First variation - Revision history

129.123.21.97 at 00:36, 11 December 2014

2014-12-11T00:36:38Z

← Older revision		Revision as of 02:36, 11 December 2014
Line 1:		Line 1:
	~~{{Unreferenced\|date=February 2007}}~~[~~[Image~~:~~Windtunnel2~~.~~JPG\|thumb\|450px\|Eiffel wind tunnel with an open test sectionl]]~~		Nice to [http://www.1a-pornotube.com/blog/29575 1a-pornotube.com] meet you, I am Marvella Shryock. Years home std test in the past we moved to North Dakota. [http://www.herpes-Coldsores.com/celebrities-with-herpes.html Body developing] is what my family and I appreciate. Since she was eighteen she's home std test kit been working home std test kit as a [http://www.emedicinehealth.com/genital_herpes/article_em.htm meter reader] but she's always wanted her own company.<br><br>Feel free to visit [http://citymama.com.ua/profile_info.php?ID=38588 home std test kit] my homepage [https://Alphacomms.Zendesk.com/entries/53455304-Curing-Your-Candida-Albicans-How-To-Make-It-Happen-Easily https://Alphacomms.Zendesk.com/entries/53455304-Curing-Your-Candida-Albicans-How-To-Make-It-Happen-Easily]
	~~==Subsonic tunnel==~~
	~~Low~~-~~speed wind tunnels are used for operations at very low [[mach number]], with speeds in the test section up to 480 km~~/~~h (~ 134 [[Metre per second\|m~~/~~s]], [[Mach number\|M]] = 0.4)(Barlow, Rae, Pope; 1999). They may be of open~~-~~return type ([[:Image:Windtunnel1~~.~~JPG\|see figure below]~~]), ~~or closed-return flow ([[:Image:Windtunnel3~~.~~JPG\|see figure below]]) with air~~ moved ~~by a propulsion system usually consisting of large axial fans that increase the dynamic pressure~~ to ~~overcome the [[viscosity\|viscous]] losses~~.

	~~===Open wind tunnel===~~

	[~~[Image~~:~~Windtunnel1~~-en.~~svg\|450px\|thumb\|Schematic of an open wind tunnel~~ with ~~a closed test section~~]]

	~~The working principle~~ is ~~based on the continuity~~ and ~~[[Bernoulli~~'s ~~equation]]:~~

	~~The continuity equation is given by~~:

	~~<math>A V = constant \Rightarrow \frac{dA}{A}=-\frac{dV}{V} <~~/~~math>~~

	~~The Bernoulli equation states:~~

	~~<math>P_{total}=P_{static} + P_{dynamic} = P_s + \frac{1}{2}\rho V^2<~~/~~math>~~

	~~Putting Bernoulli into the continuity equation gives:~~

	~~<math>V_m^2=2 \frac{C^2}{C^2-1} \frac{P_{settl}-p_m}{\rho} \approx 2 \frac{\Delta p}{\rho}<~~/~~math>~~

	~~The contraction ratio of a windtunnel can now be calculated by:~~
	~~<math>C = \frac{A_{settl}}{A_m}<~~/~~math>~~

	~~===Closed wind tunnel===~~

	~~[[Image:Windtunnel3-en~~.~~svg\|450px\|thumb\|Schematic of a closed (return-flow) wind tunnel~~]]

	~~In a return-flow wind tunnel the return duct must be properly designed to reduce the pressure losses and to ensure smooth flow in the test section~~.
	~~The compressible flow regime:~~
	~~Again with the continuity law, but now for isentropic flow gives:~~

	<~~math~~>~~- \frac{d \rho}{\rho} = -\frac{1}{a^2} \frac{dp}{\rho} = -\frac{1}{a^2} \frac{-\rho V d V}{\rho} = \frac{V}{a^2}d V~~<~~/math~~>

	~~The 1-D area-velocity is known as~~:

	~~<math>\frac{d A}{A} = (M^2 - 1) \frac{d V}{V}<~~/~~math>~~

	~~The minimal area A where M=1, also known as the ''sonic throat'' area is than given for a perfect gas:~~

	~~<math> \left( \frac{A}{A_{throat}} \right)^2 = \frac{1}{M^2} \left( \frac{2}{\gamma +1} \left( 1 + \frac{\gamma -1}{2} M^2 \right) \right)^{\frac{\gamma +1}{\gamma-1}}<~~/~~math>~~

