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Experimental Investigation of Gurney Flaps on Reflection Plane Wing with Fuselage and/or Nacelle
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English
Abstract
An experimental investigation on the effects of Gurney flaps on a reflection plane model was conducted. Two sizes of Gurney flaps were tested on a series of configurations which included a tapered wing (with a NLF-0215 airfoil section), a fuselage, a nacelle, and their permutations. The tests were conducted at a Reynolds number of 1.0 million based on mean chord. Results indicated that lift and drag were increased upon using the Gurney flaps; lift to drag and lift squared to drag ratios were also increased. In particular, the lift to drag ratio for the complete “airplane” was almost the same with or without a small Gurney flap. Pitching moment became more negative (nose-down) with the Gurney flap, and positive (nose-up) with the addition of the fuselage.
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Citation
Heron, I., Myose, R., and Papadakis, M., "Experimental Investigation of Gurney Flaps on Reflection Plane Wing with Fuselage and/or Nacelle," SAE Technical Paper 971468, 1997, https://doi.org/10.4271/971468.Also In
References
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