Equations for the Loading on Triangular Wings Having Supersonic Leading and Trailing Edges Due to Various Basic Twist Distributions
Author:
Affiliation:
1. Republic Aviation Corporation,
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Link
http://arc.aiaa.org/doi/pdf/10.2514/8.2692
Reference4 articles.
1. A Superposition Method for Calculating the Aeroelastic Behavior of Swept Wings
2. Determination of Elastic Wing Aerodynamic Characteristics
3. A Unit Solution for the Load Distribution of a Nonrigid Wing by Matrix Methods
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1. Tragflügel bei kompressibler Strömung;Aerodynamik des Flugzeuges;2001
2. Tragflügel bei kompressibler Strömung;Aerodynamik des Flugzeuges;1969
3. La theorie des ecoulements a potentiel homogene et ses applications au calcul des ailes en regime supersonique;Progress in Aerospace Sciences;1961-01
4. Equations for the Loading, Section Pitching-Moment Coefficient, and Center-of-Pressure Distributions on Triangular Wings Having Supersonic Leading and Trailing Edges for Various Basic;Journal of the Aeronautical Sciences;1956-02
5. Spanwise Variation in the Pitching-Moment Coefficient and the Center of Pressure Due to Various Basic Twist Distributions on Triangular Wings Having Supersonic Leading and Trailing Edge;Journal of the Aeronautical Sciences;1955-09
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