1. has been calculated according to the Friedrichs theory, as outlined in reference 18, pp.397-402. In this method, the flow behind the shock is considered to be a simple wave, and the equation of a M a c h line m a y be written y - x t a n [(1/0) + 0] = 7(0)
2. Viscous Flow Along a Flat Plate Moving at High Supersonic Speeds
3. On the Boundary-Layer Equations in Hypersonic Flow and Their Approximate Solutions
4. Lees, L., Influence of the Leading-Edge Shock Wave on the Laminar Boundary Layer at Hypersonic Speeds, GALCIT Technical Report No. 1, July15,1954.