Computational and experimental investigation of subsonic internal reversing flowsThe flow inside a model exhaust configuration was studied using both experimental and computational techniques. The hardware was tested at the NASA Lewis Research Center's Powered Lift Facility at tailpipe total pressure to ambient static pressure ratios ranging from 1.0 to 5.0. The flow simulations were obtained using the two 3-D Navier-Stokes CFD codes run on the Lewis Cray Y-MP computer. Both codes produced oscillatory solutions due to the inflow boundary condition reflecting acoustic waves. The CFD solutions correctly predicted the flow separation along the inside elbow of the takeoff and also along the walls of the ventral duct. Mass flow rates were overpredicted due to underprediction of the turbulent energy dissipation and subsequent total pressure loss.
Document ID
19920071546
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Rhodes, James A. (McDonnell Aircraft Co. Saint Louis, MO, United States)
Esker, Barbara S. (NASA Lewis Research Center Cleveland, OH, United States)
Smith, C. F. (Sverdrup Technology Inc. Brook Park, OH, United States)