Author: Harold Mirels
Publisher:
Published: 1959
Total Pages: 32
ISBN-13:
DOWNLOAD EBOOK →Approximate analytical solutions are presented for two-dimensional and axisymmetric hypersonic flow over slender power law bodies. Both zero-order (M->∞) and first-order (small but nonvanishing values of 1/(Mδ)2) solutions are presented, where M is free-stream Mach number and δ is a characteristic slope. These solutions are compared with exact numerical integrations of the equations of motion and appear to be accurate particularly when the shock is relatively close to the body.
Author: United States. Superintendent of Documents
Publisher:
Published: 1960
Total Pages: 1812
ISBN-13:
DOWNLOAD EBOOK →Author: Wallace D. Hayes
Publisher: Courier Corporation
Published: 2012-07-13
Total Pages: 628
ISBN-13: 0486160483
DOWNLOAD EBOOK →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: Louis A. Girifalco
Publisher:
Published: 1959
Total Pages: 1082
ISBN-13:
DOWNLOAD EBOOK →A general theory of solid-state diffusion in strained systems is developed on a molecular-kinetic basis. The theory predicts that for simple strains the diffusion coefficient is an exponential function of the lattice parameter and that the rate of change of the diffusion coefficient with strain is linearly related to the interatomic forces. It has also been shown that for plastic flow the diffusion coefficient is a linear function of strain rate. All the conclusions are confirmed by the data available in the literature.
Author: Harold Mirels
Publisher:
Published: 1962
Total Pages: 108
ISBN-13:
DOWNLOAD EBOOK →Self-similar flows with volumetric mass, momentum, and energy addition are investigated. Unsteady flows bounded by shock waves and equivalent steady hypersonic flows over slender bodies are considered, and the form of the shock shape and of the volumetric sources for self-similar motion are noted. For unsteady flows, it is found that the shock shape mu t have the form R sub O=ct to the m power (where R sub O = shock ordinate, t = time) and that the mass, momentum, and energ sources must be expressible in the fom of a funtion of r/R sub O times t to the -1 power, t to the m-2 power, and t to the 2m-3 power, respectively (where r is the lateral ordinate). If the sources introduce only sll perturbations in an otherwise self-similar flow, solutions can be obtained for sources expressible as a function of r/R sub O times t to arbitrary constant exponents. Thus, the small perturbation case is less restrictive with regard to the functional form of the sources. For equivalent steady hypersonic flows, the streamwise distance, x, replaces t in the above expressions. Numerical perturbation solutions are obtained for the effect of a uniform transverse magnetic field on piston-driven flows and blast waves. The firstorder effect of body-thickness raio on the hypersonic flow (in the limit of infinite Mach number) over slender power law bodies is aso reated. (Author).