Transition and separation control on a low-Reynolds number airfoilThe 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.
Document ID
19880023959
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Mangalam, S. M. (NASA Lewis Research Center Cleveland, OH, United States)
Bar-Sever, A. (AS&M, Inc. Hampton, VA, United States)
Zaman, K. B. M. Q. (NASA Lewis Research Center Cleveland, OH, United States)
Harvey, W. D. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 13, 2013
Publication Date
January 1, 1986
Subject Category
Aerodynamics
Meeting Information
Meeting: Aerodynamics at low Reynolds numbers Re greater than 10 to the 4th and less than 10 to the 6th