Drag and rolling-moment effectiveness of trailing-edge spoilers at Mach numbers 2.2 and 5.0
Description:
Report presenting free-flight measurements of the rolling effectiveness and drag of trailing-edge spoilers on low-aspect-ratio wings with both laminar and turbulent boundary layers at two different Mach numbers. The effect of a spoiler deflected from the surface of a wing is to cause boundary-layer separation upstream.
Date:
October 3, 1955
Creator:
Canning, Thomas N. & DeRose, Charles E.
Item Type:
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Report
Partner:
UNT Libraries Government Documents Department