CAJ | 학술논문

采用数值模拟与工程计算相结合的方法对高超音速栅格翼进行了研究,分析了在高超音速情况下,栅格翼激波干扰对前缘钝度的敏感性以及对栅格翼热流分布产生的影响.结果表明:在同等栅格间距下,产生激波干扰的第三临界马赫数随栅格翼前缘钝度的增大而增加,传统的尖前缘栅格翼理论不适用于钝化前缘外形.另外,激波干扰在栅格翼表面会产生局部的高热流区域,但此热流峰值与前缘驻点相比仍然较低,因此对栅格翼热防护无额外影响.
채용수치모의여공정계산상결합적방법대고초음속책격익진행료연구,분석료재고초음속정황하,책격익격파간우대전연둔도적민감성이급대책격익열류분포산생적영향.결과표명:재동등책격간거하,산생격파간우적제삼림계마혁수수책격익전연둔도적증대이증가,전통적첨전연책격익이론불괄용우둔화전연외형.령외,격파간우재책격익표면회산생국부적고열류구역,단차열류봉치여전연주점상비잉연교저,인차대책격익열방호무액외영향.
Numerical simulation and engineering prediction methods were applied to investigate the influence of leading edge bluntness on the shock-shock interaction of hypersonic grid fin, besides, the heat flux distribution caused by the shock-shock interaction was also studied. Results showed that the third critical mach number, which defines the end of shock-shock interaction, increases with the leading edge bluntness when the space length between grid fin is fixed , and the traditional theory developed for the grid fin with sharp leading edge is invalid for blunt leading one. On the other hand, as a result of the shock-shock interaction, there is a region with high heat flux locally. Nevertheless, the peak value is much low compared with the stagnation, so it does not have additional influence on the thermal protection.