Application of a Reynolds-Averaged Navier–Stokes Approach to Supersonic Retropropulsion Flowfields

Abstract

Systems analysis efforts have identified supersonic retropropulsion as a candidate decelerator technology for the human exploration of the surface of Mars. These efforts are presently challenged by a lack of available models and are looking to computational fluid dynamics analyses for databases representing the aerodynamic-propulsive interactions inherent to supersonic retropropulsion. This work uses a Reynolds-averaged Navier-Stokes approach to predict the flowfield structure, surface pressure distributions, and integrated aerodynamic force coefficients for four configurations recently tested in the NASA Langley Research Center Unitary Plan Wind Tunnel. These configurations have zero, one, three, and four nozzles on the model forebody. Comparisons are made with experimental data for static pressure distributions on the forebody and aftbody, and computational schlieren images illustrating the resulting flowfields have also been generated. The results of this work illustrate the applicability of the Reynolds-averaged Navier Stokes equations to this problem through comparison with data from a test series designed explicitly for the validation of computational fluid dynamics tools in simulating supersonic retropropulsion flowfields. The Reynolds-averaged Navier-Stokes approach applied performed well in predicting the surface pressure distribution and flowfield structure for supersonic retropropulsion configurations with single and multiple nozzles at zero degrees angle of attack and a thrust coefficient of approximately 2.0.

Similarity and Key Parameters of Retropropulsion Assisted Deceleration in Hypersonic Wind Tunnels

“…The two-equation turbulence model Menter's Shear Stress Transport (SST) was selected, as it was widely used in previous SRP simulations for other CFD codes [8,11,[17][18][19]. All presented CFD simulations were performed as steady-state computations for calorically perfect gas, as steady RANS computations compared favorably to experimental data in a study of SRP flows [19]. Large exhaust plumes found in retropropulsion flowfields effectively create a larger obstruction of the flow, as opposed to ordinary nonblowing wind-tunnel models.…”