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Tangential Gas Injection Into a Supersonic Stream

[+] Author Affiliations
Eduard B. Vasilevskiy, Ivan V. Ezhov, Andrey V. Novikov

Central Aerohydrodynamic Institute (TsAGI), Zhukovsky, Moscow Region, Russia

Paper No. IHTC14-22922, pp. 701-710; 10 pages
  • 2010 14th International Heat Transfer Conference
  • 2010 14th International Heat Transfer Conference, Volume 2
  • Washington, DC, USA, August 8–13, 2010
  • Conference Sponsors: Heat Transfer Division
  • ISBN: 978-0-7918-4937-8 | eISBN: 978-0-7918-3879-2
  • Copyright © 2010 by ASME


An experimental and numerical study of a tangential gas injection effect on a flow pattern and heat flux was carried out. The cooling gas (air) was injected in the flow (air) through the tangential axis-symmetric slot on the spherically blunted cylinder streamlined longitudinally. Experiments were conducted in TsAGI shock wind tunnel at free-stream Mach number M∞ = 6, Reynolds number Re∞, Rw = 0.76×106 (calculated for free-stream parameters and bluntness radius Rw = 37.5 mm), cylinder angle of attack α = 0[[ellipsis]]30°, slot width h* = hk /Rw = 0–0.021, free-stream stagnation temperature T0 = 710 K, pressure behind the normal shock ps = 0.5 bar. The mass rate of the injected gas G* = gj /πρ∞ u∞ rw 2 = 0[[ellipsis]]0.12. It is shown, that maximum of the heat flux toward the sphere surface could be sufficiently decreased. For example, for coolant mass rate G* = 0.03 and angle of attack α = 0 the heat flux maximum is reduced by factor of two.

Copyright © 2010 by ASME



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