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2014-08-18T13:32:06Z

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	~~In compressible fluid dynamics~~, ''~~'impact pressure''' (dynamic pressure) is the difference between total pressure (also known~~ as ~~[[pitot tube\|pitot pressure]] or [[stagnation pressure]]) and [[static pressure]]~~.<~~ref~~>[http://~~www~~.~~answers~~.com/~~topic~~/~~impact~~-~~pressure DoD and NATO definition of impact pressure] Retrieved on 2008~~-10-~~01<~~/~~ref> <ref>~~[http://~~www~~.~~thefreedictionary~~.com/~~impact+pressure The Free Dictionary] Retrieved~~ on ~~2008~~-10-~~01<~~/~~ref>~~ In ~~[[aerodynamics~~]~~] notation, this quantity is denoted as '''~~<~~math~~>~~q_c~~<~~/math~~>~~'''~~ or ~~'''~~<~~math~~>~~Q_c~~<~~/math~~>~~'''~~.		It's bеst to keeр away from meals that include trans body fat, that are present in several refined meals. Trans fats consiɗerably imρrove your risk for coronary diѕeasе and аlso other medical issuеs. Trans fats lead to a highеr-level of bad choleѕterοl levels and minimize great cholesterol.<br><br>Consume a lot more salmon. 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	~~When input to an airspeed indicator, impact pressure is used to provide a [[calibrated airspeed]] reading. An [[air data computer]]~~ with ~~inputs of pitot and static pressures is able to provide a [[Mach number]] and, if static temperature is known, [[true airspeed]]~~.

	~~Some authors in the field~~ of ~~compressible flows use the term ''dynamic pressure''~~ or ~~''compressible dynamic pressure'' instead of ''impact pressure''~~.~~<ref name=LJC3~~.~~12>Clancy, L~~.J.~~, ''Aerodynamics'', Section 3.12 and 3.13~~<~~/ref~~><~~ref~~>"the ~~dynamic pressure is equal~~ to ~~''half rho vee squared''~~ only ~~in incompressible flow~~."<br />~~Houghton, E.L. and Carpenter, P.W. (1993), ''Aerodynamics for Engineering Students'', Section 2.3.1~~<~~/ref~~>

	~~==Isentropic flow==~~
	~~In [[isentropic flow]] the ratio of [[stagnation pressure\|total pressure]]~~ to [~~[static pressure]] is given by~~:~~<ref name=LJC3~~.12/>

	~~<math>\frac{P_t}{P}~~ = ~~\left(1~~+ ~~\frac{\gamma~~ -~~1}{2} M^2 \right)^\tfrac{\gamma}{\gamma~~ - 1}<~~/math~~>

	~~where:~~

	<~~math~~>~~P_t~~<~~/math~~> ~~is total pressure~~

	<~~math~~>P</~~math> is static pressure~~

	~~<math>\gamma\;<~~/~~math> is the [[Heat capacity ratio\|ratio of specific heats]]<br~~ />

	~~<math>M\;<~~/~~math> is the freestream Mach number~~


	~~Taking <math>\gamma\;<~~/~~math>~~ to ~~be 1~~.4, and ~~since~~ <~~math~~>~~\;P_t=P+q_c~~<~~/math~~>


	~~<math>\;q_c = P\left[\left(1+0~~.~~2 M^2 \right)^\tfrac{7}{2}-1\right]</math>~~


	~~Expressing the incompressible [[dynamic pressure]]~~ as <~~math~~>~~\;\tfrac{1}{2}\gamma PM^2~~<~~/math~~> ~~and expanding by the~~ [~~[binomial series]] gives~~:


	~~<math>\;q_c=q \left(1 + \frac{M^2}{4} + \frac{M^4}{40} + \frac{M^6}{1600}~~ ..~~. \right)\;<~~/~~math>~~

	~~where:~~

	~~<math>\;~~q~~</math> is dynamic pressure~~

	==~~References~~==
	~~{{reflist}}~~

	~~== See also ==~~
	* [[Dynamic pressure]]
	* [[Pitot-~~static system]]~~
	* [~~[Pressure]]~~
	* [[Static pressure]]

	~~[[Category~~:~~Fluid dynamics]~~]

98.232.93.10: In 2nd sentence, changes Lee. E. Atlas to Les E. Atlas, correcting both the error in the 1st name of Les E. Atlas and the punctuation error.

2011-12-25T00:15:16Z

In 2nd sentence, changes Lee. E. Atlas to Les E. Atlas, correcting both the error in the 1st name of Les E. Atlas and the punctuation error.

New page

In compressible fluid dynamics, '''impact pressure''' (dynamic pressure) is the difference between total pressure (also known as [[pitot tube|pitot pressure]] or [[stagnation pressure]]) and [[static pressure]].<ref>[http://www.answers.com/topic/impact-pressure DoD and NATO definition of impact pressure] Retrieved on 2008-10-01</ref> <ref>[http://www.thefreedictionary.com/impact+pressure The Free Dictionary] Retrieved on 2008-10-01</ref> In [[aerodynamics]] notation, this quantity is denoted as '''<math>q_c</math>''' or '''<math>Q_c</math>'''.

When input to an airspeed indicator, impact pressure is used to provide a [[calibrated airspeed]] reading. An [[air data computer]] with inputs of pitot and static pressures is able to provide a [[Mach number]] and, if static temperature is known, [[true airspeed]].

Some authors in the field of compressible flows use the term ''dynamic pressure'' or ''compressible dynamic pressure'' instead of ''impact pressure''.<ref name=LJC3.12>Clancy, L.J., ''Aerodynamics'', Section 3.12 and 3.13</ref><ref>"the dynamic pressure is equal to ''half rho vee squared'' only in incompressible flow."<br />Houghton, E.L. and Carpenter, P.W. (1993), ''Aerodynamics for Engineering Students'', Section 2.3.1</ref>

==Isentropic flow==
In [[isentropic flow]] the ratio of [[stagnation pressure|total pressure]] to [[static pressure]] is given by:<ref name=LJC3.12/>

<math>\frac{P_t}{P} = \left(1+ \frac{\gamma -1}{2} M^2 \right)^\tfrac{\gamma}{\gamma - 1}</math>

where:

<math>P_t</math> is total pressure

<math>P</math> is static pressure

<math>\gamma\;</math> is the [[Heat capacity ratio|ratio of specific heats]]<br />

<math>M\;</math> is the freestream Mach number

Taking <math>\gamma\;</math> to be 1.4, and since <math>\;P_t=P+q_c</math>

<math>\;q_c = P\left[\left(1+0.2 M^2 \right)^\tfrac{7}{2}-1\right]</math>

Expressing the incompressible [[dynamic pressure]] as <math>\;\tfrac{1}{2}\gamma PM^2</math> and expanding by the [[binomial series]] gives:

<math>\;q_c=q \left(1 + \frac{M^2}{4} + \frac{M^4}{40} + \frac{M^6}{1600} ... \right)\;</math>

where:

<math>\;q</math> is dynamic pressure

==References==
{{reflist}}

== See also ==
* [[Dynamic pressure]]
* [[Pitot-static system]]
* [[Pressure]]
* [[Static pressure]]

[[Category:Fluid dynamics]]

Cone-shape distribution function - Revision history

132.3.33.79 at 13:32, 18 August 2014

98.232.93.10: In 2nd sentence, changes Lee. E. Atlas to Les E. Atlas, correcting both the error in the 1st name of Les E. Atlas and the punctuation error.