Wing and vertical tail and elevon hinge moments.ĭata were obtained in the Mach number range from 0.6 to 1.55 with Reynolds Ure integration and to measure loads directly by load indicators on the The objective of these tests was to obtain aerodynamic loads on all vehi-Ĭle elements (orbiter, external tank and solid rocket boosters) by press. Rockwell International Space Transportation SystemĪn experimental investigation (test IA105A) was conducted in the ArnoldĮngineering Development Center 16-foot Transonic Propulsion Wind Tunnelįrom Septemthrough Septem(first entry) and from No responsibility for the data presented other than display characteristics

National Aeronautics and Space AdministrationĬhrysler Huntsville Electronics Division/Slidell Engineering Office assumes Prepared under NASA Contract Number NAS9-16283 Space Transportation System Development and Production Division RESULTS OF TESTS USING A 0.03 SCALE MODEL ROOT THANSONiC PriOPULSlON v.iNE TUNI'lEi. SHUTTLE j.STEGilAl£i) VEHICLE IN THE AEUC 16 (N&SA-Cfi-lbO&50) EtSULTS OF TESTS USlhG A Full text of ' Results of tests using a 0.03 scale model (47-OTS) of the Space Shuttle integrated vehicle in the AEDC 16 foot transonic propulsion wind tunnel (IA105A), volume 1'

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