Transition on a Wing with Spanwise Varying Crossflow and Linear Stability Analysis-Reference-Cited by-同舟云学术

Transition on a Wing with Spanwise Varying Crossflow and Linear Stability Analysis

Published:2015-02 Issue:2 Volume:53 Page:321-335
ISSN:0001-1452
Container-title:AIAA Journal
language:en
Short-container-title:AIAA Journal

Author:

Petzold R.¹,Radespiel R.¹

Affiliation:

1. Institute of Fluid Mechanics, Technische Universität Braunschweig, 38108 Brunswick, Germany

Publisher

American Institute of Aeronautics and Astronautics (AIAA)

Subject

Aerospace Engineering

Link

http://arc.aiaa.org/doi/pdf/10.2514/1.J053127

Reference25 articles.

1. Van IngenJ. L. “A Suggested Semi-Empirical Method for the Calculation of the Boundary-Layer Transition Region,” Dept. of Aerospace Engineering, Univ. of Delft, Rept. VTH-74, Delft, The Netherlands, 1956.

2. SmithA. M. O.GamberoniN. “Transition, Pressure Gradient and Stability,” Douglas Aircraft Co., Rept. ES-26-388, Santa Monica, CA, 1956.

3. Large-Scale Laminar Flow Tests Evaluated with Linear Stability Theory

4. Notes on Numerical Fluid Mechanics and Multidisciplinary Design (NNFM);Schrauf G.,2003

5. SchraufG. “LILO 2.1 Users Guide and Tutorial,” GSSC TR-6, Bremen, Germany, 2006.

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