Experimental Investigation of Gurney Flaps on Reflection Plane Wing with Fuselage and/or Nacelle

971468

05/01/1997

Event
General, Corporate & Regional Aviation Meeting & Exposition
Authors Abstract
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.
Meta TagsDetails
DOI
https://doi.org/10.4271/971468
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.
Additional Details
Publisher
Published
May 1, 1997
Product Code
971468
Content Type
Technical Paper
Language
English