FLUCTUATING PRESSURE LOADS DEFINITION FOR HYPERSONIC VEHICLE STRUCTURES

A RESEARCH PROGRAM IS PROPOSED TO INVESTIGATE THE PREDICTION CAPABILITY FOR AEROACOUSTIC LOADS SUBJECT TO HYPERSONIC FLOW CONDITIONS. IN PARTICULAR, THIS INVESTIGATION WILL FOCUS ON HYPERSONIC FLOW STRUCTURES FEATURING CONTROL SURFACES THAT EXPERIENCE 2D AND 3D SHOCK/BOUNDARY LAYER INTERACTIONS. REGIONS SUBJECT TO THESE FLOW INTERACTIONS CONSIST OF INLETS (COWL) OF AIR BREATING SYSTEMS, BOW SHOCK/TAIL BOUNDARY LAYERS, VERTICAL/HORIZONTAL TAIL SHOCK/BOUNDARY LAYERS, WING HOCK/FUSELAGE BOUNDARY LAYER, AND RAMPS LEADING TO THE INLETS. AS A CONSEQUENCE OF THE LIMITED DATA BASE (M<3) AVAILABLE FOR THESE INTERACTIONS, A DETAILED INVESTIGATION IS PROPOSED THAT CONSISTS OF REVIEWING AEROACOUSTIC LITERATURE (BOTH CLASSIFIED/ UNCLASSIFIED), CRITIQUE TO PREDICTION TECHNIQUES RELATIVE TO FUNDAMENTAL PHYSICS AND SCALING LAWS, USE OF AEROACOUSTIC DATA (KNOWN TO THE AUTHORS AND EXISTING IN OUR LIBRARY) THAT ALLOWS FURTHER VALIDATION OF EXISTING PREDICTION TECHNIQUES (DEVELOPED BY THE PROPOSED TEAM) TOMACH 8, AND FINALLY TO RECOMMEND A FUNDAMENTAL EXPERIMENTAL PROGRAM TO EXTEND THE DATA BASE AS WELL AS ENHANCE PREDICTION TECHNIQUES.