STABILITY AND TRANSITION IN CHEMICALLY REACTING NONEQUILIBRIUM FLOWS

IT IS PROPOSED HERE TO DEVELOP A METHOD FOR PREDICTION OF TRANSITION ON NASP (NATIONAL AERO-SPACE PLANE) CONFIGURATION AND FOR THE CONTROL/ENHANCEMENT OF SUPERSONIC COMBUSTION IN THE SCRAMJET. THE METHOD IS BASED UPON LINEAR STABILITY ANALYSIS WITH NONEEQUILIBRIUM EFFECTS WHICH TYPIFY THE BOUNDARY LAYERS ON NASP AIRFRAME AND THE MIXING LAYER IN THE SCRAMJET. THESE THREE-DIMENSIONAL VISCOUS LAYERS, DEPENDING UPON FLOW PARAMETERS, MAY BE SUBJECTED TO VARIOUS TYPES OF INSTABILITIES SUCH AS TOLLMIEN-SCHLICHTING, CROSSFLOW AND GORTLER INSTABILITY. IN ORDER TO DELAY TRANSITION OR AUGMENTMIXING, A STUDY OF THESE INSTABILITIES WILL BE MADE AND MEANS FOR THEIR CONTROL WILL BE DEVISED. PHASE I WILL BE A FEASIBILITY STUDY IN WHICH LINEAR VISCOUS STABILITY THEORY WITH FINITE-RATE CHEMISTRY EFFECTS WILL BE DEVELOPED.