Hypersonic And High Temperature Gas Dynamics Anderson Pdf [UPDATED] Download
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COURSE DESCRIPTIONConservation equations. Thermodynamics of ideal gases. Isentropic flows. Crocco-Vazsonyi's equation, creation and destruction of vorticity by compressibility effects. Acoustics and generation of sound by turbulence. Shock waves. Kovasznay's modal decomposition of compressible flow, linear and nonlinear modal interactions, interaction of turbulence with shock waves. Turbulent Mach number. Shocklets. Energetics of compressible turbulence, effects of compressibility on homogeneous turbulence, free-shear flows and turbulent boundary layers. Van Driest transformation, recovery temperature, and shock/boundary layer interaction. Strong Reynolds analogy. Subgrid-scale modeling for compressible turbulence.
SUPPLEMENTARY MATERIAL AUXILIARY TEXTBOOKS - E.H. Hirschel & C.W. Weiland, ''Selected Aerothermodynamic Design Problems of Hypersonic Vehicles'', Springer, 2009. (applied hypersonics) - W.G. Vincenti & C.H. Kruger, ''Introduction to Physical Gas Dynamics'', Krieger 1965. (kinetic theory of gases)- Y.B. Zel'dovich & A.S. Kompaneets, ''Theory of Detonation'', Academic Press, 1960. (detonations)- G.S. Sutton & O. Bliblarz, ''Rocket Propulsion Elements'', Wiley, 2010. (rocket nozzles)- M. van Dyke, ''Perturbation Methods in Fluid Mechanics'', Parabolic, 1975. (two-dimensional aerodynamic theory)- J.D. Anderson, ''Computational Fluid Dynamics'', McGraw-Hill, 1995. (numerical methods for compressible flows)- R.J. le Veque, ''Numerical Methods for Conservation Laws'', Birkhauser, 1992. (numerical methods for hyperbolic equations)OTHER REFERENCES: - Air Force Test Pilot School Edwards AFBCA, ''USAF Test Pilot School. Performance Phase Textbook. Volume 1" (See Ch. 6: Supersonic Aerodynamics), 1986. (PDF Download, 30MB)
The problem of spatial flow around a hypersonic flying vehicle is considered for trajectories with different attack angles for flight through air with chemical equilibrium. The conjugate problem statement gives solutions for gas state in the boundary layer, thermal regime of streamlined body (made of different composites), and the rate of mass loss for heat protecting material. Physical processes in the condensed phase of carbon-containing coatings have complex nature: processes of heating, pyrolysis, heterogeneous oxidation, and sublimation. These processes result in protective material destruction. It was shown that using different materials for passive protection can be beneficial in reduction of the surface temperature, characteristics of thermochemical degradation, and this allows a control over heat and mass transfer for a flying body.
Hypersonic flight powered by airbreathing engines offers the potential for faster response time at long ranges, and reduced cost for access-to-space. In the present paper the operating environment of typical hypersonic vehicles are discussed, including results for the radiation equilibrium wall temperature of external vehicle surfaces and the flow properties through three sample engines spanning the range of hydrocarbon-fueled Mach 4-8 flight and hydrogen-fueled flight at speeds up to Mach 17. Flow conditions at several locations through the sample engines were calculated to provide indications of the required operating flow environment. Additional system consideration such a seals, joints, vehicle integration and in-service engineering are addressed. 2b1af7f3a8