钝前缘三角翼的高阶湍流数值模拟研究

摘要

The computationalmodel of this paperis thedelta wing configurations with rounded leading edge from The Second Vortex Flow Experiment-VEF-2,and the flow solver is developed by AVIC Aerodynam-ic Research Institute ( ARI) of large aviation parallel computing platform -UNSMB,currently can carry out conventional ( U) RANS and unsteady DES calculation .The core content of this researchisfor the spe-cial double ( inner and outer ) main vortex flow structures and flow separation point of thedelta wing con-figurations with rounded leading edges .Through steady RANS computation and DES based on SA model calculation results show that the calculated degree of agreement with the test data is fine ,can accurately capture the double main vortex structures of delta wing ,and SA -DES calculation can significantly im-prove the calculation accuracy .%模拟钝前缘三角翼的特殊双（内、外侧）主涡流动结构和流动分离点的情况，通过定常的RANS计算和基于SA模型的DES计算表明，计算结果与试验数据吻合度较好，可以比较准确地捕捉了三角翼的双主涡结构。同时，应用SA-DES方法可以提高漩涡的模拟精度。