要約

Three-dimensional inviscid flow fields over three variants of an integrated design of a hypersonic flying vehicle with an air-breathing engine are investigated numerically. Computations are performed by solving the three-dimensional Euler equations, based on a multizone technology implemented in an ARGOLA 2 computational fluid dynamics program package. The numerical study is performed without modeling the exhaustion of the "hot" jet from the engine duct into a concurrent flow. The effect of the fuselage bluntness and the shape of the forward sidepieces of the intake on the flow structure and its internal characteristics at Mach number M_∞ = 6 and angles of attack α = 0−10° is studied. Numerical predictions are compared with the experimental results obtained in the T-121 wind tunnel based at TsAGI.