NACA 64A410 (naca64a410-il)
NACA 64A410 - NACA 64A410 airfoil
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(naca64a410-il) NACA 64A410 NACA 64A410 airfoil Max thickness 10% at 39.9% chord. Max camber 2.7% at 50% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
NACA 64A410 1.00000 0.00021 0.95053 0.01028 0.90104 0.02038 0.85148 0.03018 0.80151 0.03967 0.75126 0.04780 0.70108 0.05480 0.65085 0.06106 0.60057 0.06624 0.55025 0.07040 0.49989 0.07344 0.44950 0.07522 0.39910 0.07552 0.34871 0.07414 0.29834 0.07131 0.24800 0.06705 0.19770 0.06126 0.14748 0.05366 0.09737 0.04380 0.07230 0.03865 0.04749 0.03034 0.02276 0.02095 0.01059 0.01451 0.00582 0.01112 0.00350 0.00902 0.00000 0.00000 0.00650 -0.00678 0.00918 -0.00796 0.01441 -0.00969 0.02724 -0.01251 0.05251 -0.01592 0.07770 -0.01919 0.10263 -0.01996 0.15252 -0.02244 0.20230 -0.02406 0.25200 -0.02499 0.30166 -0.02537 0.35129 -0.02518 0.40090 -0.02436 0.45050 -0.02266 0.50011 -0.02024 0.54975 -0.01736 0.59943 -0.01418 0.64915 -0.01086 0.69892 -0.00760 0.74874 -0.00460 0.79849 -0.00229 0.84852 -0.00132 0.89896 -0.00076 0.94947 -0.00048 1.00000 -0.00021 |
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Polars for NACA 64A410 (naca64a410-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca64a410-il | 50,000 | 9 | 38.1 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca64a410-il | 50,000 | 5 | 37.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca64a410-il | 100,000 | 9 | 58.2 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca64a410-il | 100,000 | 5 | 55.5 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca64a410-il | 200,000 | 9 | 79 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca64a410-il | 200,000 | 5 | 71.3 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca64a410-il | 500,000 | 9 | 100.7 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca64a410-il | 500,000 | 5 | 75.2 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca64a410-il | 1,000,000 | 9 | 98.6 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca64a410-il | 1,000,000 | 5 | 80.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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