Space Shuttle Static Aerodynamic Characteristics of the Msc-040A THE Msc-040A Space Shuttle Orbiter with Wedge Centerline Vertical and Twin Vertical Tails at Mach Numbers from 0.6 to 4.96

摘要

The results are presented from experimental aerodynamic inv estigations conducted on a 0.6-percent scale model of the MSC-040 space shuttle orbiter in a 14 inch trisonic wind tunnel. The purpose of the test program was to define the stability, control, and performance characteristics of the baseline MSC-040A orbiter configuration with proposed alternate wing pods, with several vertical tail configurations with and without flared rudders, and with upper wing surface flap deflections. Force and moment data and model base and balance cavity pressure data were obtained for a Mach range of 0.60 through 4.96 and dynamic pressure range of 465 through 1580 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 0, 10, 20, and 24 degrees angle of attack. (Author)