Wind tunnel tests made at 0.60 to 0.92 Mach, corresponding to 3.0×106 to 4.2×106 Re based on wing mean aerodynamic chord, and at angles of attack from -2° to 24°; strakes provided improvements in directional stability characteristics of wing fuselage configuration, reflected in characteristics of model in angle of attack range where losses in directional stability frequently occur.
Effect of high subsonic speeds of fuselage forebody strakes on static stability and vertical-tail-load characteristics of complete model having delta wing
NASA -- Tech Note
1961
32 pages
Report
English
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