	~~==Transonic tunnel==~~

	High subsonic wind tunnels (0.4 < M < 0.75) and transonic wind tunnels (0.75 < M < 1.2) are designed on the same principles as the subsonic wind tunnels. The highest speed is reached in the test section. The Mach number is approximately 1 with combined subsonic and supersonic flow regions. Testing at transonic speeds presents additional problems, mainly due to the reflection of the shock waves from the walls of the test section (see figure below or enlarge the thumb picture at the right). Therefore, perforated or slotted walls are required to reduce shock reflection from the walls. ~~Since important viscous or inviscid interactions occur (such as shock waves or boundary layer interaction) both Mach and Reynolds number are important and must be properly simulated~~.
	~~Large-scale facilities and~~/~~or pressurized or cryogenic wind tunnels are used.~~

	~~[[Image:Tunnelreflection-en~~.~~svg\|500px\|Experimental rhombus variation with the mach number]]~~

	=~~= de Laval nozzle ==~~
	~~: ''Main article [[de Laval nozzle~~]~~].''~~

	~~With a sonic throat, the flow can be accelerated or slowed down. This follows from the 1D area–velocity equation. If an acceleration to supersonic flow is required, a convergent-divergent~~ [~~[nozzle]] is required.~~
	~~Otherwise~~:
	*Subsonic (M < 1) then <math>\frac{d A}{d x}< 0\Rightarrow </~~math> converging~~
	*Sonic throat (M = 1) where <math>\frac{d A}{d x} = 0</~~math>~~
	*Supersonic (M >1 ) then <math>\frac{d A}{d x}>0 \Rightarrow </~~math> diverging~~

	~~Conclusion: The Mach number is controlled by the expansion ratio <math>\frac{A}{A_{throat}}<~~/~~math>~~

	~~== See also ==~~
	* [http://~~www~~.~~niar~~.~~wichita.edu~~/~~researchlabs~~/~~ad_overview.asp 7x10 Foot Low Speed Wind Tunnel]~~
	* [[Wind tunnel]]
	* [[Supersonic wind tunnel]]
	* [[Hypersonic wind tunnel]]
	* [[Gustave Eiffel]]
	* [[National Aerospace Laboratory]], Netherlands

	~~[[Category:Fluid dynamics]]~~
	~~[[Category:Aerodynamics]]~~
	~~[[Category:Wind tunnels]~~]

en>Nicoguaro: Adding "See also"

2013-11-22T22:29:12Z

Adding "See also"

← Older revision		Revision as of 00:29, 23 November 2013
Line 1:		Line 1:
	~~Hi there~~. ~~Let me begin by introducing~~ the ~~author~~, ~~her title is Sophia~~. ~~What me and my family love is to climb but I'm thinking on beginning~~ [~~http~~:~~//breenq~~.~~com/index~~.~~php?do~~=~~/profile~~-~~1144/info/ real psychics~~] ~~something new. Distributing production~~ is ~~how he tends to make a residing. Some time online psychic reading (~~[~~http~~://~~www.prayerarmor.com~~/~~uncategorized~~/~~dont~~-~~know~~-~~which~~-~~kind~~-of-~~hobby~~-to-~~take~~-up-~~read~~-the-~~following~~-~~tips~~/ ~~www~~.~~prayerarmor~~.~~com]~~) in the ~~past he selected~~ to ~~live in North Carolina~~ and ~~he doesn~~'~~t plan on altering it~~.<br><br>~~Feel free to visit my web page; psychic phone - [http:~~//~~www.010-5260-5333.com~~/~~index.php?document_srl~~=~~1880&mid~~=~~board_ALMP66~~ http://www.~~010-5260-5333~~.~~com~~/~~index~~.~~php?document_srl=1880&mid=board_ALMP66~~] -		{{Unreferenced\|date=February 2007}}[[Image:Windtunnel2.JPG\|thumb\|450px\|Eiffel wind tunnel with an open test sectionl]]
			==Subsonic tunnel==
			Low-speed wind tunnels are used for operations at very low [[mach number]], with speeds in the test section up to 480 km/h (~ 134 [[Metre per second\|m/s]], [[Mach number\|M]] = 0.4)(Barlow, Rae, Pope; 1999). They may be of open-return type ([[:Image:Windtunnel1.JPG\|see figure below]]), or closed-return flow ([[:Image:Windtunnel3.JPG\|see figure below]]) with air moved by a propulsion system usually consisting of large axial fans that increase the dynamic pressure to overcome the [[viscosity\|viscous]] losses.

