NACA 64(3)-618 (naca643618-il)
NACA 64(3)-618 - NACA 64(3)-618 airfoil
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(naca643618-il) NACA 64(3)-618 NACA 64(3)-618 airfoil Max thickness 17.9% at 34.7% chord. Max camber 3.3% at 50% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
NACA 64(3)-618 1.00000 0.00000 0.95056 0.01344 0.90115 0.02646 0.85161 0.03963 0.80191 0.05270 0.75203 0.06544 0.70196 0.07754 0.65171 0.08870 0.60129 0.09870 0.55071 0.10730 0.50000 0.11423 0.44917 0.11915 0.39827 0.12163 0.34735 0.12065 0.29645 0.11698 0.24560 0.11065 0.19486 0.10153 0.14427 0.08937 0.09395 0.07322 0.06895 0.06312 0.04417 0.05093 0.01982 0.03518 0.00805 0.02452 0.00359 0.01885 0.00150 0.01534 0.00000 0.00000 0.00850 -0.01234 0.01141 -0.01465 0.01695 -0.01810 0.03018 -0.02402 0.05583 -0.03197 0.08105 -0.03769 0.10605 -0.04220 0.15573 -0.04899 0.20514 -0.05377 0.25440 -0.05695 0.30355 -0.05866 0.35265 -0.05885 0.40173 -0.05737 0.45083 -0.05345 0.50000 -0.04805 0.54929 -0.04160 0.59871 -0.03444 0.64829 -0.02690 0.69804 -0.01922 0.74797 -0.01174 0.79809 -0.00494 0.84839 0.00075 0.89885 0.00456 0.94944 0.00552 1.00000 0.00000 |
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Polars for NACA 64(3)-618 (naca643618-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca643618-il | 50,000 | 9 | 18.6 at α=13° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca643618-il | 50,000 | 5 | 14.9 at α=12.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca643618-il | 100,000 | 9 | 31.8 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca643618-il | 100,000 | 5 | 41.8 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca643618-il | 200,000 | 9 | 74.3 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca643618-il | 200,000 | 5 | 73.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca643618-il | 500,000 | 9 | 109.9 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca643618-il | 500,000 | 5 | 103.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca643618-il | 1,000,000 | 9 | 136.3 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca643618-il | 1,000,000 | 5 | 124.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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