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FDNS CFD Code Benchmark for RBCC Ejector Mode Operation: Continuing Toward Dual Rocket EffectsComputational Fluid Dynamics (CFD) analysis results are compared with benchmark quality test data from the Propulsion Engineering Research Center's (PERC) Rocket Based Combined Cycle (RBCC) experiments to verify fluid dynamic code and application procedures. RBCC engine flowpath development will rely on CFD applications to capture the multi -dimensional fluid dynamic interactions and to quantify their effect on the RBCC system performance. Therefore, the accuracy of these CFD codes must be determined through detailed comparisons with test data. The PERC experiments build upon the well-known 1968 rocket-ejector experiments of Odegaard and Stroup by employing advanced optical and laser based diagnostics to evaluate mixing and secondary combustion. The Finite Difference Navier Stokes (FDNS) code [2] was used to model the fluid dynamics of the PERC RBCC ejector mode configuration. Analyses were performed for the Diffusion and Afterburning (DAB) test conditions at the 200-psia thruster operation point, Results with and without downstream fuel injection are presented.
Document ID
20010020157
Acquisition Source
Marshall Space Flight Center
Document Type
Preprint (Draft being sent to journal)
Authors
West, Jeff
(NASA Marshall Space Flight Center Huntsville, AL United States)
Ruf, Joseph H.
(NASA Marshall Space Flight Center Huntsville, AL United States)
Turner, James E.
Date Acquired
September 7, 2013
Publication Date
January 1, 2000
Subject Category
Spacecraft Propulsion And Power
Meeting Information
Meeting: Propulsion
Location: Cleveland, OH
Country: United States
Start Date: October 26, 2000
End Date: October 27, 2000
Sponsors: Pennsylvania State Univ.
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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