高超声速进气道优化设计初探

Investigation on optimization design of scramjet inlet

以总压恢复系数为目标,利用无粘流斜激波关系式和约束最优化计算方法,在考虑混合气体比热随温度变化的条件下,对二维混压式高超声速进气道设计方法作了初步探索,利用数值模拟软件对附面层作了修正,研究了进气道的基本性能。数值模拟结果表明:该进气道在飞行马赫数Ma=4～6.5范围内能够可靠工作。

To get maximum total pressure recovery coefficient, based on oblique shock equations and specific heats as the function of temperature, optimization design of scramjet inlet was primarily investigated. The boundary layer effect correction and primary performance analysis were accomplished by numerical simulation. Results of numerical simulation showed that the scramjet inlet could operate between Mach 4 and Mach 6.5.