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Thursday, April 23, 2020 | History

2 edition of supersonic three-dimensional code for flow over blunt bodies found in the catalog.

supersonic three-dimensional code for flow over blunt bodies

D. S. Chaussee

supersonic three-dimensional code for flow over blunt bodies

program documentation and test cases

by D. S. Chaussee

  • 49 Want to read
  • 36 Currently reading

Published by National Aeronautics and Space Administration, Scientific and Technical Information Office, For sale by National Technical Information Service] in Washington, D.C, [Springfield, Va .
Written in English

    Subjects:
  • Aerodynamics -- Automation.

  • Edition Notes

    StatementD.S. Chaussee and O.J. McMillan ; prepared for Langley Research Center under contract NAS1-15305.
    SeriesNASA contractor report -- 3224., NASA contractor report -- NASA CR-3224.
    ContributionsMcMillan, Oden J., United States. National Aeronautics and Space Administration. Scientific and Technical Information Office., Langley Research Center.
    The Physical Object
    Paginationiii, 203 p. :
    Number of Pages203
    ID Numbers
    Open LibraryOL18021074M

    Thesis Title: "Supersonic Flow and its Control Over Highly Three-Dimensional Cavities" Charney Davy, M.S. Thesis Title: "Surface Flow Measurement of Supersonic Impinging Jets" Currently a Sr. Engineer at Becton, Dickinson, and Company Vikram Siddavaram, M.S. Thesis Title: "The Effect of Microjet Injection of the Flow Characterstics of. The paper includes the three dimensional analysis of viscous flow over a sharp-edged rectangular delta wing. The analysis was conducted at Mach no of with . a three-dimensional wave produced by overlapping spheres that form a cone. the speed of the source equals the wave speed. sonic boom. the sharp crack heard when the shock wave that sweeps behind a supersonic aircraft that reaches the listener. Honor Code. Community Guidelines. Students. Teachers. About. Company. Press. Careers. Advertise. They USE shock waves for chemical kinetics studies, for materials studies, and smashing kidney stones; they STUDY the phenomena associated with flows involving shock waves, such as supersonic flow, explosions, detonations, volcanic eruptions, and, in this symposium, even such with-it topics as impact of Shoemaker-Levy on Jupiter and blast waves.

    Publications: 1. THREE-DIMENSIONAL STRUCTURE AND EQUIVALENCE RULE OF TRANSONIC FLOWS, H. K. Cheng and M. M. Hafez, AIAA Journal, 2. EQUIVALENCE RULE AND TRANSONIC FLOWS INVOLVING LIFT, H. K. Cheng and M. M. Hafez, AIAA Paper , 11th AIAA Science Meeting, January , Washington, DC. 3. EQUIVALENCE .


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supersonic three-dimensional code for flow over blunt bodies by D. S. Chaussee Download PDF EPUB FB2

Get this from a library. A supersonic, three-dimensional code for flow over blunt bodies: user's manual. [D S Chaussee; Oden J McMillan; United States. National Aeronautics and Space Administration. Scientific and Supersonic three-dimensional code for flow over blunt bodies book Information Office.; Langley Research Center.].

Supersonic three-dimensional code for flow over blunt bodies. Washington, D.C.: National Aeronautics and Space Administration, Scientific and Technical Information Office ; [Springfield, Va.: For sale by National Technical Information Service], (OCoLC) Material Type: Government publication, National government publication.

A. Antonets, “Calculation of three-dimensional supersonic flow over blunt bodies with bends in the generating lines with allowance for the equilibrium and frozen-in state of the gas in the shock layer,” Izv.

Akad. Nauk SSSR, Mekh. Zhidk. Gaza, No. 2 ().Cited by: 1. In three-dimensional flow round bodies with a spherical nose, axial symmetry is sometimes retained in the subsonic region, though well down in the flow the Zh.

vychisl. Mat. mat. Fix. 8, 3,Three-dimensional supersonic gas flow problem is definitely by: 2. Supersonic Flow over Blunt Body with a Decelerator. For a supersonic speed, a flow around blunt body is complicated due to the detached shock wave, flow separation, boundary layer and their.

An algorithm is devised for calculating by the finite difference method the supersonic flow region for three-dimensional steady-state flow of a viscous gas past a blunted body with many contour discontinuities.

The state of this gas at high hypersonic flight speeds can be characterized by equilibrium or frozen physicochemical processes. Generally speaking, any arbitrary number and sequence of Author: A. Antonets. results only for the flow over slender bodies flying at low supersonic Mach numbers and small angles of attack, while Newtonian theory yields useful results only for large Mach numbers.

Neither of these theories can yield all the details of the flow even over their particular range of by: 6. A supersonic, three-dimensional code for flow over blunt bodies: user's manual / (Washington, D.C.: National Aeronautics and Space Administration, Scientific and.

