J. A. Fay

Bio: J. A. Fay is an academic researcher. The author has contributed to research in topics: Stagnation temperature & Critical heat flux. The author has an hindex of 1, co-authored 1 publications receiving 1359 citations.

Hypersonic and high temperature gas dynamics

Abstract: Some Preliminary Thoughts * Part I: Inviscid Hypersonic Flow * Hypersonic Shock and Expansion-Wave Relations * Local Surface Inclination Methods * Hypersonic Inviscid Flowfields: Approximate Methods * Hypersonic Inviscid Flowfields: Exact Methods * Part II: Viscous Hypersonic Flow * Viscous Flow: Basic Aspects, Boundary Layer Results, and Aerodynamic Heating * Hypersonic Viscous Interactions * Computational Fluid Dynamic Solutions of Hypersonic Viscous Flows * Part III: High-Temperature Gas Dynamics * High-Temperature Gas Dynamics: Some Introductory Considerations * Some Aspects of the Thermodynamics of Chemically Reacting Gases (Classical Physical Chemistry) * Elements of Statistical Thermodynamics * Elements of Kinetic Theory * Chemical Vibrational Nonequilibrium * Inviscid High-Temperature Equilibrium Flows * Inviscid High-Temperature Nonequilibrium Flows * Kinetic Theory Revisited: Transport Properties in High-Temperature Gases * Viscous High-Temperature Flows * Introduction to Radiative Gas Dynamics.

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On Catalytic Recombination Rates in Hypersonic Stagnation Heat Transfer

Abstract: Stagnation laminar heat transfer at hypersonic speeds depends on the rate of recombination of the dissociated air behind the detached shock wave. This paper is concerned with the case of a large recombination t ime compared to the t ime of diffusion across the boundary layer. The conditions of existence of such a "frozen flow" and i ts coupling with the dissociation lag behind the shock are discussed. In order to account for finite catalytic recombination rates at the wall, a nonsimilar boundary condition is introduced which can be reduced to similarity for stagnation flow only. In this latter case, Lees' ( l ) 3 and Fay and Ridell's (2) heat transfer solutions are shown to correspond to the l imit ing case of an infinitely fast catalyst. The validity of their solutions is extended to the general case of a wall of finite catalytic efficiency, by introducing a correction factor (p. This factor is a s imple function of the flight condit ion, nose geometry and the wall catalytic recombinat ion rate constant . For a given nose material , the percentage of the heat transfer by catalysis is found to in crease wi th the velocity, the nose diameter and the wall temperature and to decrease with alt itude. Finally, the experimental values obtained for the catalytic recombination rates of oxygen and nitrogen atoms on various surfaces i l lustrate numerically the importance of the nature of the wall on the catalytic heat transfer to a missi le nose . In particular, the superiority of pyrex over metal l ic surfaces stresses the need for more experimental values for glassy and ceramic coatings.