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A Time Dependent Method For Calculating Supersonic Blunt Body Flow Fields With Sharp Corners And Embedded Shock Waves Book in PDF, ePub and Kindle version is available to download in english. Read online anytime anywhere directly from your device. Click on the download button below to get a free pdf file of A Time Dependent Method For Calculating Supersonic Blunt Body Flow Fields With Sharp Corners And Embedded Shock Waves book. This book definitely worth reading, it is an incredibly well-written.
Author : Richard W. Barnwell
Publisher : Unknown
Page : 76 pages
File Size : 43,7 Mb
Release : 1970
Category : Blunt bodies
ISBN : UIUC:30112106881235
Author : Richard W. Barnwell
Publisher : Unknown
Page : 84 pages
File Size : 53,5 Mb
Release : 1971
Category : Finite differences
ISBN : UIUC:30112106881557
A time-dependent numerical method for calculating supersonic flow about blunt bodies at large angles of attack is presented. The axisymmetric bodies with sharp shoulders which are treated are constructed with a generator composed of segments of constant curvature. The nonaxisymmetric bodies have continuous slope and curvature. All flow fields are inviscid and adiabatic and have one plane of symmetry. A modification to the method of characteristics is introduced for use at the shock wave. A two-step finite-difference method of second-order accuracy is used at the body surface and in the region between the shock and body. A new finite-difference technique is introduced for use at sharp sonic shoulders. Comparisons of the results of the present method with experiment and the results of other methods are made for the flow of equilibrium air past the Apollo command module at the trim angle of attack and for perfect gas flow past a spherical cap and a spherically blunted cone at angle of attack. Both the cap and the blunted cone are terminated with sharp shoulders. Results are presented also for perfect gas flow past a prolate spheroid with its major axis normal to the flow.
Author : Anonim
Publisher : Unknown
Page : 438 pages
File Size : 40,9 Mb
Release : 1975
Category : Electronic
ISBN : MINN:319510008465504
Author : Anonim
Publisher : Unknown
Page : 268 pages
File Size : 52,7 Mb
Release : 1983
Category : Astronautics
ISBN : MINN:31951000586536V
Author : United States. Superintendent of Documents
Publisher : Unknown
Page : 1292 pages
File Size : 54,5 Mb
Release : 1971
Category : Government publications
ISBN : UCAL:B2968745
February issue includes Appendix entitled Directory of United States Government periodicals and subscription publications; September issue includes List of depository libraries; June and December issues include semiannual index.
Author : Anonim
Publisher : Unknown
Page : 1388 pages
File Size : 53,7 Mb
Release : 2024-06-06
Category : Government publications
ISBN : WISC:89117116475
Author : United States. Superintendent of Documents
Publisher : Unknown
Page : 1408 pages
File Size : 53,5 Mb
Release : 1976
Category : United States
ISBN : STANFORD:36105021034173
Author : Anonim
Publisher : Unknown
Page : 758 pages
File Size : 52,7 Mb
Release : 1970
Category : Aerodynamics
ISBN : NASA:31769000654080
Author : Robert M. Bennett
Publisher : Unknown
Page : 68 pages
File Size : 53,7 Mb
Release : 1972
Category : Aerodynamics, Supersonic
ISBN : UIUC:30112106882845
The method of integral relations is applied in a one-strip approximation to the perturbation equations governing small motions of an inclined, sharp-edged, flat surface about the mean supersonic steady flow. Algebraic expressions for low reduced-frequency aerodynamics are obtained and a set of ordinary differential equations are obtained for general oscillatory motion. Results are presented for low reduced-frequency aerodynamics and for the variation of the unsteady forces with frequency. The method gives accurate results for the aerodynamic forces at low reduced frequency which are in good agreement with available experimental data. However, for cases in which the aerodynamic forces vary rapidly with frequency, the results are qualitatively correct, but of limited accuracy. Calculations indicate that for a range of inclination angles near shock detachment such that the flow in the shock layer is low supersonic, the aerodynamic forces vary rapidly both with inclination angle and with reduced frequency.
Author : Anonim
Publisher : Unknown
Page : 1280 pages
File Size : 40,7 Mb
Release : 1980
Category : Aeronautics
ISBN : UIUC:30112104412421
Author : Anonim
Publisher : Unknown
Page : 776 pages
File Size : 44,5 Mb
Release : 1971
Category : Mechanics, Applied
ISBN : UCAL:C2682433
Author : Anonim
Publisher : Unknown
Page : 264 pages
File Size : 53,7 Mb
Release : 1981
Category : Aeronautics
ISBN : MINN:31951000845315J
Author : Gloria R. Champine
Publisher : Unknown
Page : 134 pages
File Size : 47,8 Mb
Release : 1977
Category : Aeronautics
ISBN : NASA:31769000536642
Author : Thomas Darwin Taylor
Publisher : Unknown
Page : 56 pages
File Size : 49,6 Mb
Release : 1974
Category : Aerodynamics
ISBN : MINN:31951000534822Y
The methods available for numerical computation of subsonic, transonic and supersonic flows are discussed and comments are included on the characteristics of the popular methods. Both inviscid and viscous computation methods are addressed. A brief account of the basic approaches for developing methods initiates the discussion. Also included is a general summary of the state of the art of computational methods along with suggested approaches for solving problems in each area. The report is included with recommendations for future study and development. (Author).
Author : John David Anderson (Jr.),Lorenzo M. Albacete,Allen Edward Winkelmann
Publisher : Unknown
Page : 78 pages
File Size : 40,8 Mb
Release : 1968
Category : Aerodynamics, Hypersonic
ISBN : UOM:39015095150325
New results are presented for inviscid, supersonic and hypersonic blunt-body flow fields obtained with a numerical time-dependent method patterned after that of Moretti and Abbett. In addition, important comments are made with regard to the physical and numerical nature of the method. Specifically, numerical results are presented for two-dimensional and axisymmetric parabolic and cubic blunt bodies as well as blunted wedges and cones; these results are presented for zero degrees angle of attack and for a calorically perfect gas with gamma = 1.4. The numerical results are compared with other existing theoretical and experimental data. Also, the effects of initial conditions and boundary conditions are systematically examined with regard to the convergence of the time-dependent numerical solutions, and the point is made that the initial conditions can not be completely arbitrary. Finally, in order to learn more about the performance of the time-dependent method, a numerical experiment is conducted to examine the unsteady propagation and region of influence of a slight pressure disturbance introduced at a point on the surface of a blunt body.