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Supersonic Hypersonic Aerodynamics And Heat Transfer For Projectile Design Using Viscous Inviscid Interaction

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Supersonic Hypersonic Aerodynamics And Heat Transfer For Projectile Design Using Viscous Inviscid Interaction

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Author : Michael J. Nusca
language : en
Publisher:
Release Date : 1990

Supersonic Hypersonic Aerodynamics And Heat Transfer For Projectile Design Using Viscous Inviscid Interaction written by Michael J. Nusca and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1990 with Aerodynamic heating categories.

An aerodynamic design code for axisymmetric projectiles has been developed using a viscous-inviscid interaction scheme. Separate solution procedures for inviscid (Euler) and viscous (boundary layer) flowfields are coupled by an iterative solution procedure. This code yields body surface flow profiles in less than one minute of run time on minicomputers. These surface profiles represent converged solutions to both the inviscid and viscous equations. the capability of computing local reverse flow regions is included. The procedure is formulated for supersonic and hypersonic Mach numbers including both laminar and turbulent flow. In addition, aerodynamic heating equations are used to compute heat transfer coefficient and local Stanton number from flow profiles. Computed surface pressure profiles for Mach numbers 2 thru 6 are compared to wind tunnel measurements on cone-cylinder-flare projectiles. Computed surface heat transfer coefficients are compared to results obtained from wind tunnel measurements on cone-cylinder-flare, flat plate, and blunt-cone models at Mach numbers 5 and 10. Keywords: Hypersonic flow; Computational aerodynamics; Boundary layers; Heat transfer; Projectile design.