NASA NTRS · 19930081199
Rolling, yawing, and hinge moments produced by rectangular ailerons
Abstract
Ailerons 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.
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Heald, R H. 1933-01-01. Rolling, yawing, and hinge moments produced by rectangular ailerons. https://ntrs.nasa.gov/citations/19930081199
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