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hypersonic wind tunnel wikipedia jump to content main menu main menu move to sidebar hide navigation main page contents current events random article about wikipedia contact us contribute help learn to edit community portal recent changes upload file special pages search search appearance donate create account log in personal tools donate create account log in contents move to sidebar hide top 1 technological problems 2 hot shot wind tunnel 3 hypersonic wind tunnel facility in india 4 marhy hypersonic wind tunnel facility in orléans france 5 see also 6 external links 7 references toggle the table of contents hypersonic wind tunnel 3 languages deutsch bahasa indonesia українська edit links article talk english read edit view history tools tools move to sidebar hide actions read edit view history general what links here related changes upload file permanent link page information cite this page get shortened url switch to legacy parser print export download as pdf printable version in other projects wikimedia commons wikidata item appearance move to sidebar hide from wikipedia the free encyclopedia type of wind tunnel this article needs more citations please help improve this article by adding citations to reliable sources unsourced material may be challenged and removed find sources hypersonic wind tunnel news newspapers books scholar jstor november 2021 learn how and when to remove this message nasa langley s hypersonic facilities complex 1969 a hypersonic wind tunnel is designed to generate a hypersonic flow field in the working section thus simulating the typical flow features of this flow regime including compression shocks and pronounced boundary layer effects entropy layer and viscous interaction zones and most importantly high total temperatures of the flow the speed of these tunnels vary from mach 5 to 15 the power requirement of a wind tunnel increases linearly with its cross section and flow density but cubically with the test velocity required hence installation of a continuous closed circuit wind tunnel remains a costly affair the first continuous mach 7 10 wind tunnel with 1x1 m test section was planned at kochel am see germany during ww ii 1 and finally put into operation as tunnel a in the late 1950s at aedc tullahoma tn usa for an installed power of 57 mw in view of these high facility demands also intermittently operated experimental facilities like blow down wind tunnels are designed and installed to simulate the hypersonic flow a hypersonic wind tunnel comprises in flow direction the main components heater cooler arrangements dryer convergent divergent nozzle test section second throat and diffuser a blow down wind tunnel has a low vacuum reservoir at the back end while a continuously operated closed circuit wind tunnel has a high power compressor installation instead since the temperature drops with the expanding flow the air inside the test section has the chance of becoming liquefied for that reason preheating is particularly critical the nozzle may require cooling technological problems edit there are several technological problems in designing and constructing a hyper velocity wind tunnel supply of high temperatures and pressures for times long enough to perform a measurement reproduction of equilibrium conditions structural damage produced by overheating fast instrumentation power requirements to run the tunnel simulations of a flow at 5 5 km s 45 km altitude would require tunnel temperatures of as much as 9000 k and a pressure of 3 gpa hot shot wind tunnel edit one form of hwt is known as a gun tunnel or hot shot tunnel up to m 27 which can be used for analysis of flows past ballistic missiles space vehicles in atmospheric entry and plasma physics or heat transfer at high temperatures it runs intermittently but has a very low running time less than a second the method of operation is based on a high temperature and pressurized gas air or nitrogen produced in an arc chamber and a near vacuum in the remaining part of the tunnel the arc chamber can reach several mpa while pressures in the vacuum chamber can be as low as 0 1 pa this means that the pressure ratios of these tunnels are in the order of 10 million also the temperatures of the hot gas are up to 5000 k the arc chamber is mounted in the gun barrel the high pressure gas is separated from the vacuum by a diaphragm prior to a test run commencing a membrane separates the compressed air from the gun barrel breech a rifle or similar is used to rupture the membrane compressed air rushes into the breech of the gun barrel forcing a small projectile to accelerate rapidly down the barrel although the projectile is prevented from leaving the barrel the air in front of the projectile emerges at hypersonic velocity into the working section naturally the duration of the test is extremely brief so high speed instrumentation is required to get any meaningful data hypersonic wind tunnel facility in india edit the indian space research organization isro commissioned three major facilities namely a hypersonic wind tunnel a shock tunnel and a plasma tunnel at vikram sarabhai space center as part of its continuous and concerted efforts to minimize cost of access into space this integrated facility was named as satish dhawan wind tunnel complex as a tribute to prof satish dhawan who has made very significant contributions in the field of wind tunnels and aerodynamics isro chairman a s kiran kumar said commissioning of such facilities would provide adequate data for design and development of current and future space transportation systems in india 2 defence research and development organisation drdo commissioned an advanced hypersonic wind tunnel hwt test facility at dr apj abdul kalam missile complex on 20 december 2020 as part of facility development programme for hypersonic technology demonstrator vehicle project 3 marhy hypersonic wind tunnel facility in orléans france edit photo of the wind tunnel marhy the marhy hypersonic low density wind tunnel located at the icare 4 laboratory in orléans france is a research facility used extensively for fundamental and applied research of fluid dynamic phenomena in rarefied compressible flows applied to space research its name is an acronym for m ach a daptable r arefied hy personic and the wind tunnel is recorded under this name under the european portal meril see also edit wind tunnel low speed wind tunnel high speed wind tunnel supersonic wind tunnel ludwieg tube shock tube hypersonic nasa marhy wind tunnel external links edit hot shot wind tunnel at the von karman institute for fluid dynamics langley hot shot wind tunnel description and calibration at the langley research center meril the european facilities platform references edit eckardt dietrich the 1x1 m hypersonic wind tunnel kochel tullahoma 1940 1960 ceas space journal march 2015 vol 7 issue 1 pp 23 36 satish dhawan wind tunnel complex commissioned at vssc isro www isro gov in archived from the original on 2021 01 13 retrieved 2020 12 21 hypersonic wind tunnel test facility inaugurated at drdo the hindu 2020 12 20 issn 0971 751x retrieved 2021 03 18 icare laboratory cnrs orléans retrieved from https en wikipedia org w index php title hypersonic_wind_tunnel oldid 1334046877 categories fluid dynamics aerodynamics wind tunnels hidden categories articles with short description short description matches wikidata articles needing additional references from november 2021 all articles needing additional references this page was last edited on 21 january 2026 at 05 44 utc page was rendered with parsoid text is available under the creative commons attribution sharealike 4 0 license additional terms may apply by using this site you agree to the terms of use and privacy policy wikipedia is a registered trademark of the wikimedia foundation inc a non profit organization privacy policy about wikipedia disclaimers contact wikipedia legal safety contacts code of conduct developers 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