An Interactive Boundary-Layer Method for Three-Dimensional Flows

2007 ◽  
pp. 417-454
Keyword(s):  
Boundary Layer ◽  
Three Dimensional ◽  
Layer Method ◽  
Boundary Layer Method

Interactive three-dimensional boundary-layer method for transonic flow over swept wings

AIAA Journal ◽  
1991 ◽  
Vol 29 (5) ◽  
pp. 678-679 ◽  
Author(s):  
Shawn H. Woodson ◽  
James F. Campbell ◽  
Fred R. DeJarnette
Keyword(s):  
Boundary Layer ◽  
Transonic Flow ◽  
Three Dimensional ◽  
Layer Method ◽  
Boundary Layer Method ◽  
Dimensional Boundary ◽  
Swept Wings

A comparison of several eddy viscosity turbulence models in two and three dimensional boundary layer flows

1994 ◽  
Vol 98 (973) ◽  
pp. 73-82 ◽  
Author(s):  
A. W. C. Leung ◽  
L. C. Squire
Keyword(s):  
Boundary Layer ◽  
Eddy Viscosity ◽  
Three Dimensional ◽  
Turbulence Models ◽  
Boundary Layer Flows ◽  
Layer Method ◽  
Boundary Layer Method ◽  
Dimensional Boundary ◽  
Anisotropic Form

SummaryFour flow cases are calculated using a boundary layer method with five turbulence models. The Johnson-King model, in particular, is modified and two variant forms are used in the present work. The variant forms involve an anisotropic form of three-dimensional eddy viscosity formulations and a modification in the outer viscosity expression. It is found that the Johnson-King model generally performs very well as compared to the others, and the variant forms provide further improvement in most cases.

Boundary layer method in the problem of far propagation of surface SV-waves

2011 ◽  
Vol 175 (6) ◽  
pp. 651-671
Author(s):  
N. Ya. Kirpichnikova ◽  
A. S. Kirpichnikova
Keyword(s):  
Boundary Layer ◽  
Layer Method ◽  
Boundary Layer Method

A Simple and Robust Subsonic Boundary Layer Method to Be Used with the Panel Method for Wing Calculations Using a Wing Strip Approach

2015 ◽  
Vol 798 ◽  
pp. 596-601
Author(s):  
R.F. Francisco Reis ◽  
Guilherme A. Santana ◽  
Paulo Iscold ◽  
Carlos A. Cimini
Keyword(s):  
Boundary Layer ◽  
Lift Coefficient ◽  
Aircraft Design ◽  
Aerodynamic Characteristics ◽  
Viscous Drag ◽  
Layer Method ◽  
Boundary Layer Method ◽  
Dimensional Boundary ◽  
Classical Integral ◽  
Empirical Corrections

This paper will present the development of a simple subsonic boundary layer method suitable to be used coupled with panel methods in order to estimate the aerodynamic characteristics, including viscous drag and maximum lift coefficient, of 3D wings. The proposed method does not require viscous-inviscid iterations and is based on classical integral bi-dimensional boundary layer theory using Thwaites and Head ́s models with bi-dimensional empirical corrections applied to each wing strip being therefor robust and efficient to be used in the early conceptual stage of aircraft design. Presented results are compared to the Modified CS Method in an IBL scheme and experimental data and are shown to provide good results.

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