NACA 64(3)-218 (naca643218-il)
NACA 64(3)-218 - NACA 64(3)-218 airfoil
| Details | Dat file | Parser | |
|
(naca643218-il) NACA 64(3)-218 NACA 64(3)-218 airfoil Max thickness 18% at 34.9% chord. Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
NACA 64(3)-218 1.00000 0.00000 0.95019 0.00716 0.90038 0.01617 0.85054 0.02623 0.80064 0.03683 0.75068 0.04760 0.70065 0.05814 0.65057 0.06812 0.60043 0.07729 0.55024 0.08540 0.50000 0.09217 0.44972 0.09725 0.39942 0.10023 0.34912 0.10009 0.29881 0.09760 0.24853 0.09285 0.19828 0.08576 0.14808 0.07612 0.09797 0.06316 0.07297 0.05496 0.04804 0.04497 0.02325 0.03186 0.01099 0.02279 0.00617 0.01785 0.00380 0.01473 0.00000 0.00000 0.00620 -0.01373 0.00883 -0.01645 0.01401 -0.02065 0.02675 -0.02814 0.05196 -0.03865 0.07703 -0.04648 0.10203 -0.05282 0.15192 -0.06266 0.20172 -0.06984 0.25147 -0.07495 0.30119 -0.07816 0.35088 -0.07949 0.40058 -0.07881 0.45028 -0.07535 0.50000 -0.07011 0.54976 -0.06350 0.59957 -0.05587 0.64943 -0.04752 0.69935 -0.03870 0.74936 -0.02970 0.79936 -0.02091 0.84946 -0.01277 0.89962 -0.00583 0.94981 -0.00084 1.00000 0.00000 |
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
|
Polars for NACA 64(3)-218 (naca643218-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca643218-il | 50,000 | 9 | 21.9 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca643218-il | 50,000 | 5 | 18 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca643218-il | 100,000 | 9 | 41.5 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca643218-il | 100,000 | 5 | 39.7 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca643218-il | 200,000 | 9 | 62.3 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca643218-il | 200,000 | 5 | 60.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca643218-il | 500,000 | 9 | 89.6 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca643218-il | 500,000 | 5 | 78.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca643218-il | 1,000,000 | 9 | 106.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca643218-il | 1,000,000 | 5 | 88.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||