3 edition of Computational study of flow establishment in hypersonic pulse facilities found in the catalog.
Computational study of flow establishment in hypersonic pulse facilities
by National Aeronautics and Space Administration, Lewis Research Center, Institute for Computational Mechanics in Propulsion, National Technical Information Service, distributor in [Cleveland, Ohio], [Springfield, Va
Written in English
|Statement||S. Yungster, K. Radhakrishnan.|
|Series||NASA contractor report -- 198407., NASA contractor report -- NASA CR-198407.|
|The Physical Object|
Hypersonic Forward-Facing Cavity Flow Hypersonic vehicles travel at such high velocities that severe heating and shape changes due to ablation often occur. These shape changes need to be minimized as they can produce unacceptable perturbations in . Computational investigation of airflow, shock wave and nano-particle separation in supersonic and hypersonic impactors. good agreement of the present numerical results with experimental data shows that the assumption of steady axisymmetric flow used in this study is reasonable for analysis of supersonic by:
This study was undertaken in response to a request by the U.S. Air Force that the National Research Council (NRC) examine whether the technologies that underlie the concept of a hypersonic, air-launched, air-breathing, hydrocarbon-fueled missile with speeds up to Mach 81 can be demonstrated in time to be initially operational by Boundary-layer flow control is a prerequisite for a safe and efficient operation of future hypersonic transport systems. Here, the influence of an electric discharge—modeled by a heat-source term in the energy equation—on laminar boundary-layer flows over a flat plate with zero pressure gradient at Mach 3, 5, and 7 is investigated numerically. The aim was to Cited by: 3.
Hypersonic CFD lab specializes in computational research of high-speed turbulent flows, from fundamental studies to real-life applications. We use a combination of theoretical analysis, numerical codes, predictive models and computational simulations to tackle technologically relevant flow problems. title = "Advances in computational fluid dynamics methods for hypersonic flows", abstract = "Over the past two decades or so, there have been many advances in the numerical simulation of hypersonic flows, with most effort focused on the development of upwind methods to produce accurate heat transfer rates for steady-state laminar and turbulent Cited by:
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Computational Study of Flow Establishment in Hypersonic Pulse Facilities S. Yungster Institutefor Computational Mechanics in Propulsion Cleveland, Ohio K. Radhakrishnan NYMA,Inc. Brook Park, Ohio November Prepared for Lewis Research Center Under Cooperative Agreement NCC National Aeronautics and Space Administration.
Get this from a library. Computational study of flow establishment in hypersonic pulse facilities. [Shaye Yungster; Krishnan Radhakrishnan]. Carry out a tip-to-tail computation of the flow field of a generic hypersonic vehicle in the power-on configuration. The main focus of the task was to establish and demonstrate a solution procedure/strategy that would be useful for solving the entire flow field associated with an airbreathing hypersonic Size: 2MB.
Computational studies have been carried out to obtain the flow field around a hemispherical body with spikes at a hypersonic Mach number of 6. The effect of. Reinartz and Behr () worked on "Computational Design Study of 3D Hypersonic Intake for Scramjet Demonstrator Testing" and it has been observed.
Computational study of flow establishment in hypersonic pulse facilities [microform] / S. Yungster, K. R Application of chimera grid scheme to combustor flowfields at all speeds [microform] / Shaye Yungster, K Computational study of flow establishment in a ram accelerator [microform] / S.
Yungster, K. Radhakrishn. As shown in Table a and Table b, hypersonic ground test facilities have been examined as part of several major studies during the last few years, and the conclusions of these studies are generally agree on the following points: More-capable hypersonic ground test facilities are needed to adequately support future development programs.
Internal Flow and Porous Media For the internal flow and the heat conduction of the porous media, the present author used the 2nd order central difference to evaluate the partial derivative, and introduced the relaxation parameter to suppress the numerical instability. Computational Grid In the computational grid for the external flow.
