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Saturday, May 16, 2020 | History

2 edition of Hypersonic blunt body computations including real gas effects found in the catalog.

Hypersonic blunt body computations including real gas effects

Hypersonic blunt body computations including real gas effects

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  • 20 Currently reading

Published by National Aeronautics and Space Administration, Ames Research Center in Moffett Field, Calif .
Written in English

    Subjects:
  • Numerical analysis.,
  • Finite differences.

  • Edition Notes

    StatementJ.L. Montagne ... [et al.].
    SeriesNASA technical memorandum -- 100074.
    ContributionsMontagne, J. L., Ames Research Center.
    The Physical Object
    FormatMicroform
    Pagination1 v.
    ID Numbers
    Open LibraryOL14662841M

    for supersonic and hypersonic Mach numbers including both laminar and turbulent flow Reynolds numbers. Real-gas and high temperature effects are not included in the aerody-namic analysis. Approximate methods for aerodynamic heat transfer analysis, assuming gas at chemical equilibrium, have been included. Keywords: Aerodynamic heating, DSMC, hypersonic flow, rarefied flow, blunt body Introduction The successful design of high-lift, low-drag hypersonic configurations will depend on the ability to incorporate relatively sharp leading edges that combine good aerodynamic properties with acceptable heating rates.

    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. The book is devoted to hypersonics, including experimental work in shock tunnel flows with emphasis on the influence of "real gas" effects on aerodynamic phenomena encountered in hypersonics and aerospace studies.

    Full text of "NASA Technical Reports Server (NTRS) Numerical computation of space shuttle orbiter flow field" See other formats N6S -2 £92 1 (NAS A-CB- 12) N UH EBICAL CCKPUTAllON CF SPACE SHUTTLE OEfallEE FlOH FIELD Semiannual Status Be port, 1 Apr. - 30 Sep. {Iova State Oniv. of Science acd Technology) 5 p Unclac HC A 0 2/fl F ADI CSCL J 1A 63/02 . Finally, the increased temperature of hypersonic flows mean that real gas effects become important. For this reason, research in hypersonics is often referred to as aerothermodynamics, rather than aerodynamics. The introduction of real gas effects means that more variables are required to describe the full state of a gas.


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Hypersonic blunt body computations including real gas effects Download PDF EPUB FB2

The blunt body calculations at Mach numbers higher than 15 allow significant real gas effects to occur, while the case of an impinging shock provides a test on the treatment of slip surfaces and complex shock structures.

Abstract. The recently developed second-order explicit and implicit total variation diminishing (TVD) shock-capturing methods of the Harten and Yee [1,2], Yee [3,4], and van Leer [5,6] types in conjunction with a generalized Roe’s approximate Riemann solver of Vinokur [7] and the generalized flux-vector splittings of Vinokur and Montagné [8] for two-dimensional hypersonic real gas flows are Cited by: COVID Resources.

Reliable information about the coronavirus (COVID) is available from the World Health Organization (current situation, international travel).Numerous and frequently-updated resource results are available from this ’s WebJunction has pulled together information and resources to assist library staff as they consider how to handle coronavirus.

HYPERSONIC BLUNT BODY COMPUTATIONS INCLUDING REAL GAS EFFECTS () Cached. Download Links [] Save to List ; Add to Collection Montagnet and H. Yees}, title = {HYPERSONIC BLUNT BODY COMPUTATIONS INCLUDING REAL GAS EFFECTS}, year = {}} Share.

OpenURL. Abstract. CGIIPUTAIICNS 1blCZUfCXiPG REBL CIS EPEBLTS (EASA) 18 p. Special attention is given to the identification of some of the elements and parameters which can affect the convergence rate for high Mach numbers or real gases, but have negligible effect for low Mach numbers, for cases involving steady-state inviscid blunt flows.

Blunt body calculations at Mach numbers of greater than 15 are performed to treat real-gas effects, and impinging shock results are.

The objective of this paper is to investigate the applicability and shock resolution of these schemes for two-dimensional steady-state hypersonic blunt body flows.

The main contribution of this paper is to identify some of the elements and parameters which can affect the convergence rate for high Mach numbers or real gases but have negligible effect for low Mach number cases for steady-state inviscid blunt body.

