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Book ChapterDOI

A Calculation Method of Leading-Edge Separation Bubbles

C. Gleyzes, +2 more
- pp 173-192
TLDR
The positive pressure gradient, downstream of the suction peak at the leading edge of an airfoil at incidence, may induce large perturbations on the general pattern of the flow as discussed by the authors.
Abstract: 
The positive pressure gradient, downstream of the suction peak at the leading edge of an airfoil at incidence, may, under some conditions, induce large perturbations on the general pattern of the flow.

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Journal ArticleDOI

Computational Fluid Dynamics Compatible Transition Modeling Using an Amplification Factor Transport Equation

James G. Coder, +1 more
- 10 Oct 2014 - 
TL;DR: In this paper, a laminar-turbulent transition model is proposed to model the growth of the maximum Tollmien-Schlichting instability amplitude in the presence of a boundary layer.
Journal ArticleDOI

Analysis of transitional separation bubbles on infinite swept wings

R. L. Davis, +2 more
- 01 Jul 1985 - 
TL;DR: In this paper, a two-dimensional local inviscid-viscous interaction technique for the analysis of airfoil transitional separation bubbles, ALESEP (Airfoil Leading Edge Separation), has been extended for the calculation of transition separation bubbles over infinite swept wings.
Journal ArticleDOI

Improved Two-Dimensional Dynamic Stall Prediction with Structured and Hybrid Numerical Methods

Kai Richter, +5 more
- 01 Oct 2011 - 
TL;DR: In this article, a joint comprehensive validation activity on the structured numerical method elsA and the hybrid numerical method TAU was conducted with respect to dynamic stall applications, where the influence of several factors on the dynamic stall prediction were investigated.
Proceedings ArticleDOI

Implicit Implementation of the Full e^n Transition Criterion

Mark Drela
Book

An aerodynamic design method for supersonic natural laminar flow aircraft

Peter Sturdza
TL;DR: In this article, a boundary-layer solver is used to estimate the laminar-to-turbulent transition location of a supersonic aircraft and the total drag of the aircraft.