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Tables And Graphs Of Normal Shock Parameters At Hypersonic Mach Numbers And Selected Altitudes
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Book Synopsis Tables and Graphs of Normal-shock Parameters at Hypersonic Mach Numbers and Selected Altitudes by : Paul W. Huber
Download or read book Tables and Graphs of Normal-shock Parameters at Hypersonic Mach Numbers and Selected Altitudes written by Paul W. Huber and published by . This book was released on 1958 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt: Tables and graphs of normal-shock parameters are presented for real air in thermal and chemical equilibrium at conditions ahead of the shock corresponding to six selected altitudes, and for temperatures behind the shock from 2,000 deg K to 11,000 deg K. The altitudes used are those representing the boundaries of the isothermal layers in that part of the earth's atmosphere considered applicable to aerodynamic flight; that is, below an altitude of 300,000 feet. The altitude data and the real-air thermodynamic data used are reliable for application to this range of altitudes. Tabulated values at each altitude as a function of the temperature behind the the shock are presented to show the variation of the normal-shock parameters with flight Mach number and altitude, and some discussion of the dependence of the parameters on the initial pressure and temperature is given. A method for adapting the data to the case of oblique shocks is included.
Book Synopsis Technical Note - National Advisory Committee for Aeronautics by : United States. National Advisory Committee for Aeronautics
Download or read book Technical Note - National Advisory Committee for Aeronautics written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1958 with total page 902 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Hypersonic Shock-heated Flow Parameters for Velocities to 46,000 Feet Per Second and Altitudes to 323,000 Feet by : Paul William Huber
Download or read book Hypersonic Shock-heated Flow Parameters for Velocities to 46,000 Feet Per Second and Altitudes to 323,000 Feet written by Paul William Huber and published by . This book was released on 1963 with total page 88 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Proceedings of the NASA-University Conference on the Science and Technology of Space Exploration by :
Download or read book Proceedings of the NASA-University Conference on the Science and Technology of Space Exploration written by and published by . This book was released on 1962 with total page 544 pages. Available in PDF, EPUB and Kindle. Book excerpt: A Chinese boy's greatest wish is to be an artist but he is too poor to buy a good brush until a wizard appears and gives him one with magic powers.
Book Synopsis Monthly Catalog of United States Government Publications by :
Download or read book Monthly Catalog of United States Government Publications written by and published by . This book was released on 1961 with total page 1274 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Regime of Frozen Boundary Layers in Stagnation Region of Blunt Reentry Bodies by : Norman T. Grier
Download or read book Regime of Frozen Boundary Layers in Stagnation Region of Blunt Reentry Bodies written by Norman T. Grier and published by . This book was released on 1961 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NASA Technical Note written by and published by . This book was released on 1964 with total page 736 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Boundary-layer Similar Solutions and Correlation Equations for Laminar Heat-transfer Distribution in Equilibrium Air at Velocities Up to 41,100 Feet Per Second by : Nathaniel B. Cohen
Download or read book Boundary-layer Similar Solutions and Correlation Equations for Laminar Heat-transfer Distribution in Equilibrium Air at Velocities Up to 41,100 Feet Per Second written by Nathaniel B. Cohen and published by . This book was released on 1961 with total page 72 pages. Available in PDF, EPUB and Kindle. Book excerpt: Correlations of the transport property estimates of NASA TR R-50 are employed to determine locally similar solutions of the laminar boundary-layer equations for air in chemical equilibrium. Exact solutions for flat-plate flow, axisymmetric stagnation flow, and stagnation flow for yawed infinite cylinder are obtained, and a correlation formula for the heat-transfer distribution function for arbitrary favorable pressure gradient is determined. Extension to three-dimensional flows with small cross flow is briefly described.
