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Experimental results for the Eppler 387 airfoil at low Reynolds numbers in the Langley low-turbulence pressure tunnelExperimental results were obtained for an Eppler 387 airfoil in the Langley Low Turbulence Pressure Tunnel. The tests were conducted over a Mach number range from 0.03 to 0.13 and a chord Reynolds number range for 60,000 to 460,000. Lift and pitching moment data were obtained from airfoil surface pressure measurements and drag data for wake surveys. Oil flow visualization was used to determine laminar separation and turbulent reattachment locations. Comparisons of these results with data on the Eppler 387 airfoil from two other facilities as well as the Eppler airfoil code are included.
Document ID
19890001471
Document Type
Technical Memorandum (TM)
Authors
Mcghee, Robert J. (NASA Langley Research Center Hampton, VA, United States)
Walker, Betty S. (NASA Langley Research Center Hampton, VA, United States)
Millard, Betty F. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 5, 2013
Publication Date
October 1, 1988
Subject Category
AERODYNAMICS
Report/Patent Number
L-16430
NASA-TM-4062
NAS 1.15:4062
Funding Number(s)
PROJECT: RTOP 505-60-21-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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