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

Abstract

For a lot of 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 straightfin, positioned normal to the plate, generating a swept perpendicular shock wave to interact with the flat plate'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 5.0^o and Theta &#61 22.5^o in stepts of Delta Theta &#61 2.5^o. The tests included surface flow visualization and surface pressure measurements. The main objectives to be achievedwithin this first test phase were to gain first experimences with 3D-shock/boundary layer interaction, to qualify the test set-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 used to compute this kind of flow. This investigation is part of the CEC BRITE/EURAM pilotphase of task 1051/1064 "Supersonic Flow Phenomena" and is so partly sponsord under the corresponding CEC-contract Aero 0027-C(A). The test results are intended to contribute to the common data base whichis one main aim of this European research program. The present reportgives a description of the test-up and a complete presentation of thetest results.