Experimental investigation of the influence of the flow structure on the aerodynamic coefficients of the IXV vehicle

In the frame of the ESA Future Launchers Preparatory Programme (FLPP) an experimental re-entry phase of the Intermediate eXperimental Vehicle (IXV) configuration has been conducted in the DLR hypersonic wind tunnel H2K in Cologne. Tests have been carried out at Mach 6.0 and 8.7 with different flap deflection angles and the angle of incidence varied continuously between 20° and 55° to investigate the flow topology as well as the aerodynamic forces and moments and the surface pressure distribution. The experimental data show that depending on the combination of the flap deflection angle and angle of incidence the complex flow structure in the vicinity of the flaps (i.e. the shock/shock and shock/boundary layer interaction causing flow separation and reattachment) can influence the vehicle aerodynamic coefficients significantly