Load distributions due to steady roll and pitch for thin wings at supersonic speeds

W. E. Moeckel, J. C. Evvard
naca-tn-1689
Aug 1948


A method is presented for determining the load distribution due to steady roll and pitch for thin flat-plate wings whose plan form is arbitrary except that a part of the leading edge must be supersonic.

An Adobe Acrobat (PDF) file of the entire report:
http://naca.central.cranfield.ac.uk/reports/1948/naca-tn-1689.pdf