CAJ | 학술논문

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.
발전료일충과음속다승력면적기동설계방법화설계정서,타기우이성공응용우아、과음속궤익설계화아음속쌍익면설계적"여량수정질대"개념.당승력면상출현초음속구화격파시자동인용영풍격식대공제방정진행수정.개발료일계렬접구정서,포괄목표압력설계정서.유차기동설계정양、TAU정서이급상응적접구정서건립료과음속다승력면기동반설계연건계통.용량개압익-궤익구형험증료설계방법화설계정서,결과표명재고과음속하설계질대유흔호적수렴성.
An aerodynamic design method and corresponding codes are developed for three-dimensional multi-lifting surfaces at transonic flow. It is based on the "iterative residual correction" concept that is successfully used for transonic wing design and subsonic multi-lifting surface design. The up-wind scheme is introduced into governing equations of multi-lifting surface design method and automatically acted when supersonic flow appears on the surface. A series of interface codes are programmed, including a target-pressure modification tool. Using the improved inverse aerodynamic design code, TAU code and interface codes, the transonic multi-lifting aerodynamic design software system is founded. Two cases of canard-wing configuration have been performed to validate the method and codes. The results show that the convergence of analysis/design iteration is very good at higher speed transonic flow.