Experimental Investigation of 3-D Shock/Turbulent Boundary Layer Interaction - Technical Report -

Abstract

For a lot applications there is a need of experimental data on 3-D shock wave/turbulent boundary layer interaction, especially for the lower Mach number cases. So in August/September 1990 a basic experimental investigation was carried out in the transonic wind tunnel facility of DLR Goettingen (TWG). The test set-up mainly consisted of a sharp edged flat plate with a straight fin, positionednormal to the plate, generating a swept perpendicular shock wave to interact with the flat plats's boundary layer. The Mach numbers tested were M infinity &#61 1.63, 1.71, 1.79, 1.89, 2.00. The fin angle was varied between Theta &#61 5.0degree and Theta &#61 22.5 degree in steps of Delta Theta &#61 2.5degree. The tests included surface flow visualization and surface pressure measurements. The main objectives to be achieved within this first test phase were to gain first experiences with 3-D shock/boundary layer interaction, to qualify theset-up for further more extensive studies, i.e. flow field measurements in the interaction region with LDV for instance, and to provide reliable test data for the validation of numerical codes usedto compute this kind of flow. This investigation is part of the CEC BRITE/EURAM pilot phase of task 1051/1064 "Supersonic Flow Phenomena" and is so partly sponsored under the corresponding CEC- contract Aero 0027-C(A). The test results are intended to contribute to the common data base which is one main of this European research program. The present report gives a description of the test set-up and a complete presentation of the test results.