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.


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    Rarefield-Flow Shuttle Aerodynamics Flight Model

    Blanchard, R. / Larman, K. / Moats, C. et al. | British Library Conference Proceedings | 1993


    Rarefield-Flow Shuttle Aerodynamics Flight Model

    Blanchard, R.C. | Online Contents | 1994


    Rarefied-flow shuttle aerodynamics flight model

    Blanchard, Robert C. / Larman, Kevin T. / Moats, Christina D. | AIAA | 1994


    Rarefied-flow shuttle aerodynamics flight model

    Blanchard, Robert C. / Larman, Kevin T. / Moats, Christina D. | NTRS | 1993


    Rarefied-flow shuttle aerodynamics flight model

    BLANCHARD, ROBERT / LARMAN, KEVIN / MOATS, CHRISTINA | AIAA | 1993