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

Format:

Conference/Event

Author/Creator:

Heron, Ismael, author.

Conference Name:

General, Corporate & Regional Aviation Meeting & Exposition (1997-04-29 : Wichita, Kansas, United States)

Language:

English

Physical Description:

1 online resource

Place of Publication:

Warrendale, PA SAE International 1997

Summary:

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

Notes:

Vendor supplied data

Publisher Number:

971468

Access Restriction:

Restricted for use by site license