RESULTS OF TESTS OA12 AND IA9 IN THE AMES RESEARCH CENTER UNITARY PLAN WIND TUNNELS ON AN 0.030-SCALE MODEL OF THE SPACE SHUTTLE VEHICLE 2A TO DETERMINE AERODYNAMIC LOADS

摘要

Tests were conducted in the HASA/ARC Unitary Plan Hind Tunnels during April and May 1973, on an 0.030-scale replica of the Space Shuttle Vehicle Configuration 2A. Aerodynamic loads data were obtained at Mach numbers from 0.6 to 3.5.nThe investigation included Tests IA9A, B and C on the integrated (launch) configuration and Tests 0A12A and C on the isolated orbiter (entry configuration). The integrated vehicle vas tested at angles of attack and sideslip from -8 degrees to +8 degrees. The isolated orbiter was tested at angles of attack from -15 degrees to +40 degrees and angles of sideslip from -10 degrees to +10 degrees as dictated by trajectory considerations. The effects of arbiter/external tank incidence angle and deflected control surfaces on aerodynamic loads were also investigated.