The §ow pattern and the heat §ux to a body surface at a tangential gas injecting have been investigated. The cooling air was injected to a §ow through the tangential axisymmetric slot on the spherically blunted cylinder. The experiments were conducted at M ∞ = 6, Re ∞,Rw = 0.76 · 10 6 , angle of attack α = 0 • €30 • , and the slot width h k /R w = 0€ 0.021. The mass rate of the injecting gas was G * = g j /(πρ ∞ u 2 ∞w) = 0€ 0.16. It has been shown that maximum of the heat §ux toward the sphere surface can be su©ciently decreased. Numerical investigations have been carried out using the solution of the Navier€Stokes equations for axisymmetric two-dimensional (2D) viscous compressible unsteady §ows at α = 0.

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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…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∞rw2 = 0…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.

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