naca airfoils

naca airfoils - NACA 0021 2 1.5 1 Cl 0.5 0 - 12 -10 -8 -6...

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Unformatted text preview: NACA 0021 2 1.5 1 Cl 0.5 0 - 12 -10 -8 -6 -4 -2 0 2 4 6 8 10 12 -0.5 -1 -1.5 Column C -2 Angle o f a t t a ck (°) Column D NACA 0021 0.014 0.012 0.01 Cd 0.008 0.006 0.004 0.002 0 -1.5 -1 -0.5 0 Cl 0.5 1 1.5 NACA 0010 2 1.5 1 0.5 Cl 0 - 15 -10 -5 0 5 -0.5 -1 -1.5 Column C -2 Angle of at t ack (°) 10 15 NACA 0021 alpha CL inviscid -12 -10 -8 -6 -4 -2 0 2 4 6 8 10 12 -1.5408 -1.2869 -1.0314 -0.7747 -0.517 -0.2586 0 0.2586 0.517 0.7747 1.0314 1.2869 1.5408 NACA 0010 alpha -12 -10 -8 -6 -4 -2 0 2 4 6 8 10 12 -1.417 -1.1835 -0.9485 -0.7124 -0.4754 -0.2378 0 0.2378 0.4754 0.7124 0.9485 1.1835 1.417 CL visc -1.1364 -1.054 -0.8702 -0.6631 -0.4472 -0.2246 0 0.2246 0.4472 0.6631 0.8702 1.054 1.1364 Cd 0.01164 0.01061 0.00902 0.00792 0.00718 0.00679 0.00661 0.00679 0.00718 0.00792 0.00902 0.01061 0.01164 ...
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naca airfoils - NACA 0021 2 1.5 1 Cl 0.5 0 - 12 -10 -8 -6...

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