AERODYNAMIC RESULTS OF A SEPARATION EFFECTS TEST CONDUCTED IN THE AEDC 40*40 INCH TUNNEL A FACILITY ON THE ROCKWELL INTERNATIONAL LAUNCH CONFIGURATION 3 (MODEL 32-OTS) INTEGRATED VEHICLE (IA13) Vol. Ⅱ of Ⅲ

摘要

Experimental aerodynamic investigations were conducted from July 5 through July 17, 1973, in the AEDC/VKF tunnel A facility, on a 0.01 scale model (Model 32-OTS) of the Rockwell International launch configuration 3 Integrated Vehicle (excluding the left-hand booster). The AEDC captive trajectory system was utilized in conjunction with the tunnel primary sector to obtain "grid-type" data for tank (ET) abort from the Orbiter (SSV), and for nominal separation of one Booster (SRB) from the Orbiter-Tank combination. Booster separation was investigated with and without separation motors plume simulation. The plumes were generated by eight Mj = 2.15 nozzles using a 1500 psia cold air supply.