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Effect of Large Deflection of a Canard Control and Deflections of a Wing-Tip Control on the Static-Stability and Induced-Roll Characteristics of a Cruciform Canard Missile at a Mach Number of 2.01
Memorandum presenting an investigation conducted in the 4- by 4-foot supersonic pressure tunnel at Mach number 2.01 to determine the static stability and control characteristics of a canard-type missile configuration with large deflections of the canard controls and with deflection of wing-tip controls. The results of the investigation indicated that with a 30 degree deflection of the canard control a maximum trim normal-force coefficient of 0.4 and a maximum trim angle of attack of 12 degrees might be obtained for the optimum center-of-gravity location.
Date:
December 14, 1953
Creator:
Spearman, M. Leroy
System:
The UNT Digital Library