NACA 63-206 (naca63206-il)
NACA 63-206 - NACA 63-206 airfoil
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(naca63206-il) NACA 63-206 NACA 63-206 airfoil Max thickness 6% at 35% chord. Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
NACA 63-206 1.00000 0.00000 0.95006 0.00454 0.90013 0.00900 0.85049 0.01356 0.80022 0.01804 0.75023 0.02237 0.70023 0.02642 0.65020 0.03012 0.60015 0.03338 0.55008 0.03612 0.50000 0.03826 0.44991 0.03972 0.39981 0.04042 0.34970 0.04030 0.29960 0.03926 0.24950 0.03736 0.19941 0.03451 0.14934 0.03058 0.09930 0.02526 0.07429 0.02189 0.04932 0.01776 0.02438 0.01241 0.01197 0.00876 0.00703 0.00677 0.00458 0.00551 0.00000 0.00000 0.00542 -0.00451 0.00797 -0.00537 0.01303 -0.00662 0.02562 -0.00869 0.05068 -0.01144 0.07571 -0.01341 0.10070 -0.01492 0.15066 -0.01712 0.20059 -0.01859 0.25050 -0.01946 0.30040 -0.01982 0.35030 -0.01970 0.40019 -0.01900 0.45009 -0.01782 0.50000 -0.01620 0.54992 -0.01422 0.59985 -0.01196 0.64980 -0.00952 0.69977 -0.00698 0.74927 -0.00447 0.79978 -0.00212 0.84981 -0.00010 0.89987 0.00134 0.94994 0.00178 1.00000 0.00000 |
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Polars for NACA 63-206 (naca63206-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca63206-il | 50,000 | 9 | 24.2 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca63206-il | 50,000 | 5 | 31.1 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca63206-il | 100,000 | 9 | 43.1 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca63206-il | 100,000 | 5 | 41.5 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca63206-il | 200,000 | 9 | 57 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca63206-il | 200,000 | 5 | 52.4 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca63206-il | 500,000 | 9 | 72.4 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca63206-il | 500,000 | 5 | 58.7 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca63206-il | 1,000,000 | 9 | 80.3 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca63206-il | 1,000,000 | 5 | 69 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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