Supersonic retropropulsion CFD validation with Ames Unitary Plan Wind Tunnel test data

Author

Schauerhamer, D.G. ; Zarchi, K.A. ; Kleb, W.L. ; Edquist, K.T.

Author_Institution

NASA Johnson Space Center, Jacobs, Houston, TX, USA

fYear

2013

fDate

2-9 March 2013

Firstpage

1

Lastpage

14

Abstract

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.

Keywords

Mach number; Navier-Stokes equations; aerospace propulsion; aerospace testing; computational fluid dynamics; nozzles; supersonic flow; wind tunnels; Ames unitary plan wind tunnel test data; DPLR; FUN3D; Mach number; NASA Ames Research Center; Navier-Stokes flow solver; OVERFLOW; SRP; computational fluid dynamics; nozzle; supersonic retropropulsion CFD validation; surface pressure coefficient; unsteady plume effect; Computational fluid dynamics; Computational modeling; Electric shock; Face; NASA; Oscillators; Transducers;

fLanguage

English

Publisher

ieee

Conference_Titel

Aerospace Conference, 2013 IEEE

Conference_Location

Big Sky, MT

ISSN

1095-323X

Print_ISBN

978-1-4673-1812-9

Type

conf

DOI

10.1109/AERO.2013.6496859

Filename

6496859