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
01.06.1956
Sonstige
Keine Angabe
Englisch
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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