SADSAC/SPACE SHUTTLE WIND TUNNEL TEST DATA REPORT STATIC AERODYNAMIC CHARACTERISTICS OF THE MSC-040A SPACE SHUTTLE ORBITER WITH WEDGE ♀ VERTICAL AND TWIN VERTICAL TAILS AT MACH NUMBERS FROM 0.6 TO 4.96

摘要

This report presents the results from experimental aerodynamic investi¬gations conducted on a 0.6-percent scale model of the MSC-040 Space Shuttle Orbiter in the Marshall Space Flight Center (MSFC) 14-Inch Trisonic Wind Tunnel (TWT) daring late February 1972.nThe purpose of this test program was to define the stability, control, end performance characteristics of the baseline MSC-040A orbiter configura¬tion with proposed alternate wing pods, with several vertical tail configura¬tions with and without flared rudders, and with upper wing surface flap deflections.nForce and moment data end modal base and balance cavity pressure date were obtained for a Mach, range of 0.60 through U.96 and dynamic pressure range of U65 through I58O psf. Model attitude was varied from 0 to +34 degrees angle of attack at zero sideslip and -4 to +10 degrees angle of sideslip at C, 1C, 20, and 24 degrees angle of attack.