Wind-tunnel investigation of damping in roll at supersonic speeds of triangular wings at angles of attack /
Russell W. McDearmon and Robert A. Jones.
Description
- Language(s)
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English
- Published
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Washington, D.C. : National Advisory Committee for Aeronautics, 1956.
- Summary
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Experimental values of the damping in roll of three triangular wings have been obtained at Mach numbers of 1.62, 1.94, 2.22, 2.41, and 2.62 over a range of angle of attack from approximately 0 to 13 degrees. The aspect ratios of the wings were 1.46, 2.31, and 3.35.
- Note
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NACA Research Memorandum L56F13A.
"September 14, 1956."
Title from cover.
- Physical Description
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32 p. :
ill. ;
27 cm.
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