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Transition and separation control on a low-Reynolds number airfoil
Transition and separation control on a low-Reynolds number airfoil
- Publication Year :
- 1986
- Publisher :
- United States: NASA Center for Aerospace Information (CASI), 1986.
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Abstract
- The major problem associated with the aerodynamic performance of airfoils at low Reynolds numbers is the presence of extensive laminar boundary-layer separation resulting in a large increase in presssure drag and a decrease in lift. The rapid deterioration in airfoil characteristics can be largely eliminated by artificially controlling the flow through the introduction of suitable disturbances in the boundary layer such that transition occurs ahead of the anticipated laminar separation. This paper presents the results of wind-tunnel tests conducted on a 10-cm model of LRN (1)-1007 airfoil with passive (roughness trips) and active (acoustic excitation) controls to trigger transition and suppress separation. Significant improvements in the aerodynamic characteristics of the airfoil were observed. Results of this study for a chord Reynolds number range of 40,000 to 250,000 are presented in this paper.
- Subjects :
- Aerodynamics
Subjects
Details
- Language :
- English
- Database :
- NASA Technical Reports
- Notes :
- NAS1-17670, , NAS1-17683, , NAS1-18235
- Publication Type :
- Report
- Accession number :
- edsnas.19880023959
- Document Type :
- Report