An analysis of supersonic flow in the region of the leading edge of curved airfoils, including charts for determining surface-pressure gradient and shock-wave curvature

Samuel Kraus
naca-tn-2729
Jun 1952


Inviscid flow in the region of the leading edge of curved airfoils with attached shock waves is investigated. Tables and charts are presented for determining the surface-pressure gradient and the shock-wave curvature in supersonic flow of an ideal diatomic gas.

An Adobe Acrobat (PDF) file of the entire report:
http://naca.central.cranfield.ac.uk/reports/1952/naca-tn-2729.pdf