EFFECTS OF INCOMING FLOW ASYMMETRY ON SHOCK TRAIN STRUCTURES IN CONSTANT-AREA ISOLATORS  

隔离段进口非对称来流对激波串结构的影响(英文)

作　　者：王成鹏[1] 张堃元[2] 程克明[1] 

机构地区：[1]南京航空航天大学航空宇航学院 [2]南京航空航天大学能源与动力学院

出　　处：《Transactions of Nanjing University of Aeronautics and Astronautics》2006年第1期1-7,共7页南京航空航天大学学报（英文版）

基　　金：国家自然科学基金(10572059)资助项目~~

摘　　要：To simulate the actual flowfield at the exit of the supersonic/hypersonic inlet, a wind tunnel is designed to study the flow in the scramjet isolator under the asymmetric incoming flow. And compression fields in the isolator are investigated using wall static and pitot pressure measurements. Three incoming Mach numbers are considered as 1.5, 1.8 and 2. Results show that the increase of the asymmetry of the flow at the isolator entrance leads to the increase of the shock train length in the isolator for a given pressure ratio. Based on the analysis of the flow asymmetry effect at the isolator entrance on the shock train length, a modified correlation is proposed to calculate the length of the shock train. Predicted results of the proposed correlation are in good agreement with the experimental data.考虑进气道出口流场的影响,设计了针对非对称超声速来流矩形隔离段流场研究的直联式试验风洞,模拟进气道出口流场的各种非对称进口条件进行了吹风试验,并测量了隔离段壁面静压和隔离段进口皮托压力。研究发现,随隔离段进口流动非对称程度的增加,激波串长度增加而隔离段耐受反压的能力下降。考虑了隔离段进口流动非对称的影响,对Billig-Waltrup的激波串长度公式作了改进,故提高了激波串长度预测的精确程度。

关 键 词：asymmetric supersonic flow shock train isolator design SCRAMJET wind tunnel test 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]