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.reptR....H
 Keywords:

 Aerodynamics;
 Computational Fluid Dynamics;
 Computational Grids;
 Hypersonic Speed;
 Inlet Flow;
 NavierStokes Equation;
 Shock Wave Interaction;
 Supersonic Combustion Ramjet Engines;
 Supersonic Inlets;
 Three Dimensional Flow;
 Boundary Conditions;
 Contraction;
 Flow Characteristics;
 Flow Distribution;
 Reynolds Number;
 Surface Properties;
 Fluid Mechanics and Heat Transfer