3 edition of Review of blunt body wake flows at hypersonic low density conditions found in the catalog.
Review of blunt body wake flows at hypersonic low density conditions
by American Institute of Aeronautics and Astronautics, [National Aeronautics and Space Administration, National Technical Information Service, distributor in Washington, D.C, Springfield, Va
Written in English
|Statement||J.N. Moss and J.M. Price.|
|Series||NASA-TM -- 111599., NASA technical memorandum -- 111599.|
|Contributions||Price, J. M., United States. National Aeronautics and Space Administration.|
|The Physical Object|
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. A new chemical model in the direct simulation Monte Carlo (DSMC) algorithm, entitled modified collision energy (MCE), has been developed for simulation of reactive rarefied flows.
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 equations of motion 3/5(1). A Blunt Body in a Supersonic Stream. Annual Review of Fluid Mechanics Boundary-Layer Stability and Transition E Reshotko Annual Review of Fluid Mechanics Computation of Flows with Shocks G Moretti Annual Review of Fluid Mechanics Turbulent Flows Involving Chemical Reactions P .
drag and heat transfer reduction depend on the flow conditions, blunt body shape, and spike geometry. In addition, the drag of the hypersonic body with aerospike can be reduced from 20 to 60 percent . There are many studies as to the investigation of the reduction of drag and heat transfer in the blunt bodies, Crawford  measured the drag and. A critical summary of studies in the fluid mechanics of hypersonic wakes formed behind vehicles of different geometries. The Memorandum reviews both the history and the special problems of the field, and gives special attention to such issues as the laminar regime, transition to turbulence, and turbulence.
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Get this from a library. Review of blunt body wake flows at hypersonic low density conditions. [James N Moss; Joseph M Price; United States. National Aeronautics and Space Administration,]. Get this from a library. Review of blunt body wake flows at hypersonic low density conditions. [J N Moss; Joseph M Price; United States.
National Aeronautics and Space Administration.]. A Review of Aerothermal Modeling for Mars Entry Missions. Zonally-decoupled DSMC solutions of hypersonic blunt body wake flows. JAMES MOSS and VIRENDRA DOGRA; 28th Thermophysics Conference August Review of blunt body wake flows at hypersonic low density by: Viscous, Radiating Hypersonic Flow About a Blunt Body Richard S.
Passamaneck (c4A -C 8., 7) SC UFLOW S72 WABOUT A BLUT BISCOS y (Jet p iic $ CSCL 20D Unclas G3/12 JET PROPULSION LABORATORY CALIFORNIA INSTITUTE OF TECHNOLOGY PASADENA, CALIFORNIA May 1, JP'File Size: 1MB.
The rarefied near wake flows behind a 10 degree slender cone and a 70 degree blunt body are modeled by the direct simulation Monte Carlo method, and the numerical results are validated by experimental data measured along the axial and radial directions, by: 3. 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  has pointed out that in many ways the dynamics of hypersonic flows is similar to Newton's corpuscular theory of aerodynamics. Hypersonic Blunt-Body Flow of u Radiutin us ut Densit 1. Introduction In the past 10 years, there has been much interest in low-density1 hypersonic flow in theoretical and experi- mental research.
Some of the problems in low-density hypersonic flow are shown in Fig. 1 which depicts various. T1 - Comparison of high-altitude hypersonic wake flows of slender and blunt bodies. AU - Zhong, Jiaqiang. AU - Ozawa, Takashi.
AU - Levin, Deborah A. PY - /1/1. Y1 - /1/1. N2 - The gas dynamic features of the laminar, near-wake flow behind slender and blunt hypersonic vehicles are studied using the direct simulation Monte Carlo method. The first is the study conducted by Lin et al.,"Hypersonic Reentry Vehicle Wake Flow Fields at Angle of Attack" .
Lin et al., compiled much data regarding the base pressure from. American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA Low density effects; Independence of aerodynamic coefficients with Mach number. Small shock stand-off distance.
As a body's Mach number increases, the density behind a bow shock generated by the body also increases, which corresponds to a decrease in volume behind the shock due to conservation of mass. Consequently, the distance between the bow.
A new theoretical framework, based on the analysis of Navier–Stokes solutions for the hypersonic laminar near wake of two-dimensional and axisymmetric blunt bodies, is presented.
A semi-empirical relationship is derived between the free-stream Mach and Reynolds numbers and a characteristic wake Reynolds number. In low density flows, air can no longer be considered to be a continuum because the distance between individual particles of air becomes so great that each particle begins to affect the aerodynamic properties of a body.
Under these conditions, common aerodynamic relations, like the Euler and Navier-Stokes equations, break down. Laws of similitude of hypersonic flows of monatomic gases have been obtained earlier from asymptotic analysis of the equations as S → ∞ and confirmed by experimental data and numerical results , For diatomic gases, dimensionless numbers have not been deduced by analyzing the equations but by general arguments based on analogy with monatomic gases; they were used to compare experimental.
Where, P is the normal pressure of the blunt body. P∞, T∞ and ρ∞ are gas pressure, temperature and density of free stream respectively. DSMC and CFD Methods Direct Simulation Monte Carlo is a simulation technique for low density hypersonic and supersonic gas flows.
In this method is considered the gas is as rare gas also. Using a related technique described here as hypersonic shadowing - in which a large blunt body is embedded in the wake of one or more very small upstream bodies - overall drag potentially. 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. This book discusses the low Reynolds number effects, chemical kinetics effects, inviscid flow calculations, and experimental techniques relating to the problems in acquiring an understanding of hypersonic flow.
The structure and composition of hypersonic wakes with attendant complex chemical kinetic effects is only briefly mentioned. 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.
Under conditions of high speed and gas rarefaction the character of the wake behind a body changes significantly from its behavior at normal densities. Experimental studies at M ≃ 6 and 8 with spheres and cylinders have clearly established the transition from the shock‐expansion‐neck‐recompression type of wake to a completely merged.
Atmospheric entry is the movement of an object from outer space into and through the gases of an atmosphere of a planet, dwarf planet, or natural are two main types of atmospheric entry: uncontrolled entry, such as the entry of astronomical objects, space debris, or bolides; and controlled entry (or reentry) of a spacecraft capable of being navigated or following a.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.
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)).