AERODYNAMIC CHARACTERISTICS AT A MACH NUMBER OF 2.01 OF TWO CRUCIFORM MISSILE CONFIGURATIONS HAVING 70° DELTA WINGS WITH LENGTH-DIAMETER RATIOS OF 14.8 AND 17.7 WITH SEVERAL CANARD CONTROLS

摘要

Further tests have been made at a Mach number of 2.01 of the fineness-ratio-l4.8 missile configuration of NACA KM L53I14. In the present investigation, this configuration and a configuration with a length-diameter ratio of 17.7 were equipped with 60° and 70° delta canard controls of area approximately twice that tested previously. The purpose of these tests was to determine the combined effect of canard size on pitching effectiveness and on interference losses at the wing.