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Aerodynamic effects of leading-edge serrations on a two-dimensional airfoil
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Soderman, P. T. |
| Copyright Year | 1972 |
| Description | An investigation was conducted to determine the flow field and aerodynamic effects of leading-edge serrations on a two-dimensional airfoil at a Mach number of 0.13. The model was a NACA 66-012 airfoil section with a 0.76 m (30 in.) chord, 1.02 m (40 in.) span, and floor and end plates. It was mounted in the Ames 7- by 10-Foot Wind Tunnel. Serrated brass strips of various sizes and shapes were attached to the model in the region of the leading edge. Force and moment data, and photographs of tuft patterns and of oil flow patterns are presented. Results indicated that the smaller serrations, when properly placed on the airfoil, created vortices that increased maximum lift and angle of attack for maximum lift. The drag of the airfoil was not increased by these serrations at airfoil angles of attack near zero and was decreased at large angles of attack. Important parameters were serration size, position on the airfoil, and spacing between serrations. |
| File Size | 2926511 |
| Page Count | 38 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19720023342 |
| Archival Resource Key | ark:/13960/t6rz41j01 |
| Language | English |
| Publisher Date | 1972-09-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Two Dimensional Bodies Flow Distribution Vortex Generators Aerodynamic Noise Airfoils Wind Tunnel Models Separated Flow Aerodynamic Characteristics Leading Edges Lift Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
