Inviscid flow past a ducted axisymmetric body with annular elliptical region

1970 ◽  
Vol 2 (1) ◽  
pp. 101-104
Author(s):  
S. K. Betyaev
Keyword(s):  
Inviscid Flow ◽  
Axisymmetric Body ◽  
Flow Past ◽  
Elliptical Region

Base Pressure Associated With Incompressible Flow Past Wedges at High Reynolds Numbers

1979 ◽  
Vol 46 (3) ◽  
pp. 483-492 ◽  
Author(s):  
N. R. Warpinski ◽  
W. L. Chow
Keyword(s):  
Boundary Layer ◽  
Incompressible Flow ◽  
Inviscid Flow ◽  
The Body ◽  
Base Pressure ◽  
Jet Mixing ◽  
Flow Past ◽  
Wedge Surface ◽  
Surface Jet ◽  
High Reynolds

A model is suggested to study the viscid-inviscid interaction associated with steady incompressible flow past wedges of arbitrary angles. It is shown from this analysis that the determination of the nearly constant pressure (base pressure) prevailing within the near wake is really the heart of the problem and this pressure can only be determined from these interactive considerations. The basic free streamline flow field is established through two discrete parameters which should adequately describe the inviscid flow around the body and the wake. The viscous flow processes such as boundary-layer buildup along the wedge surface, jet mixing, recompression, and reattachment which occurs along the region attached to the inviscid flow in the sense of the boundary-layer concept, serve to determine the aforementioned parameters needed for the establishment of the inviscid flow. It is found that the point of reattachment behaves as a saddle point singularity for the system of equations describing the viscous recompression process. Detailed results such as the base pressure, pressure distributions on the wedge surface, and the wake geometry as well as the influence of the characteristic Reynolds number are obtained. Discussion of these results and their comparison with the experimental data are reported.

Development of Lattice Boltzmann Flux Solver for Simulation of Incompressible Flows

2014 ◽  
Vol 6 (4) ◽  
pp. 436-460 ◽  
Author(s):  
C. Shu ◽  
Y. Wang ◽  
C. J. Teo ◽  
J. Wu
Keyword(s):  
Circular Cylinder ◽  
Lattice Boltzmann ◽  
Incompressible Flows ◽  
Inviscid Flow ◽  
Navier Stokes ◽  
Time Interval ◽  
Uniform Mesh ◽  
Inviscid Flows ◽  
Flow Past ◽  
Flow Variables

AbstractA lattice Boltzmann flux solver (LBFS) is presented in this work for simulation of incompressible viscous and inviscid flows. The new solver is based on Chapman-Enskog expansion analysis, which is the bridge to link Navier-Stokes (N-S) equations and lattice Boltzmann equation (LBE). The macroscopic differential equations are discretized by the finite volume method, where the flux at the cell interface is evaluated by local reconstruction of lattice Boltzmann solution from macroscopic flow variables at cell centers. The new solver removes the drawbacks of conventional lattice Boltzmann method such as limitation to uniform mesh, tie-up of mesh spacing and time interval, limitation to viscous flows. LBFS is validated by its application to simulate the viscous decaying vortex flow, the driven cavity flow, the viscous flow past a circular cylinder, and the inviscid flow past a circular cylinder. The obtained numerical results compare very well with available data in the literature, which show that LBFS has the second order of accuracy in space, and can be well applied to viscous and inviscid flow problems with non-uniform mesh and curved boundary.

Inviscid flow past a sharp-nosed body with a closed finite wake

AIAA Journal ◽  
1975 ◽  
Vol 13 (11) ◽  
pp. 1524-1526
Author(s):  
Michael John Wheatley
Keyword(s):  
Inviscid Flow ◽  
Flow Past

Third-order blast wave theory and its application to hypersonic flow past blunt-nosed cylinders

1960 ◽  
Vol 9 (4) ◽  
pp. 613-620 ◽  
Author(s):  
R. J. Swigart
Keyword(s):  
Hypersonic Flow ◽  
Blast Wave ◽  
Wave Theory ◽  
Inviscid Flow ◽  
Order Theory ◽  
Third Order ◽  
Surface Pressure Distribution ◽  
Flow Past ◽  
Cylindrical Blast Wave ◽  
Flow Variables

The inviscid flow behind a cylindrical blast wave and its analogy with hypersonic flow past blunt-nosed cylinders is considered. Sakurai (1953, 1954) obtained a solution for the flow field behind a propagating blast wave by expanding the flow variables in power series of 1/M2, where M is the blast wave Mach number, and determining the coefficients of the first two terms in the series. Here the work is extended to include third-order terms. Third-order theory is shown to improve the prediction of shock wave shapes and surface pressure distribution on hemisphere-cylinder configurations at M∞ = 7·7 and 17·18.

Prediction of Viscous Effects in Steady Transonic Flow Past an Aerofoil

1979 ◽  
Vol 30 (3) ◽  
pp. 485-505 ◽  
Author(s):  
M.R. Collyer ◽  
R.C. Lock
Keyword(s):  
Boundary Layer ◽  
Shock Waves ◽  
Transonic Flow ◽  
Lift Coefficient ◽  
Inviscid Flow ◽  
Viscous Effects ◽  
Flow Past ◽  
Boundary Layer Development ◽  
Transition Position ◽  
Realistic Representation

SummaryAn account is given of a numerical method for calculating transonic flow past an aerofoil with an allowance for viscous effects, providing that the boundary layer remains fully attached over the aerofoil surface. The method has been developed by combining, in an iterative manner, calculations of the inviscid flow with calculations of the compressible boundary layer and wake. The solution for the inviscid flow is obtained by an iterative scheme, originally established by Garabedian & Korn, which has been modified to give a more realistic representation of shock waves. The boundary-layer development is treated as laminar initially; at a certain transition position a turbulent boundary layer is assumed to develop, and this is determined by the lag-entrainment method of Green et al. Comparisons of the results from the numerical scheme with some experimental measurements are shown for various examples in which shock waves of moderate strength are present. The method predicts, with reasonable accuracy, both the detailed pressure distribution and the variation of drag coefficient with lift coefficient.

Incompressible Potential Flow Past Axisymmetric Bodies in Cylindrical Pipes

1973 ◽  
Vol 24 (3) ◽  
pp. 179-191 ◽  
Author(s):  
J Mathew ◽  
S N Majhi
Keyword(s):  
Integral Equation ◽  
Numerical Solutions ◽  
Axisymmetric Body ◽  
The Body ◽  
Infinite Length ◽  
Flow Past ◽  
Similar Body ◽  
Axisymmetric Bodies ◽  
Cylindrical Duct ◽  
Uniform Stream

SummaryVandrey’s procedure, based on the method of singularities (ring vortices), for finding the pressure distribution on an axisymmetric body in a uniform stream is extended to the case of flow past a similar body in a uniform stream within a cylindrical duct of infinite length. The final form of the integral equation for the velocity distribution on the body is the same as that given by Vandrey; however, its kernel possesses additional terms representing the influence of the duct. Numerical solutions are worked out for varying radii ratio between a sphere and a duct and also between the more general-shaped axisymmetric body and a duct.

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