The results of an experimental investigation of the load distribution over two triangular wings in sideslip at Mach numbers from 1.20 to 1.79 are presented and compared with theory. The two wings tested have identical plan form, 45 degrees sweepback of the leading edge, and an aspect ratio of 4.0. One model was composed of round-nose airfoil sections and the other of sharp-nose, biconvex sections. For both wings the maximum thickness of streamwise sections was 6 percent and was located at the 30-percent chord.
A Comparison of the Experimental and Theoretical Loading over Triangular Wings in Sideslip at Supersonic Speeds
1951-05-18
Miscellaneous
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English
Dynamic derivatives in yaw and sideslip of thin wings at supersonic speeds
Engineering Index Backfile | 1956
|Theoretical lift and drag of thin triangular wings at supersonic speeds
Engineering Index Backfile | 1946
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