@article{osti_, title = {Three-Dimensional Inviscid Flow About Supersonic Blunt Cones at Angle of Attack - I: Numerical Technique for the Three-Dimensional Blunt-Body Problem}, author = {Moretti, G and Bleich, G}, abstractNote = {The three-dimensional flow field around blunted bodies traveling at supersonic speed is computed using a time-dependent technique.

Time-Split Finite-Volume Method for Three-Dimensional Blunt-Body Flow. A three-dimensional Navier-Stokes/Euler code for blunt-body flow computations.

LI; A contribution to the computation of transonic supersonic flows over blunt bodies. Computers & Fluids, Vol. 9, No. by: 3. Shock wave and ignition boundary for combustion in supersonic flow about cone at zero angle of attack.

FLOWS ABOUT CONICAL BODIES this scheme include iterations and interpolations. This scheme is valid, naturally, both in the particular case of axisymmetric flow and in the general case of three- dimensional flow about nonconical : P.I Chushkin.

@article{osti_, title = {Three-Dimensional Inviscid Flow About Supersonic Blunt Cones at Angle of Attack - III: Coupled Subsonic and Supersonic Programs for Inviscid Three-Dimensional Flow}, author = {Abbett, M. and Fort, R.}, abstractNote = {The three-dimensional ideal gas flow in the shock layer of a blunted supersonic cone at an angle of attack is calculated using two asymptotic.

A supersonic dusty gas flow over a blunt body is considered. The mathematical model of the two-phase gas–particle flow takes into account the inter-particle collisions and the two-way coupling.

Three-dimensional supersonic flow over a spike-nosed body of revolution. experimentally investigated the effects of spike-nosed blunt bodies on heat flux and pressure drag for a Mach number of and a wide range of Reynolds numbers. In this work it was assessed the effects of varying spike length on pressure drag and heat transfer, which.

In physics, a shock wave (also spelled shockwave), or shock, is a type of propagating disturbance that moves faster than the local speed of sound in the medium. Like an ordinary wave, a shock wave carries energy and can propagate through a medium but is characterized by an abrupt, nearly discontinuous, change in pressure, temperature, and density of the medium.

A Pressure Formula for an Inclined Circular Cone in Supersonic Flow, gamma =AIAA Journal, Februarypp Kaufman, L.G., II: Pressure Estimation Techniques for Hypersonic Flows Over Blunt Bodies, Journal of Astronautical Sciences, Volume X, No. 2, Summer A numerical study of novel drag reduction techniques for blunt bodies in hypersonic flows This then requires full three-dimensional simulations of the flow-fields (i.e.

no A numerical study of novel drag reduction techniques for blunt bodies in hypersonic flows. AeroCFD is a "true" three-dimensional axisymmetric and two-dimensional implicit finite volume CFD program that solves the inviscid Euler equations for subsonic, transonic and supersonic flow using automatic mesh generation and graphical results visualization.

AeroCFD provides a maximum of cells in the axial direction, 50 cells in the transverse direction and 10 cells in the circumferential. Mitchell and McCall [], calculated the supersonic flow over blunt bodies using the stream function/vorticity formulation where the shock wave was assumed known from experimental measurements.

A serious problem was the breakdown of the. On Lifting Bodies which Two-Dimensional Supersonic By L. TOWNEND Flows BY THE DEPUTY CONTROLLER AIRCRAFT (RESEARCH AND DEVELOPMENT) MINISTRY OF AVIATION Reports and Memoranda No.

" August, ±[email protected] ~mmafy., This paper is primarily concerned with the design principles of three-dimensional surfaces which can. blunt heating viscous shock supersonic calculations solutions navier radiative heat separation equilibrium stokes Whether you've loved the book or not, if you give your honest and detailed thoughts then people will find new books that are right for them.

Iterative solution of transonic flows over airfoils and wings, including flows at mach 1. Antony Jameson. Search for more papers by this author Computation of nonlinear supersonic potential flow over three-dimensional surfaces, Journal of A contribution to the computation of transonic supersonic flows over blunt bodies, Computers Cited by:   9 Linearized Flow.

10 Conical Flow. 11 Numerical Techniques for Steady Supersonic Flow. 12 The Time-Marching Technique: With Application to Supersonic Blunt Bodies and Nozzles. 13 Three-Dimensional Flow. 14 Transonic Flow. 15 Hypersonic Flow. 16 Properties of High-Temperature Gases.

17 High-Temperature Flows: Basic Examples Appendix A5/5(1). Download Full Modern Compressible Flow With Historical Perspective Book in PDF, EPUB, Mobi and All Ebook Format.

With Application to Supersonic Blunt Bodies and Nozzles 13 Three-Dimensional Flow 14 Transonic Flow 15 Hypersonic Flow 16 Properties of High-Temperature Gases 17 High-Temperature Flows: Basic Examples Appendix A Appendix B An.

Investigation of three types of supersonic diffuser over a range of Mach numbers from to / (Washington, D.C.: National Advisory Committee for Aeronautics, []), by L. Eugene Baughman, Larence I. Gould, United States. National Advisory Committee for Aeronautics. This book is organized into two parts encompassing nine chapters that highlight the re-entry vehicle design information and re-entry thermal protection and materials.

