Transonic Panel Method to Determine Loads on Oscillating Airfoils with Shocks
Author:
Affiliation:
1. National Aerospace Laboratory NLR, Amsterdam, The Netherlands
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/3.50977
Reference14 articles.
1. Implicit Finite-Difference Computations of Unsteady Transonic Flows about Airfoils
2. Results of an improved version of LTRAN2 for computing unsteady airloads on airfoils oscillating in transonic flow
3. Analysis of transonic flow about harmonically oscillating airfoils and wings
4. Calculation of unsteady transonic flows using the integral equation method
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1. Transonic wing flow computations using the field-panel method with a shock-fitting technique;Engineering Analysis with Boundary Elements;1995-12
2. Development of a shock-fitting field-panel method for 3D transonic flows;Computational Mechanics;1995-01
3. Nonlinear aeroelasticity;A Modern Course in Aeroelasticity;1995
4. Unsteady transonic aerodynamics and aeroelasticity;A Modern Course in Aeroelasticity;1995
5. A hybrid integral equation finite volume scheme for transonic potential flow about complex configurations;The Aeronautical Journal;1994-02
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