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发展了一种跨音速多升力面的气动设计方法和设计程序,它基于已成功应用于亚、跨音速机翼设计和亚音速双翼面设计的“余量修正迭代”概念。当升力面上出现超音速区和激波时自动引用迎风格式对控制方程进行修正。开发了一系列接口程序,包括目标压力设计程序。由此气动设计程羊、TAU程序以及相应的接口程序建立了跨音速多升力面气动反设计软件系统。用两个鸭翼机翼构型验证了设计方法和设计程序,结果表明在高跨音速下设计迭代有很好的收敛性。
A pneumatics design methodology and design procedure for transonic multi-lift surfaces was developed based on the concept of “margin correction iterations” that have been successfully applied to sub-aeromechanical wing design and subsonic aerofoil design. When the supersonic zone and shock appear on the lifting surface, the governing equation is automatically referenced to the windward correction. Developed a series of interface procedures, including the target pressure design process. This pneumatic design Cheng Yang, TAU procedures and the corresponding interface program to establish a transonic multi-lift pneumatic anti-design software system. The design method and design procedure were verified with two canard wing configurations and the results show that the design iteration has good convergence at high transonic speeds.