Supersonic Retropropulsion Computational Fluid Dynamics Validation with Langley 4×4 Foot Test Data

Validation of computational fluid dynamics for supersonic retropropulsion is shown through the comparison of three Navier-Stokes solvers and wind-tunnel test results. The test was designed specifically for computational fluid dynamics validation and was conducted in the NASA Langley Research Center supersonic 4×4 foot Unitary Plan Wind Tunnel. The test includes variations in the number of nozzles, Mach and Reynolds numbers, thrust coefficient, and angles of orientation. Code-to-code and code-to-test comparisons are encouraging, and possible error sources are discussed. [PUBLICATION ABSTRACT] Presented as Paper 2012-0864 at the AIAA 50th Aerospace Sciences Meeting, Nashville, TN, 9-12 January 2012