1974•NASA STI Repository (National Aeronautics and Space Administration)Requires access
Results of transonic/supersonic static stability wind tunnel tests of an 0.004-scale space shuttle orbiter model (0A49)
Edward H. Allen
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Abstract
Experimental aerodynamic investigations of the configuration 4 space shuttle orbiter were conducted in the 14-inch trisonic wind tunnel during November and December 1973. Elevon, aileron, bodyflap, speedbrake, rudder effectiveness, and effects of ventral fins were investigated at angles of attack from -10 deg to 40 deg, angles of sideslip from -10 deg to +10 deg, and Mach numbers from 0.6 to 4.96. Resulting six-component static stability data and associated test information are presented.