			===Open wind tunnel===

			[[Image:Windtunnel1-en.svg\|450px\|thumb\|Schematic of an open wind tunnel with a closed test section]]

			The working principle is based on the continuity and [[Bernoulli's equation]]:

			The continuity equation is given by:

			<math>A V = constant \Rightarrow \frac{dA}{A}=-\frac{dV}{V} </math>

			The Bernoulli equation states:

			<math>P_{total}=P_{static} + P_{dynamic} = P_s + \frac{1}{2}\rho V^2</math>

			Putting Bernoulli into the continuity equation gives:

			<math>V_m^2=2 \frac{C^2}{C^2-1} \frac{P_{settl}-p_m}{\rho} \approx 2 \frac{\Delta p}{\rho}</math>

			The contraction ratio of a windtunnel can now be calculated by:
			<math>C = \frac{A_{settl}}{A_m}</math>

			===Closed wind tunnel===

			[[Image:Windtunnel3-en.svg\|450px\|thumb\|Schematic of a closed (return-flow) wind tunnel]]

			In a return-flow wind tunnel the return duct must be properly designed to reduce the pressure losses and to ensure smooth flow in the test section.
			The compressible flow regime:
			Again with the continuity law, but now for isentropic flow gives:

			<math>- \frac{d \rho}{\rho} = -\frac{1}{a^2} \frac{dp}{\rho} = -\frac{1}{a^2} \frac{-\rho V d V}{\rho} = \frac{V}{a^2}d V</math>

			The 1-D area-velocity is known as:

			<math>\frac{d A}{A} = (M^2 - 1) \frac{d V}{V}</math>

			The minimal area A where M=1, also known as the ''sonic throat'' area is than given for a perfect gas:

			<math> \left( \frac{A}{A_{throat}} \right)^2 = \frac{1}{M^2} \left( \frac{2}{\gamma +1} \left( 1 + \frac{\gamma -1}{2} M^2 \right) \right)^{\frac{\gamma +1}{\gamma-1}}</math>

			==Transonic tunnel==

			High subsonic wind tunnels (0.4 < M < 0.75) and transonic wind tunnels (0.75 < M < 1.2) are designed on the same principles as the subsonic wind tunnels. The highest speed is reached in the test section. The Mach number is approximately 1 with combined subsonic and supersonic flow regions. Testing at transonic speeds presents additional problems, mainly due to the reflection of the shock waves from the walls of the test section (see figure below or enlarge the thumb picture at the right). Therefore, perforated or slotted walls are required to reduce shock reflection from the walls. Since important viscous or inviscid interactions occur (such as shock waves or boundary layer interaction) both Mach and Reynolds number are important and must be properly simulated.
			Large-scale facilities and/or pressurized or cryogenic wind tunnels are used.

			[[Image:Tunnelreflection-en.svg\|500px\|Experimental rhombus variation with the mach number]]

			== de Laval nozzle ==
			: ''Main article [[de Laval nozzle]].''

			With a sonic throat, the flow can be accelerated or slowed down. This follows from the 1D area–velocity equation. If an acceleration to supersonic flow is required, a convergent-divergent [[nozzle]] is required.
			Otherwise:
			*Subsonic (M < 1) then <math>\frac{d A}{d x}< 0\Rightarrow </math> converging
			*Sonic throat (M = 1) where <math>\frac{d A}{d x} = 0</math>
			*Supersonic (M >1 ) then <math>\frac{d A}{d x}>0 \Rightarrow </math> diverging

			Conclusion: The Mach number is controlled by the expansion ratio <math>\frac{A}{A_{throat}}</math>

			== See also ==
			* [http://www.niar.wichita.edu/researchlabs/ad_overview.asp 7x10 Foot Low Speed Wind Tunnel]
			* [[Wind tunnel]]
			* [[Supersonic wind tunnel]]
			* [[Hypersonic wind tunnel]]
			* [[Gustave Eiffel]]
			* [[National Aerospace Laboratory]], Netherlands

			[[Category:Fluid dynamics]]
			[[Category:Aerodynamics]]
			[[Category:Wind tunnels]]

en>Dark Silver Crow: Stale merge proposals x2 - one with a concensus of no merge, one with a missing discussion

2012-05-08T19:12:53Z

Stale merge proposals x2 - one with a concensus of no merge, one with a missing discussion

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