*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.

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

http://naca.central.cranfield.ac.uk/reports/1957/naca-rm-a56k07.pdf