Engineering aerodynamic heating method for hypersonic flow | Zendy

Christopher J. Riley | Zendy; Fred R. DeJarnette | Zendy

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Engineering aerodynamic heating method for hypersonic flow

Author(s) -

Christopher J. Riley,

Fred R. DeJarnette

Publication year - 1992

Publication title -

journal of spacecraft and rockets

Language(s) - English

Resource type - Journals

SCImago Journal Rank - 0.758

H-Index - 79

eISSN - 1533-6794

pISSN - 0022-4650

DOI - 10.2514/3.26355

Subject(s) - aerospace engineering , spacecraft , aerodynamics , spacecraft design , missile , hypersonic speed , space (punctuation) , space shuttle , systems engineering , space vehicle , aerodynamic heating , space exploration , mechanical engineering , engineering , computer science , physics , mechanics , heat transfer , operating system

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 convective-heating 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 flow of a perfect gas. The method is also applicable to turbulent and equilibrium-air conditions. The present technique predicts surface heating rates that compare favorably with experimental (ground-test and flight) data and numerical solutions of the Navier-Stokes (NS) and viscous shock-layer (VSL) equations. The new technique represents a significant improvement over current engineering aerothermal methods with only a modest increase in computational effort.

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