Transonic Navier-Stokes solutions about a complex high-speed accelerator configurationThree-dimensional transonic viscous flow computations are presented for a generic high-speed accelerator model which includes wing, body, fillets, and a no-flow through engine nacelle. Solutions are obtained from an algorithm for the compressible Navier-Stokes equations which incorporates an upwind-biased, flux-vector-splitting approach along with longitudinally-patched grids. Results are presented for fully turbulent flow assumptions and include correlations with wind tunnel data. A good quantitative agreement for the forebody surface pressure distribution is achieved between computations and the available wind-tunnel measurements at freestream Mach number equal to 0.9. Furthermore, it is demonstrated that the flow is stagnating around the boattail region due to separation from the aft-engine cowl lip.
Document ID
19900032789
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Ghaffari, Farhad (Vigyan Research Associates, Inc. Hampton, VA, United States)
Bates, Brent L. (Vigyan Research Associates, Inc. Hampton, VA, United States)
Luckring, James M. (Vigyan Research Associates, Inc. Hampton, VA, United States)
Thomas, James L. (NASA Langley Research Center Hampton, VA, United States)