An approximate determination of the lift of slender cylindrical bodies and wing-body combinations at very high supersonic speeds

Reese H. Ivey, Robert R. Morrissette
naca-tn-1740
Oct 1948


A theory for very high supersonic flow is applied to determine a first approximation to the pressure distribution, lift, and drag due to lift for a slender cylindrical body of revolution and wing-body combination. The method is applicable only if the altitude of flight is low enough for the gas dynamics type of flow to exist, if the angle of attack is large, and if the Mach number is extremely large.

An Adobe Acrobat (PDF) file of the entire report:
http://naca.central.cranfield.ac.uk/reports/1948/naca-tn-1740.pdf