A study of flow changes associated with airfoil section drag rise at supercritical speeds

Gerald E. Nitzberg, Stewart Crandall
naca-tn-1813
Feb 1949


A study of experimental pressure distributions and section characteristics for several moderately thick airfoil sections was made. A correlation appears to exist between the drag-divergence Mach number and the free-stream Mach number for which sonic velocity occurs at the airfoil crest, the chordwise station at which the airfoil surface is tangent to the free-stress direction.

An Adobe Acrobat (PDF) file of the entire report:
http://naca.central.cranfield.ac.uk/reports/1949/naca-tn-1813.pdf