Longitudinal and Lateral Stability Characteristics of a Low-Aspect-Ratio Unswept-Wing Airplane Model at Mach Numbers of 1.82 and 2.01
Description:
Memorandum presenting an investigation in the 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1.82 and 2.01 to determine the longitudinal and lateral stability characteristics of a fighter-type airplane model with a low-aspect-ratio unswept wing and a high horizontal tail. The results indicated a region of reduced longitudinal stability at low lifts at a Mach number of 2.01 that was caused by fuselage flow fields or vertical-tail effects on the horizontal tail.
Date:
January 28, 1956
Creator:
Spearman, M. Leroy & Driver, Cornelius
Item Type:
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Partner:
UNT Libraries Government Documents Department