Navier-Stokes simulation of a hypersonic generic wing/fuselageAn unsteady thin-layer Navier-Stokes code is used to calculate a generic wing/fuselage configuration at a Mach number of 25 and freestream conditions corresponding to an altitude of 220,000 feet. Calculations were performed with the assumptions of a perfect gas and with chemical equilibrium, and the boundary layer was assumed to be turbulent and to have a surface temperature prescribed at 1255 K. Results for the two different gas assumptions were compared in terms of distributions of pressure, density, temperature, Mach number, ratio of specific heat, and heat transfer. Numerical problems arising in the calculations were identified.
Document ID
19870057628
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Wai, John C. (Boeing Co. Seattle, WA, United States)
Dao, Samuel C. (Boeing Military Airplane Co. Seattle, WA, United States)
Chaussee, Denny S. (NASA Ames Research Center Moffett Field, CA, United States)