关键词: 高超声速进气道;混压式进气道;斜激波;优化

Abstract: Two dimensional mixed compression hypersonic inlets were optimized for maximum total pressure recovery and minimum drag coefficient respectively under the condition of Mach number 6,flight altitude 25 km and the angle between the flow direction at inlet exit and the flow direction of free stream 0°,2°,4° and 6°.The external shock turning angles were selected as design variables.The inlet pressure step-up ratio was selected as a constraint.One-dimensional aerodynamics was used in the optimization.The optimum oblique shocks series were attained.Results show that for the same design condition the optimum external oblique shocks series with minimum drag coefficient is almost the same as that with maximum total pressure recovery.Both have oblique shocks series approximately with equal strength.The principial of oblique shocks series with equal strength was validated by method of numerical calculation and it can be used in preliminary design of two-dimensional mixed compression hypersonic inlet.

Key words: Hypersonic inlet;Mixed compression inlet;Oblique shock;Optimization