Abstract
A calculation and experimental study was conducted with the flow, heat flux, and pressure distributions over the front and side surfaces of a blunt cone in a nonequilibrium high-enthalpy (h 0 = 25 MJ/kg) supersonic (M = 4) air flow. The experiments were performed in a VAT-104 wind tunnel (WT), TsAGI. The nose part of the model with a small-radius nose R w = 10 mm and half angle θ = 10° was inside the “Mach cone” of the underexpanded jet flowing out from the WT nozzle. Numerical and experimental results are in good agreement.
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