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Engineering aerodynamic heating method for hypersonic flow

1992 Journal of Spacecraft and Rockets  
A capability to calculate surface heating rates has been incorporated in an approximate three-dimensional inviscid technique. Surface streamlines are calculated from the inviscid solution, and the axisymmetric analog is then used along with a set of approximate convectiveheating equations to compute the surface heat transfer. The method is applied to blunted axisymmetric and three-dimensional ellipsoidal cones at angle of attack for the laminar ow of a perfect gas. The method is also applicable
more » ... is also applicable to turbulent and equilibrium-air conditions. The present technique predicts surface heating rates that compare favorably with experimental ground-test and ight data and numerical solutions of the Navier-Stokes NS and viscous shock-layer VSL equations. The new technique represents a signi cant improvement o v er current engineering aerothermal methods with only a modest increase in computational e ort.
doi:10.2514/3.26355 fatcat:dmsesflwrbgylimv7lqwy2zm4u