APPLICATION OF A 3-D SHOCK CONTROL BUMP ON A TRANSPORT

The application of a 3-d shock control bump on a transonic wing-body configuration was studied within the framework of a cooperation between DLR, ONERA and Airbus Germany. The 3-d bump design was based on pressure distributions of the 3-d configuration both from CFD and wind-tunnel experiments as well as on the results of previous 2-d and 2.5-d studies. The bump was applied to a half model wing and tested in the S2MA wind-tunnel of ONERA. Examples from the measured forces and pressure distributions both from standard pressure tab technique and pressure sensitive paint (PSP) are presented. The drag reduction in the experiment was somewhat less than expected from the pre-test calculations. This is at least partially attributed to differences in the shock formation between the full-model configuration used for the design and the half-model arrangement at the test. Further investigations on that subject are planned.