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非对称喷管是超燃冲压发动机和涡轮基组合循环(TBCC)发动机中特有的关键部件,在跨大马赫数范围工作时,往往在非设计点下会出现严重的流动分离。针对非对称喷管在过膨胀状态下的流动分离现象,通过试验验证二维数值计算(计算采用计算流体力学(CFD)方法)的正确性,利用数值计算样本点拟合得到了非对称喷管在过膨胀状态下的分离准则表达式,并进一步通过不同构型的非对称喷管分离的试验数据来验证该准则的准确性和普适性。研究结果表明,通过特定非对称喷管计算分离数据获得的分离准则与试验结果吻合得较好,在所进行的试验模型和条件下,两者之间的均方根误差为3.68%,更好地说明了该分离准则对非对称喷管内的分离预测具有较好的准确性,同时也跨出了其普适性证明的第1步。
Asymmetric nozzles are a unique and critical component of scramjet and TBCC engines and often experience severe flow separation at non-design points when operating over a wide range of Mach numbers. Aiming at the asymmetric nozzle flow separation in over-inflated state, the correctness of two-dimensional numerical calculation (computational fluid dynamics (CFD) method) was verified through experiments. The asymmetric nozzle The separation criterion expression in the over-inflated state and the further verification of the accuracy and universality of the criterion by the experimental data separated by different configurations of asymmetric nozzle. The results show that the separation criterion obtained by the calculation of the separation data by a specific asymmetric nozzle is in good agreement with the experimental results. Under the experimental model and conditions, the root mean square error between the two is 3.68% It is shown that this separation criterion has good accuracy for the separation prediction in asymmetric nozzles and at the same time it also takes the first step of its universal proof.