A validation study of Computational Fluid Dynamics (CFD) for Supersonic Retropropulsion (SRP) was conducted using three Navier-Stokes flow solvers (DPLR, FUN3D, and OVERFLOW). The study compared results from the CFD codes to each other and also to wind tunnel test data obtained in the NASA Ames Research Center 9′×7′ Unitary PlanWind Tunnel. Comparisons include surface pressure coefficient as well as unsteady plume effects, and cover a range of Mach numbers, levels of thrust, and angles of orientation. The comparisons show promising capability of CFD to simulate SRP, and best agreement with the tunnel data exists for the steadier cases of the 1-nozzle and high thrust 3-nozzle configurations.
Supersonic retropropulsion CFD validation with Ames Unitary Plan Wind Tunnel test data
01.03.2013
16670482 byte
Aufsatz (Konferenz)
Elektronische Ressource
Englisch
Supersonic Retropropulsion Validation Experiment in the NASA Langley Unitary Plan Wind Tunnel
Online Contents | 2014
|Supersonic Retropropulsion Dynamic Data Analysis from NASA Langley Unitary Plan Wind Tunnel
Online Contents | 2014
|