AERODYNAMIC RESULTS OF AN ABOUT SEPARATION EFFECTS TEST (IA8) CONDUCTED IN THE NASA/ARC 14-FOOT TRANSONIC WIND TUNNEL ON A MODEL (6-OTS) OF THE ROCKWELL INTERNATIONAL LAUNCH CONFIGURATION INTEGRATED VEHICLE

摘要

Experimental aerodynamic investigations were conducted from February 12 through March 12, 1973 in the NASA/ARC 14-Foot Transonic Wind Tunnel on a 6-OTS 0.015-scale model of a Rockwell International Launch Configura¬tion Integrated Vehicle. The Ames dual sting support separation rig was used to obtain "grid-type" data for Tank-Booster (EOHT-BSRM) abort from Orbiter (SSV)nFreestream data were obtained for the Orbiter to provide a baseline for evaluation of proximity effects.