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| Author | : Wallace D. Hayes |
| Publisher | : Courier Corporation |
| Total Pages | : 628 |
| Release | : 2012-07-13 |
| Genre | : Science |
| ISBN | : 0486160483 |
Unified, self-contained view of nonequilibrium effects, body geometries, and similitudes available in hypersonic flow and thin shock layer; appropriate for graduate-level courses in hypersonic flow theory. 1966 edition.
| Author | : Wallace Hayes |
| Publisher | : Elsevier |
| Total Pages | : 481 |
| Release | : 2012-12-02 |
| Genre | : Technology & Engineering |
| ISBN | : 032314876X |
Hypersonic Flow Theory presents the fundamentals of fluid mechanics, focusing on the hypersonic flow theory and approaches in theoretical aerodynamics. This book discusses the assumptions underlying hypersonic flow theory, unified supersonic-hypersonic similitude, two-dimensional and axisymmetric bodies, and circular cylinder. The constant-streamtube-area approximation, streamtube-continuity methods, and tangent-wedge and tangent-cone are also deliberated. This text likewise covers the similar laminar boundary layer solutions, bluntness induced interactions on slender bodies, and free molecule transfer theory. The dynamics of hypersonic flight or hypersonic wing theory, magnetohydrodynamic theory, or any developments involving treatment of the Boltzmann equation are not included. This publication is intended for hypersonic aerodynamicists, students, and researchers conducting work on the hypersonic flow phenomena.
| Author | : Wallace Dean Hayes |
| Publisher | : |
| Total Pages | : 602 |
| Release | : 1966 |
| Genre | : Aerodynamics, Hypersonic |
| ISBN | : 9780123343611 |
| Author | : P.M. Stocker |
| Publisher | : |
| Total Pages | : 19 |
| Release | : 1955 |
| Genre | : |
| ISBN | : |
| Author | : Elmer Dale Martin |
| Publisher | : |
| Total Pages | : 60 |
| Release | : 1968 |
| Genre | : Aerodynamic heating |
| ISBN | : |
| Author | : Robert McLaughlin Wright (Jr.) |
| Publisher | : |
| Total Pages | : 88 |
| Release | : 1965 |
| Genre | : Aerodynamics, Hypersonic |
| ISBN | : |
| Author | : Wallace D. Hayes |
| Publisher | : |
| Total Pages | : 602 |
| Release | : 1966 |
| Genre | : |
| ISBN | : |
| Author | : Arnold Polak |
| Publisher | : |
| Total Pages | : 48 |
| Release | : 1970 |
| Genre | : Aerodynamics, Hypersonic |
| ISBN | : |
The flow of a perfect gas over the slab portion of a blunted delta wing flying at hypersonic speeds is studied. A set of approximate equations is derived and a solution - for an inviscid flow - is obtained. Using this solution as a representation for the inviscid flow problem, a formulation to the laminar boundary-layer equations is presented; one which is applicable to the flow field's azimuthal planes where the crossflow gradients are not too large. Numerical solutions to these boundary-layer equations have been obtained; however, these are restricted to the azimuthal planes and near to the leading edges. The results indicate the presence of a dividing surface streamline since a numerical solution could not be obtained near the centerplane of the wing, where the crossflow velocity is large. (Author).
| Author | : Jean-Antoine Désidéri |
| Publisher | : Springer |
| Total Pages | : 266 |
| Release | : 1991 |
| Genre | : Science |
| ISBN | : |
| Author | : National Aeronautics and Space Administration (NASA) |
| Publisher | : Createspace Independent Publishing Platform |
| Total Pages | : 28 |
| Release | : 2018-06-30 |
| Genre | : |
| ISBN | : 9781722063351 |
An approximate solution technique was developed for 3-D inviscid, hypersonic flows. The method employs Maslen's explicit pressure equation in addition to the assumption of approximate stream surfaces in the shock layer. This approximation represents a simplification to Maslen's asymmetric method. The present method presents a tractable procedure for computing the inviscid flow over 3-D surfaces at angle of attack. The solution procedure involves iteratively changing the shock shape in the subsonic-transonic region until the correct body shape is obtained. Beyond this region, the shock surface is determined using a marching procedure. Results are presented for a spherically blunted cone, paraboloid, and elliptic cone at angle of attack. The calculated surface pressures are compared with experimental data and finite difference solutions of the Euler equations. Shock shapes and profiles of pressure are also examined. Comparisons indicate the method adequately predicts shock layer properties on blunt bodies in hypersonic flow. The speed of the calculations makes the procedure attractive for engineering design applications. Riley, Christopher J. and Dejarnette, Fred R. Langley Research Center RTOP 506-40-91-01...
