Publication Date:
2019-07-13
Description:
A Navier-Stokes computer code was validated using a number of two- and three-dimensional configurations for both laminar and turbulent flows. The validation data covers a range of freestream Mach numbers from 3 to 14, includes wall pressures, velocity profiles, and skin friction. Nozzle flow fields computed for a generic scramjet nozzle from Mach 3 to 20, wall pressures, wall skin friction values, heat transfer values, and overall performance are presented. In addition, three-dimensional solutions obtained for two asymmetric, single expansion ramp nozzles at a pressure ratio of 10 consists of the internal expansion region in the converging/diverging sections and the external supersonic exhaust in a quiescent ambient environment. The fundamental characteristics that were captured successfully include expansion fans; Mach wave reflections; mixing layers; and nonsymmetrical, multiple inviscid cell, supersonic exhausts. Comparison with experimental data for wall pressure distributions at the center planes shows good agreement.
Keywords:
AIRCRAFT PROPULSION AND POWER
Type:
NASA-CR-185197
,
E-5267
,
NAS 1.26:185197
,
AGARD Symposium on Combined Cycle Propulsion for Hypersonic Application; May 21, 1990 - May 25, 1990; Madrid; Spain
Format:
application/pdf
