优化跨音速自适应壁试验段设计的试验研究  

THE TESTING RESEARCH FOR OPTIMIZING THE DESIGN OF TRANSONIC ADAPTIVE TEST SECTION

作　　者：左培初[1] 贺家驹[1] 李华星[1] 徐敏[1] 

机构地区：[1]西北工业大学第三研究室

出　　处：《力学学报》1995年第S1期103-108,共6页Chinese Journal of Theoretical and Applied Mechanics

摘　　要：分析了在矩形截面试验段中三元模型试验时的洞壁干扰分布。讨论了为扩大二元柔壁自适应壁风洞中进行飞机模型试验时的无干扰区，较合适的试验段宽高比。用两个翼身组合体模型，在西北工业大学高速二元柔壁自适应风洞中作了变试验段宽高比为Ｂ／Ｈ＝１．０，１．２，１．４时的测压试验。两个模型都在德国宇航院ＨＫＧ高速风洞中作了对比试验，研究结果表明，Ｂ／Ｈ＝１．４的柔壁试验段截面较为合适。This paper discusses the wall interference distribution of testing 3-D models in rectangular test section and the suitable width/height ratio B/H of the test section for extending wall interference free area.Two wing-body models were tested in Northwestern Polytechnical University(NPU)2-D flexible wall adaptive wind tunnel with B/H=1.0,1.2 and 1.4.The two models were tested in Germany DLR high speed wind tunnel HKG too. The results shows that for testing aircraft models B/H=1.4 is suitable.

关 键 词：风洞试验 洞壁干扰 自适应壁风洞 

分 类 号：O354.2[理学—流体力学]