摘要
Abstract
In order to optimize the performance of a supersonic split line nozzle,the effect of the area ration at split line posi-tion(ε)on the flow field distribution was studied,which was proved by the ground firing test.The results show that,under the same ε,with the increase of swing angle(θ),the main trend of axial thrust coefficient(Cfx)decreases gradually.Under different values of ε,Cfx varies greatly at the same θ,and Cfx reaches the maximum value at ε=1.68.Under the same ε,with the increase of θ,the amplification factor of supersonic split line nozzle(K)increases first and then decreases,and the K value reaches the maximum(K=2.5)when θ is 1°～2°.Under different values of ε,K varies greatly,K>1at ε≥1.46 and θ=1°～8°,and the de-flection benefit is greatly affected by θ at ε=1.21,and the minimum value of K is less than 1.The numerical simulation of the nozzle plume state is consistent with the ground test,which verifies the effectiveness of the simulation method.The pressure at the separa-tion line has a certain deviation due to the model error,and the swing torque has a calculation deviation due to the non-uniform dis-tribution of the pressure at the separation line.In the future,the numerical model will be continuously optimized,and the influence of the non-uniform distribution of the separation line pressure and the refinement of the model on the accurate design will be fully considered,and the nozzle performance will be continuously optimized.关键词
超音速分离线摆动喷管/分离线扩张比/轴向推力系数/矢量角放大系数Key words
supersonic split line nozzle/area expansion ration at split line position/axial thrust coefficient/angle vector amplifi-cation factor分类
航空航天
