Investigation of Chord Ratio, Stagger, Decalage Angle, and Flap Angle for Dual Wing Configurations
Aerodynamical closely coupled dual wing configurations of unequal chords are investigated for medium speed general aviation applications. Vortex panel and momentum boundary layer analysis are utilized for the two-dimensional predictions. A multi-surface vortex lattice method is used for the three dimensional predictions. In the process of searching for the highest lift to drag ratio upper airfoil to lower airfoil chord ratios, both greater than and less than one, are investigated in terms of stagger, decalage angle, and gap. With the optimum chord ratio, at the optimum stagger and gap, proper spanwise decalage distribution is shown to yield the lowest two dimensional drag results. Various wing taper ratios and wing twists are investigated to increase wing efficiency. The dual wing configuration is shown to have significantly less drag and hence longer range than the conventional single wing configuration.
B. P. Selberg and G. D. Vincent, "Investigation of Chord Ratio, Stagger, Decalage Angle, and Flap Angle for Dual Wing Configurations," Proceedings of the 24th Aerospace Sciences Meeting (1986, Reno, NV), American Institute of Aeronautics and Astronautics (AIAA), Jan 1986.
The definitive version is available at https://doi.org/10.2514/6.1986-317
24th Aerospace Sciences Meeting (1986: Jan. 6-9, Reno, NV)
Mechanical and Aerospace Engineering
Article - Conference proceedings
© 1986 American Institute of Aeronautics and Astronautics (AIAA), All rights reserved.
09 Jan 1986