Julian H. Kainer
naca-tn-2009
Jan 1950
The study of the supersonic pressure distribution and wave drag of sweptback wings at zero lift has been extended by means of linearized theory to include the combined effects of plan-form taper and curvature of profile. Calculations have been made for a specific wing with a supersonic leading edge and these results are applicable to a limited family of plan forms.
An Adobe Acrobat (PDF) file of the entire report:
http://naca.central.cranfield.ac.uk/reports/1950/naca-tn-2009.pdf