Case analysis - Revision history

122.172.205.204: /* Connections with logical principles */

2014-10-28T10:06:54Z

Connections with logical principles

← Older revision		Revision as of 12:06, 28 October 2014
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	[[File:Engineers_Check_Body_Revolution_Model_-_GPN-2000-001473.jpg\|thumb\|Engineers check an aircraft model before a test run in the Supersonic Wind Tunnel at [[Glenn Research Center\|Lewis Flight Propulsion Laboratory]].]]		The author's name is Andera and she thinks it seems quite great. The favorite pastime for him and his children is to perform lacross and he would by no means give it up. For years she's been working as a journey agent. Alaska is the only place I've been residing in but now I'm considering other options.<br><br>Feel free to visit my webpage :: clairvoyants ([http://netwk.hannam.ac.kr/xe/data_2/85669 netwk.hannam.ac.kr])
	~~[[File:Pitot-Mach4-PSUSWT.jpg\|thumb\|[[Schlieren photography]]~~ is ~~often used to capture images of gas flow~~ and ~~shock waves in supersonic wind tunnels~~. ~~Here, Mach 4 flow over a pitot probe is observed by schlieren optics in the [[Penn State]] Supersonic Wind Tunnel.~~ The ~~flow direction~~ is ~~left-~~to~~-right~~.]]

	A '~~''supersonic wind tunnel''' is~~ a ~~[[wind tunnel]] that produces [[supersonic]] speeds (1~~.~~2<[[Mach number\|M]]<5)~~
	~~The Mach number and flow are determined by the [[nozzle]] geometry. The [[Reynolds number]]~~ is ~~varied by changing~~ the ~~density level (pressure~~ in the settling chamber). Therefore a high pressure ratio is required (for a supersonic regime at M=4, this ratio is of the order of 10). Apart from that, condensation of moisture or even gas liquefaction can occur if the static temperature becomes cold enough. This means that a supersonic wind tunnel usually needs a drying or a pre-heating facility.
	~~A supersonic wind tunnel has a large power demand, so that most are designed for intermittent instead of continuous operation.~~

	~~==Restrictions for supersonic tunnel operation==~~
	~~===Minimum required pressure ratio===~~
	~~Optimistic estimate:~~
	~~Pressure ratio~~ <~~math~~>~~\leq~~<~~/math~~> ~~the total pressure ratio over normal shock at M in test section~~:

	~~<math>\frac{P_t}{P_{amb}} \leq\left(\frac{P_{t_1}}{P_{t_2}}\right)_{M_1=M_m}</math>~~

	~~Examples:~~

	~~===Temperature effects: condensation===~~
	~~Temperature in the test section~~:

	~~<math>\frac{T_m}{T_t}=\left~~(~~1+\frac{\gamma-1}{2}M_m^2\right)^{-1}</math>~~

	~~with <math>T_t</math> = 330K~~: ~~<math>T_m<~~/~~math> = 70K at <math>M_m<~~/~~math> = 4~~

	~~The velocity range is limited by reservoir temperature~~

	~~==Power requirements==~~
	~~The power required to run a supersonic wind tunnel is enormous, of the order of 50 MW per square meter of test section cross-sectional area~~. ~~For this reason most wind tunnels operate intermittently using energy stored in high-pressure tanks~~. ~~These wind tunnels are also called intermittent supersonic blowdown wind tunnels (of which a schematic preview is given below)~~. Another way of achieving the huge power output is with the use of a vacuum storage tank. <!-- What are high pressure tanks or vacuum storage tanks? --> These tunnels are called indraft supersonic wind tunnels, and are seldom used because they are restricted to low Reynolds numbers. Some large countries have built major supersonic tunnels that run continuously; one is shown in the photo.
	~~Other problems operating a supersonic wind tunnel include:~~
	*starting and [[unstart]] of the test section (related to maintaining at least a minimum pressure ratio)
	*adequate supply of dry air
	*wall interference effects due to shock wave reflection and (sometimes) blockage
	*high-quality instruments capable of rapid measurements due to short run times in intermittent tunnels
	~~[[File:Supersonic-en.svg\|400px]]~~

	~~Tunnels such as a [[Ludwieg tube]] have short test times (usually less than one second), relatively high [[Reynolds number]], and low power requirements.~~

	~~==Further reading==~~
	* {{cite book \| author=Pope, A.; Goin, K.\| title=High-speed Wind Tunnel Testing \| publisher=Krieger \|year=1978 \| isbn=0-88275-727-X}}

	~~==See also==~~
	* [[Wind tunnel]]
	* [[Subsonic and transonic wind tunnel#Subsonic_tunnel\|Low speed wind tunnel]]
	* [[Subsonic and transonic wind tunnel#Transonic_tunnel\|High speed wind tunnel]]
	* [[Hypersonic wind tunnel]]
	* [[Ludwieg tube]]
	* [[Shock tube]]

	~~== External links ==~~
	* [http://~~www~~.~~youtube~~.~~com/watch?v=iNBZBChS2YI Supersonic wind tunnel test demonstration (Mach 2~~.~~5) with flat plate and wedge creating an oblique shock(Video~~)]

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

en>McGeddon: "what remains" is the unlikely thing, not "the effect"!

