Experimental Investigation of Gurney Flaps on Reflection Plane Wing with Fuselage and/or Nacelle
971468
05/01/1997
- Event
- Content
- 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.
- Pages
- 9
- 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.