The inviscid stability of supersonic flow past a sharp cone
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The inviscid stability of supersonic flow past a sharp cone

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Published by Institute for Computer Applications in Science and Engineering, NASA Langley Research Center, National Technical Information Service, distributor in Hampton, VA, [Springfield, Va .
Written in English

Subjects:

  • Cones.,
  • Flow stability.,
  • Inviscid flow.,
  • Mathematical models.,
  • Supersonic flow.

Book details:

Edition Notes

StatementPeter W. Duck, Stephen J. Shaw..
SeriesICASE report -- no. 90-14., NASA contractor report -- 181996., NASA contractor report -- NASA CR-181996.
ContributionsShaw, Stephen J., 1955-, Institute for Computer Applications in Science and Engineering.
The Physical Object
FormatMicroform
Pagination1 v.
ID Numbers
Open LibraryOL16126900M

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The supersonic flow past a sharp cone is studied. The associated boundary layer flow (i.e. the velocity and temperature field) is computed. The inviscid linear temporal stability of axisymmetric boundary layers in general is considered, and in particular, a so- called “triply generalized” inflection condition for “subsonic” non Author: Peter W. Duck. bers. Numerical solutions for inviscid flow at zero angle of attack are pre- sented and analyzed to show the effect of cone angle on surface-pressure distribution for Mach numbers of 10 and M and half-angle blunted cone are given at several axial stations. and specific-heat ratios of File Size: 2MB. where a 2 = (dp/dρ) is the sound velocity in gas.. Depending on whether the motion is subsonic or supersonic, the differential equation is an elliptic or hyperbolic one. Inviscid flows of an incompressible fluid form a large and important class because with the velocity of flow much lesser than the velocity of sound, the velocity potential equation takes the form of the Laplace linear. His book, Hypersonic Flow Theory, co-authored with Wallace D. Hayes, and reprinted by Dover in as Hypersonic Inviscid Flow, is still the basic book on this subject. Synthetic Fuels, written with R. Edwin Hicks, is certainly one of the most important and timely engineering texts ever reprinted by by:

Inviscid flow is the flow of an inviscid fluid, in which the viscosity of the fluid is equal to zero. Though there are limited examples of inviscid fluids, known as superfluids, inviscid flow has many applications in fluid dynamics. The Reynolds number of inviscid flow approaches infinity as the viscosity approaches zero. When viscous forces are neglected, such as the case of inviscid flow.   Hi PF! Some classmates and I were talking about the streamlines around a submerged cone being pulled at a velocity ##V##. The picture is attached. Can someone shed some light on the streamlines of this flow, assuming it is inviscid? I take a frame of reference that moves with the cone. computing the inviscid supersonic flow about these shapes. In addition, studies based on simple conical geometry provide a clearer insight into fundamental physical processes for both the experimental and computational investigator. Busemann (1) pioneered the concept of conical flow defined as a self-.   His book, Hypersonic Flow Theory, co-authored with Wallace D. Hayes, and reprinted by Dover in as Hypersonic Inviscid Flow, is still the basic book on this subject. Synthetic Fuels, written with R. Edwin Hicks, is certainly one of the most important and timely engineering texts ever reprinted by :

This paper studies the steady supersonic flow past a Lipschitz curved cone. Under the assumptions that the cone has an opening angle less than a critical value and has sufficiently small total variation of the tangent of the perturbation and that the Mach number of incoming flow is sufficiently large, the global weak solution is constructed via Glimm scheme for 1 Cited by: 5. the point where the flow breaks down due to viscous effects. Unfortunately, such viscous, vortex flows do not allow easy analysis. A classical example, which illustrates the nature and difficulties of these flows, is the delta wing problem. The supersonic flow around a delta wing at angle of attack with sharpFile Size: 1MB. Steady-state examples include flow over a sharp cone, a hyperbolic cone and a hyperbolic wedge. For the cone, the exact flow solution is used to show that the method is spectrally accurate. As an example of an unsteady flow, we present a calculation of the interaction of a free-stream hot ring with the flow over a sharp Cited by: We establish the global existence and stability of a three-dimensional supersonic conic shock wave for a perturbed steady supersonic flow past an infinitely long circular cone with a sharp angle.