Numerical computation of hypersonic flow past a two-dimensional blunt body.

by Eva V. Swenson

Publisher: Courant Institute of Mathematical Sciences, New York University in New York

Written in English
Cover of: Numerical computation of hypersonic flow past a two-dimensional blunt body. | Eva V. Swenson
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StatementBy Eva V. Swenson.
The Physical Object
Pagination62 p.
Number of Pages62
ID Numbers
Open LibraryOL23322341M

(). Non-equilibrium flow of an ideal dissociating gas. Nonweiler, T. R. F. Aerodynamic problems of manned space vehicles. J. R. Aeronauti. Soc. 63, – (). Numerical computation of two dimensional viscous blunt body flows with an impinging shock. (). Numerical simulation of reacting flows related to the HEG.   This paper investigated the spiked blunt bodies with and without sideward jets flying at hypersonic speed, using numerical simulations. The incoming flow Mach number changed from 5 to 10, and the spike length ratio over the blunt body diameter changed from to   I am trying to do a hypersonic flow simulation over a spiked blunt body at mach 6 using fluent In my case, I use first order upwind scheme and get a very well converged solution. however, when I switch to second order upwind scheme, totally diverge Any one has some suggestion to . THE BLUNT-BODY PROBLEM IN HYPERSONIC FLOW AT LOW REYNOLDS NUMBER, [Hsien K. Cheng] on *FREE* shipping on qualifying offers. THE BLUNT-BODY PROBLEM IN HYPERSONIC FLOW AT LOW REYNOLDS NUMBERAuthor: Hsien K. Cheng.

Hypersonic flow can be approximately separated into a number of regimes. The selection of these regimes is rough, due to the blurring of the boundaries where a particular effect can be found. Perfect gas. In this regime, the gas can be regarded as an ideal gas. Flow in . T1 - Numerical study of hypersonic boundary layer transition on a blunt body. AU - Johnson, Heath B. AU - Candler, Graham V. AU - Hudsonf, Mary L. PY - /1/1. Y1 - /1/1. N2 - Highly resolved solutions of the flow over both sharp cone and blunt-nosed hypersonic bodies are found using computational fluid by: 5. Welcome to the hypersonic CFD group at IIT Bombay. We are an interesting collection of graduate and undergraduate students synergistically working together at the frontiers of research. Our primary interest is to study high-speed flows in aerospace applications. realized in the broad, stagnation region of blunt bodies where system eigenvalues are small. Nevertheless, computational aerothermo-dynamic tools that generally do a good job in handling the difficulties of steady, laminar, hypersonic, blunt body and attached flow simulation have evolved over the past 15 years. The greatest.

Hypersonic nonequilibrium flow simulations over a blunt body using bgk simulations. View/ Open. (Mb) a lot of focus has been given on research pertaining to numerical approach to understand this physics. The features of such flows are quite different from those of subsonic, transonic and supersonic ones and thus normal. *****.Excerpt from Numerical Computation of Hypersonic Flow Past a Two-Dimensional Blunt Body Given a two-dimensional blunt body in a steady supersonic flow of compressible fluid, the problem is to study the flow between the body and the detached shock wave formed in front of it.

Numerical computation of hypersonic flow past a two-dimensional blunt body. by Eva V. Swenson Download PDF EPUB FB2

[33] Kalimuthu R. and Rathakrishnan E., “ Aerospike in Drag Reduction for Hypersonic Flow,” AIAA PaperLink Google Scholar [34] Mansour K.

and Numerical computation of hypersonic flow past a two-dimensional blunt body. book M., “ The Drag Reduction in Spherical Spiked Blunt Body,” Acta Astronautica, Vol. 99, June–Julypp. 92– Crossref Google ScholarCited by: Computation of Hypersonic Flow past a Blunt Body in an Inert Binary Gas Mixture in Rotational Non-equilibrium Using the Generalized Boltzmann Equation Topics Generalized Boltzmann Equation, Non-equilibrium Hypersonic Flows, Shock Waves in Inert Gas Mixtures, Rotational and Vibrational Non-equilibrium FlowS.

The purpose of this paper is to explore the characteristics of hypersonic flow past a blunt body.,The implicit finite volume schemes are derived from axisymmetric Navier–Stokes equations by means of AUSM+ and LU-SGS methods, and programmed in FORTRAN.

