Equivalence of a compressible inviscid flow and the Bloch vector under the thermal Jaynes–Cummings model

A three-dimensional inviscid flow analysis in the combined scroll-nozzle system of a radial inflow turbine is presented. The coupling of the two turbine components leads to a geometrically complicated, multiply-connected flow domain. Nevertheless, this coupling accounts for the mutual effects of both elements on the three-dimensional flow pattern throughout the entire system. Compressibility effects are treated for an accurate prediction of the nozzle performance. Different geometrical configurations of both the scroll passage and the nozzle region are investigated for optimum performance. The results corresponding to a sample scroll-nozzle configuration are verified by experimental measurements.

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Three-dimensional inviscid flow analysis of turbofan forced mixers

10.2514/6.1985-86 ◽

1985 ◽

Author(s):

T. BARBER ◽

G. MULLER ◽

S. RAMSAY ◽

E. MURMAN

Keyword(s):

Flow Analysis ◽

Three Dimensional ◽

Inviscid Flow

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Essential Ingredients for the Computation of Steady and Unsteady Blade Boundary Layers

Journal of Turbomachinery ◽

10.1115/1.2929124 ◽

1991 ◽

Vol 113 (4) ◽

pp. 608-616 ◽

Cited By ~ 3

Author(s):

H. M. Jang ◽

J. A. Ekaterinaris ◽

M. F. Platzer ◽

T. Cebeci

Keyword(s):

Boundary Layer ◽

Boundary Layers ◽

Stokes Equations ◽

Inviscid Flow ◽

Reynolds Numbers ◽

Navier Stokes ◽

Transitional Region ◽

Low Reynolds Numbers ◽

Flow Equations ◽

Low Reynolds

Two methods are described for calculating pressure distributions and boundary layers on blades subjected to low Reynolds numbers and ramp-type motion. The first is based on an interactive scheme in which the inviscid flow is computed by a panel method and the boundary layer flow by an inverse method that makes use of the Hilbert integral to couple the solutions of the inviscid and viscous flow equations. The second method is based on the solution of the compressible Navier–Stokes equations with an embedded grid technique that permits accurate calculation of boundary layer flows. Studies for the Eppler-387 and NACA-0012 airfoils indicate that both methods can be used to calculate the behavior of unsteady blade boundary layers at low Reynolds numbers provided that the location of transition is computed with the en method and the transitional region is modeled properly.

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A post-processing technique for stabilizing the discontinuous pressure projection operator in marginally-resolved incompressible inviscid flow

Computers & Fluids ◽

10.1016/j.compfluid.2016.04.021 ◽

2016 ◽

Vol 139 ◽

pp. 120-129 ◽

Cited By ~ 12

Author(s):

Sumedh M. Joshi ◽

Peter J. Diamessis ◽

Derek T. Steinmoeller ◽

Marek Stastna ◽

Greg N. Thomsen

Keyword(s):

Projection Operator ◽

Inviscid Flow ◽

Processing Technique ◽

Post Processing ◽

Pressure Projection ◽

Discontinuous Pressure

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Obstacle drag in stratified flow

Proceedings of the Royal Society of London Series A - Mathematical and Physical Sciences ◽

10.1098/rspa.1990.0054 ◽

1990 ◽

Vol 429 (1876) ◽

pp. 119-140 ◽

Cited By ~ 22

Keyword(s):

Experimental Study ◽

Linear Density ◽

Three Dimensional ◽

Inviscid Flow ◽

Force Balance ◽

Video Recordings ◽

Lee Waves ◽

Time Variations ◽

Obstacle Height ◽

Stable Linear

This paper describes an experimental study of the drag of two- and three-dimensional bluff obstacles of various cross-stream shapes when towed through a fluid having a stable, linear density gradient with Brunt-Vaisala frequency, N . Drag measurements were made directly using a force balance, and effects of obstacle blockage ( h / D , where h and D are the obstacle height and the fluid depth, respectively) and Reynolds number were effectively eliminated. It is shown that even in cases where the downstream lee waves and propagating columnar waves are of large amplitude, the variation of drag with the parameter K ( = ND /π U ) is qualitatively close to that implied by linear theories, with drag minima existing at integral values of K . Under certain conditions large, steady, periodic variations in drag occur. Simultaneous drag measurements and video recordings of the wakes show that this unsteadiness is linked directly with time-variations in the lee and columnar wave amplitudes. It is argued that there are, therefore, situations where the inviscid flow is always unsteady even for large times; the consequent implications for atmospheric motions are discussed.

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