Peer-review under responsibility of the organizing committee of RAEREST doi: / Global Colloquium in Recent Advancement and Effectual Researches in Engineering, Science and Technology (RAEREST ) Computational study of hypersonic flow past spiked blunt body using RANS and DSMC method Jiss J Sebastiana, Cited by: 4.
A modern treatment of hypersonic aerothermodynamics for students, engineers, scientists, and program managers involved in the study and application of hypersonic flight. It assumes an understanding of the basic principles of fluid mechanics, thermodynamics, compressible flow, and heat transfer.
Ten chapters address: general characterization of hypersonic flows; basic 3/5(1). 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 this regime is still Mach number dependent. International Journal of Mechanical Engineering and Technology (IJMET), ISSN – (Print), ISSN – (Online) Volume 4, Issue 3, May - June ( Recent considerable progress in the field of rarefied hypersonic computational fluid dynamics (CFD) gives reason to address its evolution to an independent CFD branch that covers many fundamental and closely related applied problems of high-altitude aerothermodynamics of space vehicles.
The primary purpose of this review is to describe the main numerical methods and Cited by: EXPERIMENTAL AND COMPUTATIONAL INVESTIGATION OF AN ELECTRIC ARC AIR-SPIKE IN HYPERSONIC FLOW WITH DRAG MEASUREMENTS R.M. Bracken*, L.N.
Myrabo f, H.T. Nagamatsu*, E.D. Meloney§ Department of Mechanical Engineering, Aeronautical Engineering, and Mechanics Rensselaer Polytechnic Institute Troy, New York and M.
N, Shneider1. Hypersonic and High Temperature Gas Dynamics by John D. Anderson to the AIAA Education Series. I have known John Anderson for more years than either he or I are comfortable recalling, and I have always found him to be extre-mely articulate and insightful.
The original edition published by McGraw-Hill in. Numerical Study of Rarefied Hypersonic Flow Interacting with a Continuum Jet [Glass, Christopher E., National Aeronautics and Space Administr] on *FREE* shipping on qualifying offers.
Numerical Study of Rarefied Hypersonic Flow Interacting with a Continuum JetAuthor: Christopher E. Glass. The Hypersonic Facilities Complex, originally named the Gas Dynamics Laboratory, was the NACA’s earliest installation with multiple hypersonic wind tunnels.
The various tunnels utilized air and, later, specific gasses, particularly helium and nitrogen, to investigate aerodynamic and aerothermodynamic problems in flight regimes above the speed Center: Langley Research Center.
For a given free stream Mach number M, obtain the stagnation pressure coefficient in terms of the limit of the stagnation pressure coefficient for M approaching infinity. Use the point at the surface and the first point Δn away from the surface, obtain Eq. from Eq. which gives the pressure caused by the curvature (take R = −1/(dθ/ds)).
Introduction to Hypersonic Flow has been made available to the English speaking reader because of its usefulness for those individuals desirous of obtaining an introduction to the subject.
Written by an internationally acknowledged expert in the field of hypersonic flow, the book makes available heretofore unpublished Soviet work, as well as Book Edition: 1. enced with intermittent hypersonic facilities. This study is concerned with the establishment times of these high-speed hypersonic facilities, particularly in relation to shock-wave boundary-layer interactions (SWBLIs).
In continuous (long duration) facilities, the freestream test-ﬂow is established and runs for many characteristic ﬂow. The computational grid employed in this study consists of cells along the body by cells normal to the body. The translational temperature at t = msec is shown in Fig.
6. Fig. 6. Translational temperature for the ° sharp double cone flow The comparisons of computational and experimental results are demonstrated in Figs. 7 and 8.In the modern years space vehicle like rockets, reentry vehicles irrespective their unique designs needed control surfaces at hypersonic speeds.
This paper explores the problem of determining the aerodynamics of cone and its effects on drag, model geometry, reentry heating, and type of flow, inlet temperature, aerodynamic heating and thermal protection : N S Harshavardhana, K Sanjana, K Sai Sharan, G Srinivas. Purchase Hypersonic Flow Research - 1st Edition.
Print Book & E-Book. ISBNBook Edition: 1.