(n0009sm-il) NACA-0009 9.0% smoothed Airfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file NACA 0009 airfoil (smoothed)Max thickness 9% at 30.9% chordMax camber 0% at 0% chordSource UIUC Airfoil Coordinates Database (n0012-il) ...
An investigation was conducted in the NACA full-scale wind tunnel to determine the aerodynamic characteristics of the NACA 0009, 0012, and 0018 airfoils, with the ultimate purpose of providing data to be used as a basis for comparison with other wind-tunnel data, mainly in the study of scale...
A similar trend of the 𝐶𝐿CL characteristics for the NACA 0009 airfoil for Reynolds numbers in the range of 3×1063×106 to 6×1066×106 can be found in the well-known report “Summary of Airfoil Data” from 1945 [42]. Even though the Jacobs and Sherman results are more useful ...
Send to airfoil plotterAdd to comparisonAdd to My airfoils NACA 4 digit airfoils in the database NACA 0006 NACA 0008 NACA 0009 NACA 0010 NACA 0012 NACA 0015 NACA 0018 NACA 0021 NACA 0024 NACA 1408 NACA 1410 NACA 1412 NACA 2408 NACA 2410 NACA 2411 NACA 2412 NACA 2414 NACA 2415 NACA ...
The objective of this study is to investigate the impact of airfoil thickness and camber for canonical NACA airfoils at Reynolds numbers in this range and to correlate the observed aerodynamic behavior with the flow patterns. For this purpose, NACA-0009, 0012, 0021, and 6409 airfoils were used...
Source UIUC Airfoil Coordinates DatabaseSource dat fileThe dat file is in Lednicer format NACA M2 AIRFOIL 17. 17. 0.0000000 0.0000000 0.0125000 0.0130000 0.0250000 0.0174000 0.0500000 0.0233000 0.1000000 0.0284000 0.1500000 0.0318000 0.2000000 0.0349000 0.2500000 0.0378000 0.3000000 0.0400000 0.4000000 0.0400000...
The findings can be useful for engineers and researchers involved in the design and optimization of wind turbine blades, particularly in selecting the optimal airfoil for a given operating condition [19]. Authors explores the effect of adding half NACA 0009 and 0012 air foils to the trailer of ...
Future tests will measure heat transfer data from the same airfoil in the Lewis Icing Research Tunnel. Roughness was obtained by the attachment of small, 2 mm diameter hemispheres of uniform size to the airfoil in three different patterns. Heat transfer measurements were recorded in flight on the...
Each airfoil was also tested with a 0.20c full-span split flap. Tuft surveys were included to show the progressive breakdown of flow with increasing angles of attack. Previously published data from tests of the NACA 0009, 0012, and 0018 airfoils in the full-scale tunnel have been included ...
Send to airfoil plotterAdd to comparisonAdd to My airfoils NACA 4 digit airfoils in the database NACA 0006 NACA 0008 NACA 0009 NACA 0010 NACA 0012 NACA 0015 NACA 0018 NACA 0021 NACA 0024 NACA 1408 NACA 1410 NACA 1412 NACA 2408 NACA 2410 NACA 2411 NACA 2412 NACA 2414 NACA 2415 NACA ...