NON-INTRUSIVE BOUNDARY LAYER TRANSITION FREQUENCY DETECTOR

A NON-INTRUSIVE, BOUNDARY-LAYER TRANSITION DETECTOR THAT CANINDICATE THE PRESENCE OF LOCAL TRANSITION AND PROVIDE INFORMATION ON THE FREQUENCY COMPONENTS OF THE FLOW WILL BE DEVELOPED. THE DESIGN CONCEPT IS AN ADAPTATION OF A TRANSITION DETECTOR USED SUCCESSFULLY IN BALLISTIC-MISSILE REENTRY-VEHICLE FLIGHTS. THE WORK WILL DEMONSTRATE CONCEPT FEASIBILITY ON FLIGHT SKINS OF PRESENT INTEREST TO NASA. A STUDY WILL BE PERFORMED TO PROVIDE DATA FOR MODELING THE TRANSITIONAL AND TURBULENT BOUNDARY LAYER PRESSURE SPECTRUM. AN EVALUATION OF ACOUSTIC NOISE SOURCES WHICH MAYAFFECT GAGE PERFORMANCE AND A METHOD FOR ADDRESSING THEM WILL BE MADE. A PRELIMINARY HEAT-RESISTANT DESIGN WILL BE CONSTRUCTED AND TESTED IN THE LABORATORY FOR LOCALIZED AND FREQUENCY RESPONSE. METHODS FOR IMPROVING GAGE ABILITY TO RESPOND TO ONLY LOCAL SIGNALS WILL BE IDENTIFIED. A FLIGHT TEST PROGRAM WILL BE SPECIFIED FOR EVALUATING GAGE PERFORMANCE IN A NASA FIELD TESTING. A NON-INTRUSIVE, BOUNDARY-LAYER TRANSITION DETECTOR THAT CANINDICATE THE PRESENCE OF LOCAL TRANSITION AND PROVIDE INFORMATION ON THE FREQUENCY COMPONENTS OF THE FLOW WILL BE DEVELOPED. THE DESIGN CONCEPT IS AN ADAPTATION OF A TRANSITION DETECTOR USED SUCCESSFULLY IN BALLISTIC-MISSILE REENTRY-VEHICLE FLIGHTS. THE WORK WILL DEMONSTRATE CONCEPT FEASIBILITY ON FLIGHT SKINS OF PRESENT INTEREST TO NASA. A STUDY WILL BE PERFORMED TO PROVIDE DATA FOR MODELING THE TRANSITIONAL AND TURBULENT BOUNDARY LAYER PRESSURE SPECTRUM. AN EVALUATION OF ACOUSTIC NOISE SOURCES WHICH MAYAFFECT GAGE PERFORMANCE AND A METHOD FOR ADDRESSING THEM WILL BE MADE. A PRELIMINARY HEAT-RESISTANT DESIGN WILL BE CONSTRUCTED AND TESTED IN THE LABORATORY FOR LOCALIZED AND FREQUENCY RESPONSE. METHODS FOR IMPROVING GAGE ABILITY TO RESPOND TO ONLY LOCAL SIGNALS WILL BE IDENTIFIED. A FLIGHT TEST PROGRAM WILL BE SPECIFIED FOR EVALUATING GAGE PERFORMANCE IN A NASA FIELD TESTING.