INVESTIGATION OF SPACE SHUTTLE ORBITER SUBSONIC STABILITY AND CONTROL CHARACTERISTICS AND DETERMINATION OF CONTROL SURFACE HINGE MOMENTS IN THE ROCKWELL INTERNATIONAL LOW SPEED WIND TUNNEL (OA3-)

摘要

Experimental aerodynamic investigations were conducted on a sting mounted 0.030-scale representation of the 140A,T. Space Shuttle Orbiter in the Rockwell International 7.75- by 11-Foot Low Speed Wind Tunnel. These tests were conducted during the time period from 3 January 1974 to 25 January 1974. The NASA designation for this test was 0A37.nThe primary test objectives were to establish basic longitudinal and lateral-directional stability and control characteristics for the basic configuration plus control surface hinge moments.