Mach 10 computational study of a threedimensional scramjet inlet flow field
Abstract
The present work documents the computational results for a combined computational and experimental parametric study of the internal aerodynamics of a generic threedimensional sidewallcompression scramjet inlet configuration at Mach 10. The threedimensional NavierStokes code SCRAMIN was chosen for the computational portion of the study because it uses a wellknown and wellproven numerical scheme and has shown favorable comparison with experiment at Mach numbers between 2 and 6. One advantage of CFD was that it provided flow field data for a detailed examination of the internal flow characteristics in addition to the surface properties. The experimental test matrix at mach 10 included three geometric contraction ratios (3, 5, and 9), three Reynolds numbers (0.55 x 10(exp 6) per foot, 1.14 x 10(exp 6) per foot, and 2.15 x 10(exp 6) per foot), and three cowl positions (at the throat and two forward positions). Computational data for two of these configurations (the contraction ratio of 3, Re = 2.15 x 10 (exp 6) per foot, at two cowl positions) are presented along with a detailed analysis of the flow interactions in successive computational planes.
 Publication:

Unknown
 Pub Date:
 March 1995
 Bibcode:
 1995mcst.reptQ....H
 Keywords:

 Computational Fluid Dynamics;
 Flow Distribution;
 Hypersonic Speed;
 Inlet Flow;
 Internal Flow;
 Supersonic Combustion Ramjet Engines;
 Three Dimensional Flow;
 Boundary Conditions;
 Computational Grids;
 Cowlings;
 Engine Inlets;
 NavierStokes Equation;
 Performance Tests;
 Pressure Distribution;
 Reynolds Number;
 Shock Waves;
 Fluid Mechanics and Heat Transfer