Numerical Determination of the Flow Field about Axisymmetric and Two-Dimensional Bodies in Supersonic Flow.
Research and development rept.,
NAVAL SHIP RESEARCH AND DEVELOPMENT CENTER WASHINGTON D C DEPT OF AERODYNAMICS
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A computer program for calculating the aerodynamic characteristics and local flow properties for an arbitrary axisymmetric or two-dimensional body in supersonic flow is developed. The supersonic portion of the flow field is calculated by the method of characteristics. A conical flow solution provides the starting conditions for a sharp body with an attached shock for a blunt body detached shock case, a method of integral relations solution provides the starting conditions. The flow field is treated as inviscid with the boundary layer effects being determined by the reference temperature method and a modified Reynolds analogy in the laminar case and the method of Spalding and Chi in the turbulent case. Manglers transformation accounts for transverse curvature in the laminar flow case. Details of the entire flow field are provided including any secondary shocks which may arise as a result of overexpansion or flared surfaces. Base flow properties are provided by the semiempirical method of Love. The calculated surface properties include pressure, equilibrium temperature, skin friction and heat transfer coefficients, and Mach number. Drag coefficients are determined with the components being broken down into pressure, friction and base contributions. Author
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