Part I deals first with a parametric study on the effects of initial conditions and various mass and aerodynamic parameters on the dynamic motion of a typical re-entry vehicle. American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA Rakich, John V.; Bailey, Harry E.; and Park, Chul: Computation of Nonequilibrium Three-Dimensional Inviscid Flow Over Blunt- Nosed Bodies Flying at Supersonic Speeds.

AIAA. Anderson, K. and Knight, D., ``Aerothermodynamic Streamlining of a Blunt Body in Supersonic Flow by Pulsed Energy Deposition'', Workshop on Thermochemical Processes in Plasma Aerodynamics, Leninetz Holding Company, St.

Petersburg, Russia, July Full text of "An experimental investigation of hypersonic flow over blunt nosed cones at a Mach number of See other formats EXPERIMENTAL INVESTIGATION OF HYPERSONIC FLOW OVER BLUNT NOSED CONES AT A MACH NUMBER OF * William T.

O'Bryant ' Library U. Naval Postgraduate School Monterey, California j FIX> CH NT Thesis oy iliam. ryant Coiir^ander, Uivy In Partial. To investigate a jet from a blunt body opposing a supersonic flow, the three-dimensional Favre-filtered compressible Navier–Stokes equations in generalized coordinates are employed.

The equation of state for an ideal gas is used and the molecular viscosity is assumed to obey the Sutherland law. To non-dimensionalize the. Download Book Modern Compressible Flow With Historical Perspective in PDF format.

Velocity Potential Equation 9 Linearized Flow 10 Conical Flow 11 Numerical Techniques for Steady Supersonic Flow 12 The Time-Marching Technique: With Application to Supersonic Blunt Bodies and Nozzles 13 Three-Dimensional Flow 14 Transonic Flow 15 Hypersonic. A modified majorant frequency scheme of the Direct Simulation Monte Carlo (DSMC) method is proposed for computations of flow fields of a collisional “gas” of particles.

The developed combined CFD / DSMC method is applied to the study of the supersonic gas-particle flow over a blunt by: 6. You can write a book review and share your experiences. Other readers will always be interested in your opinion of the books you've read.

Whether you've loved the book or not, if you give your honest and detailed thoughts then people will find new books that are right for them. The drag coefficient is defined as = where: is the drag force, which is by definition the force component in the direction of the flow velocity, is the mass density of the fluid, is the flow speed of the object relative to the fluid, is the reference area.

The reference area depends on what type of. On the Structure and Stability of Three-Dimensional Laminar Separation Bubbles on a Swept Plate.- Receptivity Study of the Attachment-Line Instability on a Blunt Body in Supersonic Flow.- Numerical Investigation of the Flow in the Vicinity of an Isolated 3D Surface Roughness.- Separation Control in Diffuser Flow Using Periodic Excitation.-Author: Christian Breitsamter.

In this paper we describe a new approximate Riemann solver for compressible gas flow. In contrast to previous Riemann solvers, where a numerical approximation for the pressure and the velocity at the contact discontinuity is computed, we derive a numerical approximation for the largest and smallest signal velocity in the Riemann problem.

Having obtained the numerical signal velocities, we use Cited by: contmction ratiofor thisMach nmiber is givingan over-all contractionratio for the diffuserof and a pressurerewvery of percentwhen the shockoccurs at the throatMach numberof These* inletshave the samemass flow and entrancearea,but the unsymmetricone has about 10 percenthigher theoreticalpressurerecovery.

Proceedings of the Eighth GAMM-Conference on Numerical Methods in Fluid Mechanics Numerical Simulation of Laminar Hypersonic flow Past Blunt Bodies Including High Temperature Effects.

Pages Brenner, G. (et al.) Proceedings of the Eighth GAMM-Conference on Numerical Methods in Fluid Mechanics : Vieweg+Teubner Verlag. A flow field is best characterized by its velocity distribution, and thus a flow is said to be one- two- or three-dimensional if the flow velocity varies in one, two, or three primary dimensions.

The Finite Element Method for Fluid Dynamics offers a complete introduction the application of the finite element method to fluid mechanics. The book begins with a useful summary of all relevant partial differential equations before moving on to discuss convection stabilization procedures, steady and transient state equations, and numerical solution of fluid dynamic equations.Hypersonic high-enthalpy flow over a blunt-stepped cone.

A study of three-dimensional supersonic mixing flow phenomena induced by ramp injectors. Interaction of a turbulent shear flow with a Mach normal shock wave. Waves, General.

Converging shock waves: modeling and analysis of structures.Three-Dimensional Flow around Blunt Bodies. Gino Moretti Dual-Code Thin-Layer Parabolized Navier-Stokes Strategy for Supersonic Flows over Spinning Bodies.

Abouali, O. / Alishahi, M.M print version. Dual-Code Thin-Layer Parabolized NavierStokes Strategy for Supersonic Flows over Spinning Bodies. Omid Abouali /.