AER0DYNAMIC RESULTS OF A SEPARATION EFFECTS TEST OH A 0.01O-SCALE MODEL (52-OTS) OF THE INTEGRATED SSV IN THE AEDC/VEF 40-BY-40 INCH SUPERSONIC WIND TUNNEL A (IA111)

摘要

Experimental aerodynamic investigations were conducted March 27 through March 31, 1973, in the AEDC/VKF Tunnel A Facility on a 0.010-Scale Model (52-OTS) of the Integrated Space Shuttle Vehicle. The purpose of the investigation was to obtain data with the SRB in proximity to the Or biter/External Tank (O/ET) over a large O/ET initial angle of attack and sideslip range. SRB alone (greatly separated from O/ET)data were also requirednThe entire investigation was conducted at a free-stream Mach number of 4.5 at unit Reynolds numbers of 3.95 and 5.9 million per foot, This report for IA111 consists of two volumes:Volume 1 contains the data figures and Volume 2 contains the tabulated source data.