3 edition of **The inviscid stability of supersonic flow past a sharp cone** found in the catalog.

The inviscid stability of supersonic flow past a sharp cone

- 150 Want to read
- 36 Currently reading

Published
**1990**
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

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

**Edition Notes**

Statement | Peter W. Duck, Stephen J. Shaw.. |

Series | ICASE report -- no. 90-14., NASA contractor report -- 181996., NASA contractor report -- NASA CR-181996. |

Contributions | Shaw, Stephen J., 1955-, Institute for Computer Applications in Science and Engineering. |

The Physical Object | |
---|---|

Format | Microform |

Pagination | 1 v. |

ID Numbers | |

Open Library | OL16126900M |

Rotational flow may be characterized by vorticity, which is the curl of velocity. A simple example is a vortex ring (like a cigarette smoke puff but without the diffusion process) Check out fundamental fluid dynamic books. It is important NOT to confuse potential flow with inviscid flow (which may be the source of your confusion). @article{osti_, title = {Three-Dimensional Inviscid Flow About Supersonic Blunt Cones at Angle of Attack - III: Coupled Subsonic and Supersonic Programs for Inviscid Three-Dimensional Flow}, author = {Abbett, M. J. and Fort, R.}, abstractNote = {The three-dimensional ideal gas flow in the shock layer of a blunted supersonic cone at an angle of attack is calculated using two asymptotic.

Stability of Inviscid Parallel Flows between Two Parallel Walls Hua-Shu Dou Temasek Laboratories, National University of Singapore, Singapore Email: [email protected]; [email protected] Abstract: In this paper, the stability of inviscid parallel flow between two parallel walls is studied. 17 Flow Field Downstream of Sharp Cone-Cylinder on this problem in the past. Murthy and ~arnmit'') investigated experimentally the interaction of a turbulent boundary layer with supersonic layer, an inviscid sublayer and a viscous sublayer adja- cent to the wall. The flow in .

A wake-dominated unsteady flow of Mach number past a cone of vertex angle 60 deg is calculated numerically using high-order finite difference schemes on structured grids. The three-dimensional compressible Euler equations are solved to simulated an inviscid flow that exhibits large fluctuations of pressure and velocity as a result of the shedding of vortices behind the by: Test Model. The test model consisted of a flat plate and an interchangeable instrumentation plate. The test model was mm wide and mm long, which was supported by a single sting mounted on the bottom wall of the test section, as shown in Figure concave corner with 5-, 7-, , and deg angles or the convex corner with 5-, , , and deg angles was located at mm Cited by: 2.

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In this paper we consider the laminar boundary layer which forms on a sharp cone in a supersonic freestream, where lateral curvature plays a key role in the physics of the problem.

This flow is then analysed from the point of view of linear, temporal, inviscid by: 7. Get this from a library. The inviscid stability of supersonic flow past a sharp cone.

[Peter W Duck; Stephen J Shaw; Institute for Computer Applications in Science and Engineering.]. 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.

The effect of distributed suction/injection on the spatial linear inviscid instability of a supersonic boundary layer past a slender cone Article (PDF Available) in Acta Mechanica (1) When supersonic flow (think of a stream tube/cylinder) hits a cone a differential volume element of the stream tube will constantly increase in size while it follows the cone surface.

This changes the pressure and is called relaxation. Due to this volume increase of the stream tube the cone flow has two features/regimes which the wedge flow. Geometry. The geometry is a cone with a semi-vertex angle of 10 degrees and a length of approximately ft.

Comparison Data. An analytic solution for the inviscid, supersonic, steady, adiabatic flow over a cone is available through the Taylor-Maccoll differential equation as described in most compressible flow textbooks.

Flow Past a Spherical Obstacle Consider the steady flow pattern produced when an impenetrable rigid spherical obstacle is placed in a uniformly flowing, incompressible, inviscid fluid.

For instance, suppose that the radius of the sphere is, and that its center coincides with the origin. Hypersonic Inviscid Flow (Dover Books on Physics) - Kindle edition by Hayes, Wallace D., Probstein, Ronald F. Download it once and read it on your Kindle device, PC, phones or tablets. Use features like bookmarks, note taking and highlighting while reading Hypersonic Inviscid Flow (Dover Books on Author: Wallace D.

Hayes, Ronald F. Probstein. The problem of calculating the supersonic flow past a circular cone at small incidence c~ is treated by the method of inner and outer expansions, on the assumption that it can be expressed as a perturbation (in 15owers of e~) of the corresponding axially symmetric flow.

3 parameter K and the critical condition is determined by the maximum value of K in the flow. For a given flow geometry and fluid properties, when the maximum of K in the flow field is larger than a critical value Kc, it is expected that instability can occur for certain initial disturbance [1].

Turbulence transition is a local phenomenon in the earlier stage.I Flow deections through angles other than 90 o can be obtained by taking other values of n.

Inviscid Flows /11 17 / 22 Example 3: Flow Past a Cylinder I Consider a uniform stream of velocity Uo, owing past a circular cylinder of radius R as shown.

I = =File Size: KB.Rayleigh's Inviscid Instability Argument. To study the stability of inviscid circular flow between concentric cylinders, Lord Rayleigh developed an analogy with the stability of a fluid of variable density under the force of gravity. Taylor summarizes this as: ``the varying centrifugal force of the different layers of fluid plays the part of.