Serial/Series Title
1 Matching Results
Results open in a new window/tab.
Results:
1 - 1 of
1
Preliminary Wind-Tunnel Tests of Triangular and Rectangular Wings in Steady Roll at Mach Numbers of 1.62 and 1.92
Report presenting the damping-in-roll coefficients for a series of thin triangular plan-form wings and two rectangular wings in the 9-inch supersonic wind tunnel. The damping in roll of the rectangular wings was very close to what was predicted by linear theory, but the triangular wings gave results approximately 10 percent below that predicted when the wing leading edges were well ahead of or behind the Mach cone.
Date:
February 17, 1949
Creator:
Brown, Clinton E. & Heinke, Harry S., Jr.
System:
The UNT Digital Library