摘要
为了测定具有埋入式进气道的某航弹发动机进排气对航弹的气动影响量 ,采用引射式动力模拟器在FL 7高速风洞 ,首次在国内成功地进行了高速风洞进排气动力模拟试验。试验模型缩比为 1∶1 0 ,M =0 .7,P0j/P∞ =2 .62 ,Cφ=0 .79。试验结果表明 ,有动力后XD,CL,CD增加 ,Cma减少。试验表明在高速风洞中对于小尺寸的试验模型 。
It is briefly introduced of the investigation of engine simulation test with ejector in FL 7 high speed wind tunnel in this paper. Test condition: M ∞=0.7, P 0j / P ∞=2.62, C φ =0.79. The test results show that the air intake and exhaust increase the value of X D,C L and C D , but decrease the value of C ma . And it also shows that the test is a simple and good method for small model in high speed wind tunnel.
出处
《流体力学实验与测量》
CSCD
北大核心
2002年第3期8-13,共6页
Experiments and Measurements in Fluid Mechanics
关键词
排气流模型
引射器
动力模拟
进气流
风洞试验
飞机
high speed wind tunnel
exhaust flow simulation
ejector
dynamic modeling
inlet flow