Download or read book NASA Technical Report written by and published by . This book was released on 1963 with total page 722 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Nonlinear Theory for Predicting the Effects of Unsteady Laminar, Turbulent, Or Transitional Boundary Layers on the Attenuation of Shock Waves in a Shock Tube with Experimental Comparison by : Robert L. Trimpi
Download or read book A Nonlinear Theory for Predicting the Effects of Unsteady Laminar, Turbulent, Or Transitional Boundary Layers on the Attenuation of Shock Waves in a Shock Tube with Experimental Comparison written by Robert L. Trimpi and published by . This book was released on 1958 with total page 682 pages. Available in PDF, EPUB and Kindle. Book excerpt: The linearized attenuation theory of NACA Technical Note 3375 is modified in the following manner: (a) an unsteady compressible local skin-friction coefficient is employed rather than the equivalent steady-flow incompressible coefficient; (b) a nonlinear approach is used to permit application of the theory to large attenuations; and (c) transition effects are considered. Curves are presented for predicting attenuation for shock pressure ratios up to 20 and a range of shock-tube Reynolds numbers. Comparison of theory and experimental data for shock wave strengths between 1.5 and 10 over a wide range of Reynolds numbers shows good agreement with the nonlinear theory evaluated for a transition Reynolds nuniber of 2.5 million.
Book Synopsis Ideal-gas Tables for Oblique-shock Flow Parameters in Air at Mach Numbers from 1.05 to 12.0 by : John S. Dennard
Download or read book Ideal-gas Tables for Oblique-shock Flow Parameters in Air at Mach Numbers from 1.05 to 12.0 written by John S. Dennard and published by . This book was released on 1964 with total page 168 pages. Available in PDF, EPUB and Kindle. Book excerpt: Oblique-shock tables are presented for air with initial Mach numbers from 1.05 to 12.0 and flow-deflection angles from 0 degrees up to the maximum turning angle for attached flow. Parameters presented are flow-deflection angle, shock-wave angle, total-pressure ratio, static-pressure, density, and temperature ratios, downstream Mach number, ratio of downstream velocity to maximum velocity, and increase in entropy. Perfect-gas equations have been used throughout these calculations.
Book Synopsis Monthly Catalog of United States Government Publications, Cumulative Index by : United States. Superintendent of Documents
Download or read book Monthly Catalog of United States Government Publications, Cumulative Index written by United States. Superintendent of Documents and published by . This book was released on 1968 with total page 1366 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Graphical Solution of Shock Equations by : Charles E. Treanor
Download or read book A Graphical Solution of Shock Equations written by Charles E. Treanor and published by . This book was released on 1959 with total page 88 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Normal Shock Wave Parameters in Equilibrium Air by : Charles E. Wittliff
Download or read book Normal Shock Wave Parameters in Equilibrium Air written by Charles E. Wittliff and published by . This book was released on 1961 with total page 102 pages. Available in PDF, EPUB and Kindle. Book excerpt: Tables and graphs are given of normal shock wave parameters for equilibrium air. Composition of the air behind the shock is also tabulated. The results cover the range of velocities from 2000 to 26,000 fps in increments of 1000 fps and altitudes from sea level to 300,000 ft at 10,000ft intervals. The 1959 ARDC model atmosphere was used to specify ambient conditions ahead of the shock. An effective specific heat ratio, was tabulated which permits solution of oblique shock waves.
Book Synopsis Annual Report of the National Advisory Committee for Aeronautics by : United States. National Advisory Committee for Aeronautics
Download or read book Annual Report of the National Advisory Committee for Aeronautics written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1958 with total page 1516 pages. Available in PDF, EPUB and Kindle. Book excerpt: Includes the Committee's Technical reports no. 1-1058, reprinted in v. 1-37.
Book Synopsis U.S. Government Research Reports by :
Download or read book U.S. Government Research Reports written by and published by . This book was released on 1964 with total page 100 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Method of Solution with Tabulated Results for the Attached Oblique Shock-wave System for Surfaces at Various Angles of Attack, Sweep, and Dihedral in an Equilibrium Real Gas Including the Atmosphere by : Robert L. Trimpi
Download or read book A Method of Solution with Tabulated Results for the Attached Oblique Shock-wave System for Surfaces at Various Angles of Attack, Sweep, and Dihedral in an Equilibrium Real Gas Including the Atmosphere written by Robert L. Trimpi and published by . This book was released on 1960 with total page 148 pages. Available in PDF, EPUB and Kindle. Book excerpt:
