DESIGN AND QUALIFICATION OF A SUPERSONIC WIND TUNNEL FOR TRANSITION EXPERIMENTS

摘要

In air-breathing engines, the status of the boundary layerrnalong the intake surface dictates the aerothermal performance.rnThis paper presents the design of a quiet windrntunnel to study roughness induced boundary layer transitionrnin an adjustable supersonic regime (M 1.6 to 2.2)rnwith Reynolds varying from 30·10~6 m~(-1) to 46·10~6 m~(-1).rnThe features to achieve a low-disturbance environmentrnare described,in particular the design and implementationrnof the bleeding slots. The test model is a flat plate heavilyrninstrumented with thin films, and piezo resistive pressurerngauges. The optical access allows the use of pressure sensitivernpaints, Schlieren and infrared thermography. Thernqualification procedure to assess the test section performancernis described.