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.

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.

An Adobe Acrobat (PDF) file of the entire report: