A simplified method for assessing the effect of steady rolling on angle of attack and sideslip

Schmidt, Stanley F., Bergrun, Norman R., Merrick, Robert B., Matthews, Howard F.
naca-rm-a56k07
1957


Algebraic equations are derived which define the roll-induced steady-state angle of attack and sideslip of an airplane. The derivation omits gravity and certain nonlinear terms, and considers forward speed and rolling velocity constant.

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