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Rolling, yawing, and hinge moments produced by rectangular aileronsAilerons described in references 1, 2, and 3, are summarized in the form of empirical equations which relate the aileron dimensions and displacements to the rolling, yawing, and hinge moments for pitch angles of 0 and 12 degrees, corresponding to angles of attack of the wings of 4 and 16 degrees, respectively.
Document ID
19930081199
Acquisition Source
Legacy CDMS
Document Type
Other
Authors
Heald, R H (Bureau of Standards)
Date Acquired
September 6, 2013
Publication Date
January 1, 1933
Report/Patent Number
NACA-TN-441
Report Number: NACA-TN-441
Accession Number
93R10489
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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