Subsonic Aerodynamic Characteristics of Proposed High Wing Maneuvering Air-To-Surface Submunitions.
Final rept. Nov 75-May 76,
AIR FORCE ACADEMY COLO
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Subsonic aerodynamic and static stability characteristics of proposed high wing mounted Maneuvering Air-to-Surface Submunitions were investigated using 0.5-scale models in the USAFA 2 ft. x 3 ft. Subsonic Wind Tunnel facility. Data were obtained on fourteen configurations at Mach numbers of 0.18, 0.22, or 0.27 and corresponding Reynolds numbers of 230,000, 280,000, or 330,000 based on the average chord. Nominal angle of attack range tested varied from -10 to 15 degrees and angle of sideslip range at alpha 0 deg varied from -15 to 15 degrees. A technique for determining the maximum contribution of wing dihedral to static lateral stability as well as methods for improving aerodynamic efficiency are presented and verified experimentally. All configurations tested were statically stable in pitch, yaw, and roll and the maximum LD untrimmed obtained was 7.45. The results of the investigations may be used as a baseline for other configurations as well as general design guidance.
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