A model of the Shuttle Orbiter rarefied-flow aerodynamic force coefficients has been derived from the ratio of flight acceleration measurements. The in-situ, low-frequency (less than 1Hz), low-level (approximately 1 x 10 to the -6th power g) acceleration measurements are made during atmospheric re-entry. The experiment equipment designed and used for this task is the High Resolution Accelerometer Package (HiRAP), one of the sensor packages in the Orbiter Experiments Program. The HiRAP-derived aerodynamics model is described in detail. The model includes normal and axial hypersonic continuum coefficient equations as function of angle of attack, body-flap deflection, and elevon deflection. Normal and axial free molecule flow coefficient equations as a function of angle of attack are also presented, along with flight-derived rarefied-flow transition bridging formulae. Comparisons are made between the aerodynamics model, data from the latest Orbiter Operational Aerodynamic Design Data Book, applicable computer simulations, and wind-tunnel data.
Rarefield-Flow Shuttle Aerodynamics Flight Model
1994
8 pages
Report
Keine Angabe
Englisch
Aerodynamics , Manned Spacecraft , Spacecraft Trajectories & Flight Mechanics , Free molecular flow , Hypersonic flow , Mathematical models , Rarefied gas dynamics , Spacecraft reentry , Transition flow , Space shuttle orbiters , Accelerometers , Angle of attack , Computational fluid dynamics , Computerized simulation , Data simulation , In-flight monitoring , Spacecraft modules , Wind tunnel tests
Rarefield-Flow Shuttle Aerodynamics Flight Model
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