Theoretical antisymmetric span loading for wings of arbitrary plan form at subsonic speeds

John DeYoung
naca-tn-2140
Jul 1950


A simplified lifting-surface theory that includes effects of compressibility and spanwise variation of section lift-curve slope is used to provide charts with which antisymmetric loading due to arbitrary antisymmetric angle of attack can be found for wings having symmetric plan forms with a constant spanwise sweep angle of the quarter-chord line.

An Adobe Acrobat (PDF) file of the entire report:
http://naca.central.cranfield.ac.uk/reports/1950/naca-tn-2140.pdf