Experimental and numerical study of the Mars Sample Return Orbiter in cold laminar hypersonic flow

This action has been undertaken in the framework of a collaborative program between NASA and CNES to support CNES in the development of the Mars Sample Return Orbiter (MSRO). The study, devoted to ONERA in this first phase of the program, consists in testing a 1/50th size model in the hypersonic low Reynolds number wind tunnel R5Ch. Visualizations and heat-flux measurements have been carried out for different incidences in order to check the protection furnished to the satellite by the heat shield. The experimental measurements are discussed and compared with numerical results obtained with the Navier–Stokes finite volume solver FLU3M from ONERA. In addition, the influence on the measured heat flux of a partial cover, aiming at improving the thermal protection offered by the heat shield to the orbital vehicle is presented.