Based on the verified result that a 2D axisymmetric chemical equilibrium flow has a good agreement with the literature, the Cited by: 5. Pris: kr. Inbunden, Skickas inom vardagar. Köp Numerical Computation of Hypersonic Flow Past a Two-Dimensional Blunt Body av Eva Swenson på compute two-dimensional viscous blunt body flows with an impinging shock.

Thus far, numerical difficulties have prevented the computation of Edney's Type IV shock interference patterns. However, Type III inter-actions have been successfully computed in this study.

Numerical simulations are presented of steady state, hypersonic blunt body nitrogen flow for conditions under which there is considerable thermal dissociation. Mohling, Robert Allan, "Numerical computation of the hypersonic rarefied flow past the sharp leading edge of a flat plate " ().

Retrospective Theses and Dissertations. by: 6. A time-dependent computational method for blunt body flows. Numerical computation of two-dimensional viscous blunt body flows with an impinging shock.

TANNEHIL, T. HOLST and J. RAKICH; 13th Aerospace Sciences Meeting August Method of belotserkovskii for asymmetric blunt-body flows A time dependent solution for the blunt body Cited by:   Bohachevski IO, Mates RE () A direct method for calculation of the flow about an axisymmetric blunt body at angle of attack.

AIAA J 4(5)– Google Scholar Bowcutt KG, Anderson JD, Capriotti D () Numerical optimization of conical flow. A model of supersonic flow past blunt axisymmetric bodies, with application to Chester's solution - Volume 3 Issue 5 - M. Van Dyke Please note, due to scheduled maintenance online transactions will not be possible between and BST, on Sunday 17th February ( EDT, 17th February, ).Cited by: The results of 2-D numerical simulations of hypersonic flow of a single diatomic gas, e.g., Nitrogen and a binary inert mixture of two gases (which are constituents of air namely N 2, O 2, Ar) past a 2-D blunt body in rotational non-equilibrium from low to high Knudsen Numbers are obtained using the Wang-Chang Uhlenbeck equation [1] or the Generalized Boltzmann Equation (GBE) [2].

The results of 2‐D numerical simulations of hypersonic flow of a diatomic gas, namely Nitrogen past a 2‐D blunt body at low to high Knudsen Numbers are presented.

In a previous paper AIAA –, flow field simulations in a monoatomic gas were reported by employing several computational models namely the Navier‐Stokes equations, Burnett equations, Direct Simulation Cited by: 8.

The problem of flow at zero angle of attack past blunt bodies possessing two planes of symmetry is investigated numerically for flow patterns varying from smeared layer structure to almost ideal flow (Re ∞ = 5).

The flow conditions corresponded to the motion of a body Cited by: 2. Hsue-shen Tsien, in Collected Works of H.S. Tsien (–), Hypersonic flows are flow fields where the fluid velocity is much larger than the velocity of propagation of small disturbances, the velocity of sound.

von Kármán [1] has pointed out that in many ways the dynamics of hypersonic flows is similar to Newton's corpuscular theory of aerodynamics. Numerical simulation of hypersonic flows past three-dimensional blunt bodies through a unstructured shock-fitting solver. The second was flow past a tension shell with nose injection.

These cases simulate (1) injection for nose cooling, or (2) small retrorockets. The third case to be investigated was flow past Supersonic flow past blunt bodies a sphere-cone body with injection over the entire surface.

This case simulates ablation for a high speed planetary by: 3. Numerical Simulation of Hypersonic Blunt Body and Nozzle Flows using Master Equation Prakash Vedula∗ and Eswar Josyula† ∗School of Aerospace and Mechanical Engineering, University of Oklahoma, Norman, Oklahoma, U.S.A.

† Air Force Research Laboratory, Wright-Patterson AFB, Ohio, U.S.A. Abstract. Numerical simulations of hypersonic flow past blunt body and expanding nozzles Cited by: 4. Purchase Hypersonic Flow Research - 1st Edition.

Print Book & E-Book. ISBNBook Edition: 1. Frontiers in Aerospace Engineering Volume 2 Issue 3, August Computation of Hypersonic Flow past a Blunt Body in an Inert Binary Gas Mixture in Rotational Non-equilibrium.

