0">0-273-01120-0</a></li> <li>Streeter, V.L. (1966), <i>Fluid Mechanics</i>, McGraw-Hill, New York</li></ul>    </div><noscript><img src="https://login.wikimedia.org/wiki/Special:CentralAutoLogin/start?useformat=desktop&type=1x1&usesul3=0" alt="" width="1" height="1" style="border: none; position: absolute;"></noscript> <div class="printfooter" data-nosnippet="">Retrieved from "<a dir="ltr" href="https://en.wikipedia.org/w/index.php?title=Static_pressure&oldid=1274548935">https://en.wikipedia.org/w/index.php?title=Static_pressure&oldid=1274548935</a>"</div></div> <div id="catlinks" class="catlinks" data-mw="interface"><div id="mw-normal-catlinks" class="mw-normal-catlinks"><a href="/wiki/Help:Category" title="Help:Category">Categories</a>: <ul><li><a href="/wiki/Category:Aerodynamics" title="Category:Aerodynamics">Aerodynamics</a></li><li><a href="/wiki/Category:Aircraft_instruments" title="Category:Aircraft instruments">Aircraft instruments</a></li><li><a href="/wiki/Category:Fluid_dynamics" title="Category:Fluid dynamics">Fluid dynamics</a></li></ul></div><div id="mw-hidden-catlinks" class="mw-hidden-catlinks mw-hidden-cats-hidden">Hidden categories: <ul><li><a href="/wiki/Category:Webarchive_template_wayback_links" title="Category:Webarchive template wayback links">Webarchive template wayback links</a></li><li><a href="/wiki/Category:Articles_with_short_description" title="Category:Articles with short description">Articles with short description</a></li><li><a href="/wiki/Category:Short_description_is_different_from_Wikidata" title="Category:Short description is different from Wikidata">Short description is different from Wikidata</a></li></ul></div></div> </div> </main> </div> <div class="mw-footer-container"> <footer id="footer" class="mw-footer" > <ul id="footer-info"> <li id="footer-info-lastmod"> This page was last edited on 7 February 2025, at 23:59<span class="anonymous-show"> (UTC)</span>.</li> <li id="footer-info-copyright">Text is available under the <a href="/wiki/Wikipedia:Text_of_the_Creative_Commons_Attribution-ShareAlike_4.0_International_License" title="Wikipedia:Text of the Creative Commons Attribution-ShareAlike 4.0 International License">Creative Commons Attribution-ShareAlike 4.0 License</a>; additional terms may apply. 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