A combined analytical and experimental investigation of the effect of stagnation region chemicalionization non-equilibrium phenomena on the aerothermodynamic and electrical properties of the flow field over a hemisphere cylinder at hypersonic speeds was conducted. In the analytical studies, flow field caluclations were made using several IBM 704 computer programs which account for finite reaction rate processes. The experimental phases of the study were done in the Cornell Aeronautical Laboratory 6' Shock Tunnel at a nominally constant velocity of 15,500 ft/sec. Measurements were made of the surface pressure and heat transfer, shock layer pitot pressure, and suface layer electrical conductivity on hemishpere cylinder models for a range of values of the stagnation region non-equilibrium scaling parameter. (Author).

Two flow-field computer codes are described. The codes were developed to compute the flow about blunt axisymmetric or two-dimensional bodies moving with supersonic speeds at zero angle of attack. Boundary-layer effects and a variety of thermochemical options are included. A pair of auxiliary codes for machine-plotting the flow-field results is also described.