Creager, M. The effect of leading-edge sweep and surface inclination on the hypersonic flow field over a blunt flat plate. NASA-MEMO A. Dietz, G. & Meijering, A. Numerical investigation of boundary-layer instabilities over a blunt flat plate at angle of attack in supersonic flow. A numerical method for calculation of strong radiation for two-dimensional reactive air flow field is developed.

The governing equations are taken to be two dimensional, compressible Reynolds-average Navier-Stokes and species transport equations. Also, radiation heat flux in energy equation is evaluated using a model of discrete ordinate : Morteza Rahmanpour, Reza Ebrahimi, Mehrzad Shams.

linear model equation and to an oscillating plate problem using the two-dimensional Navier-Stokes equations. Then, the third-order EN0 scheme was used to compute the unsteady interaction of a freestream acoustic wave with a bow shock in hypersonic flow past a cylinder.

The numerical results along the stagnation line were compared. Numerical solution of hypersonic flow along the stagnation streamline of blunt body *Chang-Ho Lee 1) 1) Aerodynamics Research Team, Korea Aerospace Research Institute, DaejeonKorea.

1) [email protected] ABSTRACT. The hypersonic flow near the stagnation streamline of a blunt body File Size: KB. and hypersonic flow past a blunt body that combines the advantages of minimum computational difficulty with maximum accuracy of results.

Physically, the problem under consideration is the following. A blunt-nosed configuration is traveling through a uniform gas at a flight Mach number greater than unity. A detached shock wave forms ahead of the.

Hypersonic flow over a blunt body with a high rate of mass transfer has been studied by a number of investigators. For example, in an early investi- gation, Hoshizaki (ref. 1) made numerical calculations from the incompressible Navier-Stokes equations to determine the effects of mass transfer on the heat-File Size: 1MB.

Dissertation: Numerical Computation of Hypersonic Flow Past a Two-Dimensional Blunt Body Mathematics Subject Classification: 35—Partial differential equations Advisor: Paul Roesel Garabedian.

Flow field reconfiguration and drag reduction have been investigated by numerically solving Navier-Stokes equations, with the 2nd order dispersion controlled dissipative scheme adopted for the convective term discretion and the 2nd order central difference scheme for viscous term.

Spikes and sideward jets nearby the spike noses were set up in the front of the blunt body to reconfigure the flow Cited by: 3. Hypersonic Nonequilibrium Flow Simulation Over a Blunt Body Using BGK Method.

(December ) Sunny Jain,Indian Institute of Technology, Bombay Chair of Advisory Committee: Dr. Sharath Girimaji There has been a continuous effort to unveil the physics of hypersonic flows both. Abstract. The results of 2-D numerical simulations of hypersonic flow of a single diatomic gas, namely Nitrogen and a binary inert mixture of two gases (which are constituents of air namely N2, O2, Ar) past a 2-D blunt body in rotational nonequilibrium from low to high Knudsen Numbers are obtained using the Wang-Chang Uhlenbeck equation or the Generalized Boltzmann.

Hypersonic Flow Theory presents the fundamentals of fluid mechanics, focusing on the hypersonic flow theory and approaches in theoretical aerodynamics. This book discusses the assumptions underlying hypersonic flow theory, unified supersonic-hypersonic similitude, two-dimensional and axisymmetric bodies, and circular Edition: 1.

book Numerical Solution of Partial Differential Equations-!!, Academic E. V.: Numerical Computation of Hypersonic Flow Past a Two-Dimensional Blunt Body.

AEC Research and Development Report, Communications on Pure and Appl. Math., vol. 21, no. 2, March (6) Korn, D. G.: Computation of Hypersonic Axially Symmetric Flow at low Mach File Size: KB.The flow of an active thermal protection system exploiting subsonic counter-flow jets for wing leading edges of hypersonic vehicles is numerically studied on the basis of the three dimensional Navier-Stokes equations.

The coolant air issuing from around the stagnation point as an array of three jets spreads over both the upper and the lower sides of the cylinder surface and about 40 ~ 60%.In the present work steady inviscid hypersonic flows are calculated by approximate Method.

Maslens' inverse method is the chosen approximate method. For the inverse problem, parabolic shock shape is chosen for the two-dimensional flow, and the body shape and flow .