突起物气动热环境理论分析与试验研究

Theoretical Analysis and Experimental Study on Aerodynamic Heating Environment of Protuberance

针对高超声速飞行器复杂外形突起物干扰气动热环境参数准确预测难题,开展了数值模拟与工程计算相结合的方法研究,并开展了验证性风洞试验。理论预测与试验吻合良好,表明采用的"数值模拟+工程计算+试验验证"的研究方法正确,能较快的给出满足工程设计需求的高准确度热环境结果,既可大量节省试验经费又可有效缩短工程研发周期。

A combination method of numerical simulation and engineering calculation has been adopted to accurately predict aerodynamic heating environment parameters of complex protuberance interaction on hypersonic vehicles.In order to verify the method,wind tunnel tests have been carried out.The good agreement between theoretical predictions and experiment results show that the method adopted,described as ＂numerical simulation ＋ engineering calculation ＋ validation experiment＂ is correct.With this method,high accurate results of aerodynamic heating environment parameters for engineering design can be obtained quickly,and the cost of wind tunnel tests and engineering development cycle can be reduced remarkably.