Journal ArticleDOI
Inviscid Surface Streamlines and Heat Transfer on Shuttle-Type Configurations
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TLDR
In this article, the axisymmetric analog is applied to solutions of boundary-layer equations to calculate laminar, transitional, and turbulent heating rates on arbitrary blunt-nosed three-dimensional bodies at angle of attack in hypersonic flow.Abstract:
A method is developed which calculates laminar, transitional, and turbulent heating rates on arbitrary blunt-nosed three-dimensional bodies at angle of attack in hypersonic flow. The geometry of the body may be specified analytically, or generated from a doubly cubic spline fit to coordinate points. Inviscid surface streamlines are calculated from Euler's equation using a prescribed pressure distribution. Laminar and turbulent heating rates are determined along a streamline by applying the axisymmetric analog to solutions of the axisymmetric boundary-layer equations. The location of the transition region may be specified optionally by geometric location, momentum thickness Reynolds number, or integrated unit Reynolds number along a streamline. Transitional heating rates are then calculated as a weighted average of the local laminar and turbulent values. Either ideal gas or equilibrium air properties may be used. Results are presented for blunted circular cones, and a typical delta-wing space shuttle orbiter at angle of attack. In comparison with experimental data, the present method was found to yield accurate laminar heating rates and reasonably accurate transitional and turbulent heating rates. The computer program developed to calculate the results presented herein requires only a few seconds of computing time per streamline on the CDC 6600 computer.read more
Citations
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Journal ArticleDOI
Approximate Convective-Heating Equations for Hypersonic Flows
TL;DR: In this paper, Laminar and turbulent heating-rate equations appropriate for engineering predictions of the convective heating rates about blunt reentry spacecraft at hypersonic conditions were developed, applicable to both nonreacting and reacting gas mixtures for either constant or variable-entropy edge conditions.
Proceedings ArticleDOI
Results of a flight experiment on the catalytic efficiency of the Space Shuttle heat shield
TL;DR: In this article, an experiment was performed on the second Space Shuttle flight to verify data from arc-heated wind-tunnel tests indicating that the thermal protection tiles used on the Shuttle's surface are non-catalytic to the recombination of dissociated air.
Journal ArticleDOI
A review of some approximate methods used in aerodynamic heating analyses
TL;DR: In this paper, the authors discuss some approximate methods which have been used to calculate aerodynamic heating rates on high-speed vehicles, including the stagnation point and leading edges, axisymmetric analog, laminar and turbulent heating rate, transition heating rates, gas models, and three-dimensional applications.
Journal ArticleDOI
Numerical Computation of Space Shuttle Laminar Heating and Surface Streamlines
TL;DR: In this article, exact inviscid flowfield codes are used, together with a quasi-three-dimensional boundary-layer analysis, to provide estimates of the windward surface heating and streamline patterns of the shuttle orbiter vehicle under laminar flow conditions.
Boundary layers in three dimensions
J.C. Cooke,M.G. Hall +1 more
TL;DR: In this article, the boundary layer equations for laminar compressible flow, and corresponding momentum integral equations, are written down, in an orthogonal curvilinear system of co-ordinates.
References
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Journal ArticleDOI
Laminar Heat Transfer Over Blunt-Nosed Bodies at Hypersonic Flight Speeds
TL;DR: In this article, the authors considered the case of laminar heat transfer over blunt-nosed bodies at hypersonic flight speeds, or high s tagnat ion temperatures, in which the chemical reaction rates are regarded as "very fas t" compared to the rates of diffusion across streamlines.
Journal ArticleDOI
Some properties of boundary layer flow during the transition from laminar to turbulent motion
Satish Dhawan,Roddam Narasimha +1 more
TL;DR: In this paper, the authors examined the transition in the boundary layer on a flat plate from the point of view of intermittent production of turbulent spots and derived a relation between the transition Reynolds number and the rate of production of the turbulent spots.
Journal ArticleDOI
The drag of a compressible turbulent boundary layer on a smooth flat plate with and without heat transfer
D. B. Spalding,S. W. Chi +1 more
TL;DR: In this article, the root-meansquare error of the theory of van Driest-II was calculated by using mixing-length theory and semi-empirically.
Journal ArticleDOI
Computation of Space Shuttle Flowfields Using Noncentered Finite-Difference Schemes
TL;DR: In this article, second-and third-order finite-difference schemes are described for numerical solution of the hyperbolic equations of fluid dynamics, and the results are compared with regard to dissipative and dispersive errors and shock-capturing ability.