RESULTS OF AH AERODYNAMIC INVESTIGATION OF A SPACE SHUTTLE ORBITER/747 CARRIER VEHICLE CONFIGURATION TO ESTABLISH A FREE-STREAM DATA BASE FOR ALT SEPARATION INVESTIGATIONS, UTILIZING A 0.0125-SCALE MODEL (48-0/AX13l8I-l) IN THE ARC 14-FOOT WIND TUNNEL (CA23A)

摘要

This report presents results of tests conducted on a 0.0125-scale model of the l40c (Modified) Space Shuttle Orbiter and a 0.0125-scale model of the 747 CAM configuration in the HASA-ARC ll4-foot Wind Tunnel. Force and moment data were obtained for each vehicle separately at a Mach number of 0.6, and for the mated orblter/747 configuration at Mach num bers of 0.3, 0.5. 0.6, and 0.7. The enclosed data forms a pre-launch and free air data base for planned separation tests of the carrier ALT configuration. Six component force and moment data are presented for each vehicle as well as total mated carrier vehicle data for mated runs. Orbiter angles of attack from 0 degrees to +12 degrees and 747/Currier angles of attack from -3 degrees to +7 degrees were investigated at angles of sideslip of 0 degrees and -5 degrees. Model variables include orbiter elevon and rudder deflections, orbiter tail cone-on and off, various orbiter/747 attach structure con figurations, 747 stabilizer end rudder deflections, and 747 CAM modification components-on and cif. The tests, designated CA23A, were con ducted from March 18 through April l4, 1975.