VOLUME 18 of 18 RESULTS OF TESTS 0A12 AND IA9 IN THE AMES RESEARCH CENTER UNITARY PLAIT WIND TUNNELS ON AN 0.030-SCALE MODEL OF THE SPACE SHUTTLE VEHICLE 2A TO DETERMINE AERODYNAMIC LOADS

摘要

Tests vere concerted in the NASA /ARC Unitary Plan Wind 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 Teats IA9A, B and C on the integrated (launch) configuration and Tests 0A12A and C on the isolated orbiter (entry configuration) The integrated vehicle was tested at angles of attack end sideslip from -8 degrees to +8 degrees. The isolated orbiter vas tested at angles of attack from -15 degrees to +40 degrees and angles of side-slip from -10 degrees to +10 decrees as dictated by trajectory consideration. The effects of arbiter/external tack incidence angle and deflected control surfaces on aerodynamic loads were also investigated.