1. Shapiro, A. EL, The Dynamics and Thermodynamics of Compressible Fluid Flow, Vol.1, 1953, Ronald Press, New York, pp.144-145.
2. Mitchell, G. A. and Cubbison, R. W. "An Experimental Investigation of the Restart Area Ratio of a Mach 3 Axisymmetric Mixed Compression Inlet/' TMX-1547, 1968, NASA. on an airfoil from the airfoil crest (where the tangent to the airfoil surface is parallel to the freestream) to the trailing edge. Their method relies heavily on empiricism and on a detailed understanding of the physical phenomena present in a supersonic flow region terminated by a shock wave. The Sinnott and Osborne method was used by the author in toto except that for the present results, compressibility corrections were made using the Karman-Tsien law instead of the Prandtl-Glauert rule as used by Sinnott and Osborne.f