Current status of numerical flow prediction for separated nozzle flows

Kurzfassung

The European ‘Flow Separation Control Device’ group (FSCD) organized in collaboration with the French ‘Aérodynamiques des tuyères et Arrière-Corps’ group (ATAC) a CFD workshop with test cases on different nozzle flow topics. One of these test cases (1A) was managed by the German Aerospace Center (DLR) and Astrium ST. The objective was to compute the flow inside a strongly over-expanded truncated ideal contour nozzle with respect to the prediction of location and shape of the flow separation, the oblique shock and the Mach disc. Experimental data were provided by DLR. An introduction to the test facility and the experimental setup is given. The numerical results are evaluated and compared to test data. A concluding synthesis illustrates the current status of nozzle flow computation.