SHOCK TUNNEL STUDIES OF THE AERODYNAMICS OF ATMOSPHERIC ENTRY
GENERAL ELECTRIC CO PHILADELPHIA PA MISSILE AND SPACE DIV
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Shock tunnel studies of the aerodynamic problems of current and future atmospheric entry vehicles are presented. Five major es instrumentation techniques are sed to meas re the following types of odel data 1 surface pressure distributions, through the use of small piezoelectric crystal gages and special mounting and calibration techniques, 2 surface heat transfer distributions, through the use of thin film resistance thermometers quantitative and scorch models qualitative, 3 aerodynamic forces and moments, through the use of the optical tracking of light models that are allowed to fly freely in the test flow, 4 flow field geometries through the use of high speed schlieren and shadowgraph techniques, and 5 boundary layer flow directions, inferred from surface oil streak studies. Typical experimental results are presented and discussed.
- Test Facilities, Equipment and Methods
- Spacecraft Trajectories and Reentry