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.
The method of characteristics is formulated for the computation of the supersonic flow of an inviscid, reacting gas over a smooth three-dimensional body. Various methods of constructing networks of bicharacteristic lines are examined from the point of view of numerical stability and accuracy. A new method of forming the network, which consists of projecting forward along streamlines from data points on specified data planes, is found to be most easily adopted to the particular requirements of nonequilibrium chemistry. The general method was coded for the IBM 7090 computer and the program demonstrated for the case of an ideal gas. Calculations were made for the case of an ideal gas. Calculations were made for the flow about a spherical-tip 15 degree half-angle cone at 10 degree angle of attack and a generalized elliptical body at zero incidence. Since the program yields the pressure distribution along specified streamlines, it is straightforward, in principle, to link it to a finite-rate chemistry stream tube program to treat three-dimensional, nonequilibrium flows. (Author).
A compilation of computer programs useful in the design of flight vehicles. Technical domains covered include the following: Structures; Aerodynamics; Vehicle dynamics; Flight control; Environmental control; Crew escape and retardation; and Landing gear subsystems. All programs were devised in-house in the Air Force Flight Dynamics Laboratory or were prepared for them under R and D contracts. (Author).