Real Gas Effects in Flow over Blunt Bodies at Hypersonic Speeds. REAL-GAS HYPERSONIC BLUNT-BODY FLOWS. RUDOLPH J. SWIGART ; AIAA Journal Vol. 1, No.

11 November Shock standoff on hypersonic blunt bodies in nonequilibrium gas flows. Abstract. CGIIPUTAIICNS 1blCZUfCXiPG REBL CIS EPEBLTS (EASA) 18 p CSCL 12A ancla. Blunt body calculations at Mach numbers of greater than 15 are performed to treat real-gas effects, and impinging shock results are obtained to test the treatment of slip surfaces and complex.

Modeling of Hypersonic Non Equilibrium Flows. Authors; Authors and affiliations Park C, Yoon S., “Calculation of Real-Gas Effects on Blunt-Body Trim Angles”, AIAA Google Scholar “Hypersonic Blunt Body Computations Including Real Gas Effects”, NASA TM, Google Scholar [24] Yee H.C., “A Class of High.

Hypersonic Blunt Body Computations Including Real Gas Effects Application of finite element and remeshing technique to shock interference on a cylindrical leading edge JAMES STEWART. procedure, several computations are performed for hypersonic laminar and transitional/turbulent flows over blunt-body geometries.

The results of these computations are compared with available numerical and experimental results and the effects of real gas on the flow variables are also studied. Nonlinear Hyperbolic Equations — Theory, Computation Methods, and Applications flow through porous media and compressible fluid flow including shoclcs, real gas effects, multiphase phenomena, chemical reactions etc.

Hypersonic Blunt Body Computations Including Real Gas Effects. Pages Montagné, J.-L. (et al.). The computations are performed for a benchmark case; hypersonic axisymmetric flow with real gas effects over a blunt cone at Mach The present results for the flowfield variables and also their derivatives are compared with those of the second-order method.

Numerical investigations are carried out for understanding the real gas effects for energy deposition based drag reduction technique for hypersonic flow over a blunt body. Computations are. In this work, direct simulation Monte Carlo computations have been performed to investigate flow separation and reattachment in a low-density hypersonic flow over such a configuration.

Distinct features of leading-edge flow, limited boundary layer growth, separation, shear layer, flow structure in the recirculation region and reattachment are. HYPERSONIC GAS FLOW BOUND A BLUNT BODY, ALLOWING FOB BADIATION* V. POMIN Moscow (Received 20 November ) CONSIDERABLE attention has been paid recently to hypersonic flow round blunt bodies, and several fully developed methods are now available for analysing it in the case of an ideal or real gas.

biunt-body method 49 Real-gas effect on reference Stanton number 51 Real-gas effect on delta-wing centerline Stanton number ratios 52 Stanton number ratios on the cylindrical leading edge of a 75°-swept blunt delta wing at o - 15° 53 Turbulent extrapolation factors on a 75"-swept blunt delta wing 54 An important part of the success of the DSMC technique in analyzing high Knudsen number hypersonic flows, has been the ability to include in the technique models that are effective in simulating high temperature, real gas effects.

Such effects include mixtures of chemical species, relaxation of internal. The physical problem examined is the unsteady hypersonic viscous two-dimensional blunt body flow with an impinging shock.

A schematic of the computational domain of the flow field is shown in figure 1. The blunt body has a thickness of D and a nose radius of RI.

The circumferential angle, 8, is measured from the 'Research Scientist. with perfect gas computations indicates that at least part of this so-called hypersonic anomaly was due to real gas effects at very high Mach numbers (Maus et al.

). Finally, an example of a “known unknown” is boundary-layer transition. Vehicles that are powered by air-breathing propulsion systems spend most of their atmospheric.Depending on the cone half-angle and the inverse normal-shock density ratio $\unicode[STIX]{x1D}$, hypersonic flow over a spherically blunted cone exhibits two regimes separated by an almost discontinuous jump of the body end of the sonic line from a point on the spherical nose to the shoulder of the cone, here called sphere behaviour and cone behaviour.W.H.

Mason Hypersonic Aerodynamics 7/31/16 ( 2) where θ is the angle between the flow vector and the surface. Thus you only need to know the geometry of the body locally to estimate the local surface pressure.

Also, particles impact only the portion of the body facing the flow, as shown in Figure The rest of the body is in a.