论文部分内容阅读
为使涡轮/冲压组合发动机能在宽广的飞行高度、速度内飞行,设计一种组合发动机可调进气道气动结构.编制带黏性修正激波系结构预估程序,实现不同来流马赫数及来流攻角下,进气道内激波系结构布置及强度预估,并指导进气道可调楔板尺寸选取.考虑进气道附面层抽吸后,对来流在马赫数为1.6～4.0范围内,-2°,0°和+2°三种攻角下进气道二维流场进行数值计算,流场结构与二维带黏性修正激波系结构预估程序计算结果非常吻合,得到进气道在各工况条件下气动性能,分析了来流马赫数及攻角对调节规律及进气道性能特性的影响规律.
In order to enable the turbo / ramjet engine to fly at a wide range of flight altitudes and speeds, a combined engine adjustable intake aerodynamic design was designed.A program of predicting shock structure with viscous correction was developed to achieve different flow Mach numbers And the angle of attack, the structure and strength of the shock wave in the air intake system are estimated, and the size of the adjustable wedge of the air intake is given.After taking into account the suction of the air inlets, 1.6 ~ 4.0, -2 °, 0 ° and + 2 ° of the three kinds of attack angles of the two-dimensional numerical simulation of inlet flow field, flow field structure and two-dimensional viscous correction shock wave structure prediction program to calculate The results are in good agreement. The aerodynamic performance of the intake duct under all working conditions is obtained. The influences of the Mach number and the angle of attack on the regulation law and the performance characteristics of the intake duct are analyzed.