1. R. Iglish, NACA Technical Memo 1205 (1949).
2. Spanwise Variation in the Pitching-Moment Coefficient and the Center of Pressure Due to Various Basic Twist Distributions on Triangular Wings Having Supersonic Leading and Trailing Edge
3. An analysis formally identical to the present one can be carried out for the axisymmetric flow on a cone; the parameter corresponding to ɛ then becomes proportional to [(ρυ)w∕ρeμeue] S16.
4. W. D. Hayes and R. F. Probstein,Hypersonic Flow Theory, (Academic Press Inc., New York, 1959), pp. 228–291.
5. H. Schlichting,Boundary Layer Theory(McGraw-Hill Book Company, Inc., New York, 1960), 4th ed. There is required an obvious change in bothFand η as introduced here in order to employ this tabulation.