Damping-in-roll coefficients for a series of triangular plan-form wings and two rectangular plan-form wings have been obtained from supersonic-tunnel tests. The wings were mounted on a body of revolution and tested at Mach numbers of 1.62 and 1.92.
Preliminary Wind-tunnel Tests of Triangular and Rectangular Wings in Steady Roll at Mach Numbers of 1.62 and 1.92
1956-06-01
Miscellaneous
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English
Density fields around sphere at mach numbers 1.30 and 1.62
Engineering Index Backfile | 1950
|Density fields around a sphere at mach numbers 1.30 and 1.62
TIBKAT | 1950
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