2013-10-21T18:09:02Z

"what remains" is the unlikely thing, not "the effect"!

← Older revision		Revision as of 20:09, 21 October 2013
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	~~Alyson Meagher is~~ the ~~title~~ [~~http~~:~~//koreanyelp~~.~~com/index~~.~~php?document_srl=1798&mid=SchoolNews free psychic~~] ~~her mothers and fathers gave her but she doesn't like when individuals use her full name~~. ~~My working day occupation~~ is ~~an invoicing officer but I~~'~~ve currently applied for another~~ 1. As a ~~woman what she truly likes~~ is ~~style and she's been doing it~~ for ~~fairly~~ a ~~whilst~~. ~~Mississippi is where her home is but her psychic chat online~~ (~~[http~~://~~www~~.~~chk~~.~~woobi~~.co.~~kr/xe/~~?~~document_srl=346069 www~~.~~chk~~.~~woobi.co.kr~~]) ~~spouse desires them~~ to ~~transfer~~.~~<br><br>Check out my webpage: love psychic~~ ([http://~~hknews~~.~~classicmall~~.com.~~hk/groups/some-simple-tips-for-personal-development-progress/ visit our website~~])		[[File:Engineers_Check_Body_Revolution_Model_-_GPN-2000-001473.jpg\|thumb\|Engineers check an aircraft model before a test run in the Supersonic Wind Tunnel at [[Glenn Research Center\|Lewis Flight Propulsion Laboratory]].]]
			[[File:Pitot-Mach4-PSUSWT.jpg\|thumb\|[[Schlieren photography]] is often used to capture images of gas flow and shock waves in supersonic wind tunnels. Here, Mach 4 flow over a pitot probe is observed by schlieren optics in the [[Penn State]] Supersonic Wind Tunnel. The flow direction is left-to-right.]]

			A '''supersonic wind tunnel''' is a [[wind tunnel]] that produces [[supersonic]] speeds (1.2<[[Mach number\|M]]<5)
			The Mach number and flow are determined by the [[nozzle]] geometry. The [[Reynolds number]] is varied by changing the density level (pressure in the settling chamber). Therefore a high pressure ratio is required (for a supersonic regime at M=4, this ratio is of the order of 10). Apart from that, condensation of moisture or even gas liquefaction can occur if the static temperature becomes cold enough. This means that a supersonic wind tunnel usually needs a drying or a pre-heating facility.
			A supersonic wind tunnel has a large power demand, so that most are designed for intermittent instead of continuous operation.

			==Restrictions for supersonic tunnel operation==
			===Minimum required pressure ratio===
			Optimistic estimate:
			Pressure ratio <math>\leq</math> the total pressure ratio over normal shock at M in test section:

			<math>\frac{P_t}{P_{amb}} \leq\left(\frac{P_{t_1}}{P_{t_2}}\right)_{M_1=M_m}</math>

			Examples:

			===Temperature effects: condensation===
			Temperature in the test section:

			<math>\frac{T_m}{T_t}=\left(1+\frac{\gamma-1}{2}M_m^2\right)^{-1}</math>

			with <math>T_t</math> = 330K: <math>T_m</math> = 70K at <math>M_m</math> = 4

			The velocity range is limited by reservoir temperature

			==Power requirements==
			The power required to run a supersonic wind tunnel is enormous, of the order of 50 MW per square meter of test section cross-sectional area. For this reason most wind tunnels operate intermittently using energy stored in high-pressure tanks. These wind tunnels are also called intermittent supersonic blowdown wind tunnels (of which a schematic preview is given below). Another way of achieving the huge power output is with the use of a vacuum storage tank. <!-- What are high pressure tanks or vacuum storage tanks? --> These tunnels are called indraft supersonic wind tunnels, and are seldom used because they are restricted to low Reynolds numbers. Some large countries have built major supersonic tunnels that run continuously; one is shown in the photo.
			Other problems operating a supersonic wind tunnel include:
			*starting and [[unstart]] of the test section (related to maintaining at least a minimum pressure ratio)
			*adequate supply of dry air
			*wall interference effects due to shock wave reflection and (sometimes) blockage
			*high-quality instruments capable of rapid measurements due to short run times in intermittent tunnels
			[[File:Supersonic-en.svg\|400px]]

			Tunnels such as a [[Ludwieg tube]] have short test times (usually less than one second), relatively high [[Reynolds number]], and low power requirements.

			==Further reading==
			* {{cite book \| author=Pope, A.; Goin, K.\| title=High-speed Wind Tunnel Testing \| publisher=Krieger \|year=1978 \| isbn=0-88275-727-X}}

			==See also==
			* [[Wind tunnel]]
			* [[Subsonic and transonic wind tunnel#Subsonic_tunnel\|Low speed wind tunnel]]
			* [[Subsonic and transonic wind tunnel#Transonic_tunnel\|High speed wind tunnel]]
			* [[Hypersonic wind tunnel]]
			* [[Ludwieg tube]]
			* [[Shock tube]]

			== External links ==
			* [http://www.youtube.com/watch?v=iNBZBChS2YI Supersonic wind tunnel test demonstration (Mach 2.5) with flat plate and wedge creating an oblique shock(Video)]

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

en>Gregbard: fx

2012-03-05T22:47:22Z

New page

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