Lift enhancement of an airfoil using a Gurney flap and vortex generatorsThe results of a low-speed wind tunnel test are presented for a single-element airfoil incorporating two lift-enhancing devices, namely a Gurney flap and vortex generators. The former consists of a small plate, on the order of one to two percent of the airfoil chord in height, located at the trailing edge perpendicular to the pressure side of the airfoil. The later consist of commercially-available, wishbone-shaped vortex generators. The test was conducted in the NASA Ames 7- by 10-foot Wind Tunnel with a full-span NACA 4412 airfoil. Measurements of surface pressure distributions and wake profiles were made to determine the lift, drag, and pitching-moment coefficients for the various airfoil configurations. The results indicate that the addition of a Gurney flap increased the maximum lift coefficient from 1.49 up to 1.96.
Document ID
19930040765
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Storms, Bruce L. (Sterling Software, Inc.; NASA, Ames Research Center Moffett Field, CA, United States)
Jang, Cory S. (California Polytechnic State Univ. San Luis Obispo, United States)
Date Acquired
August 16, 2013
Publication Date
January 1, 1993
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 93-0647
Meeting Information
Meeting: AIAA, Aerospace Sciences Meeting and Exhibit