Reactive and Inert Inviscid Flow Solutions by Quasi-linear Formulations and Shock Fitting

1991 ◽  
pp. 782-797
Author(s):  
F. Sabetta ◽  
B. Favini ◽  
G. Moretti ◽  
M. Onofri ◽  
M. Valorani
Keyword(s):  
Inviscid Flow ◽  
Shock Fitting

scholarly journals Eigenmode analysis of membrane stability in inviscid flow

2021 ◽  
Vol 6 (4) ◽  
Author(s):  
Christiana Mavroyiakoumou ◽  
Silas Alben
Keyword(s):  
Inviscid Flow ◽  
Membrane Stability ◽  
Eigenmode Analysis

Fresh look at floating shock fitting

1990 ◽  
Author(s):  
PETER-M. HARTWICH
Keyword(s):  
Shock Fitting

Optimization of the Three-Dimensional Flow Path in the Scroll-Nozzle System of a Radial Inflow Turbine

1984 ◽  
Vol 106 (2) ◽  
pp. 511-515 ◽  
Author(s):  
E. A. Baskharone
Keyword(s):  
Flow Analysis ◽  
Three Dimensional ◽  
Inviscid Flow ◽  
Three Dimensional Flow ◽  
Multiply Connected ◽  
Dimensional Flow ◽  
Nozzle Configuration ◽  
Flow Domain ◽  
Radial Inflow Turbine ◽  
Compressibility Effects

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.

Three-dimensional inviscid flow analysis of turbofan forced mixers

1985 ◽  
Author(s):  
T. BARBER ◽  
G. MULLER ◽  
S. RAMSAY ◽  
E. MURMAN
Keyword(s):  
Flow Analysis ◽  
Three Dimensional ◽  
Inviscid Flow

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

1991 ◽  
Vol 113 (4) ◽  
pp. 608-616 ◽  
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.

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

2016 ◽  
Vol 139 ◽  
pp. 120-129 ◽  
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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