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Scale and Turbulence Effects on the Lift and Drag Characteristics of the NACA 65(Sub 3)-418, A=1.0 Airfoil SectionWind-tunnel tests, investigating low drag wing performance in small-scale tests, showed a large increase in minimum drag coefficient, and a decrease of maximum lift coefficient occurred with decreasing Reynolds Number above certain designated values. The lift-curve slope varied up to 6% between high and low turbulence levels. Low Reynolds Number test data are unreliable for low drag airfoils either to estimate full-scale characteristics or to determine merits of airfoils for higher Reynolds numbers.
Document ID
19930092795
Acquisition Source
Legacy CDMS
Document Type
Other - NACA Wartime Report
External Source(s)
hdl:100.2/ADA800600
Authors
Tucker, Warren A. (National Advisory Committee for Aeronautics. Langley Aeronautical Lab. Langley Field, VA, United States)
Quinn, John H. (National Advisory Committee for Aeronautics. Langley Aeronautical Lab. Langley Field, VA, United States)
Date Acquired
September 6, 2013
Publication Date
August 1, 1944
Subject Category
Aerodynamics
Report/Patent Number
NACA-ACR-L4H11
NACA-WR-L-138
Report Number: NACA-ACR-L4H11
Report Number: NACA-WR-L-138
Accession Number
93R22085
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
REYNOLDS NUMBER
LIFT & DRAG-EFFECT OF TURBULENCE
WIND TUNNEL TESTS-NACA-LOW-TURBULENCE (LMAL)
WIND TUNNEL TESTS-NACA-PRESSURE, TWO-DIMENSIONAL (LMAL) (7 1/2' X 3')
AIRFOILS-NACA 653-418-CHAR & ORDINATES LOW-DRAG
SCALE EFFECT-AIRFOILS-NACA 653-418

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