Space Shuttle Verification of Transition Reentry Corridor at High Angles of Attack and Determination of Transition Aerodynamic Characteristics and Subsonic Aerodynamic Characteristics at Low Angles of Attack for the Boeing H-32 Booster

摘要

Experimental aerodynamic investigations were made in a transonic wind tunnel on a 1150-scale model of the Boeing H-32 space shuttle booster configuration. The purpose of the test was: (1) to verify the transonic reentry corridor at high angles of attack; (2) to determine the transonic aerodynamic characteristics; and (3) to determine the subsonic aerodynamic characteristics at low angles of attack. Test variables included configuration buildup, horizontal stabilizer settings of 0 and -20 deg, elevator deflections of 0 and -30 deg, and wing spoiler settings of 60 deg. (Author)