Errata: Prediction of Turbulent Boundary Layers at Low Reynolds Numbers

AIAA Journal ◽  
1977 ◽  
Vol 15 (5) ◽  
pp. 0767a-0767a
Author(s):  
Richard H. Pletcher
Keyword(s):  
Boundary Layers ◽  
Reynolds Numbers ◽  
Turbulent Boundary Layers ◽  
Low Reynolds Numbers ◽  
Low Reynolds

scholarly journals Eddy Viscosities and Mixing Lengths for Turbulent Boundary Layers on Flat Plates, Smooth or Rough

1988 ◽  
Vol 32 (04) ◽  
pp. 229-237
Author(s):  
Paul S. Granville
Keyword(s):  
Boundary Layers ◽  
Rough Surfaces ◽  
Equations Of Motion ◽  
Reynolds Numbers ◽  
Turbulent Boundary Layers ◽  
Flat Plates ◽  
Low Reynolds Numbers ◽  
Low Reynolds ◽  
Similarity Laws

Algebraic formulas are derived here for the eddy viscosities and mixing lengths of turbulent boundary layers on flat plates. The effect of low Reynolds numbers, especially on rough surfaces, is included. The formulas are based on the similarity laws and the equations of motion. Both smooth and rough surfaces are considered. The agreement with Klebanoff's measurements is excellent.

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.

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