COMPARISON BETWEEN EXPERIMENTAL AND NUMERICAL HEAT-FLUX DATA FOR SUPERSONIC-FLOW AROUND ELAC-1

The present paper deals with the comparison of calculations and measur ements of surface heat fluxes for the research configuration ELAC 1, c arried out at the Aerodynamisches Institut, RWTH Aachen. Only laminar and supersonic flow was investigated. One set of computations was obta ined with an implicit space marching method, based on the time-depende nt Thin-Layer Approximation of the Navier-Stokes equations. A second a pproach was carried out by solving the boundary layer equations for co mpressible flow. The measurements were conducted in the supersonic win d tunnel of the Aerodynamisches Institut of the RWTH Aachen. Thin film sensors were used for the diagnostics of the surface flow patterns. R esults are presented for flows with Mach numbers Ma(infinity) = 2 and Ma(infinity) = 2.5 for several angles of attack, The influence of the boundary layer and the lee side vortices on the surface flow pattern i s discussed.