NACA 63A210 (naca63a210-il)
NACA 63A210 - NACA 63A210 airfoil
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(naca63a210-il) NACA 63A210 NACA 63A210 airfoil Max thickness 10% at 34.9% chord. Max camber 1.3% at 50% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
NACA 63A210 1.00000 0.00021 0.95026 0.00769 0.90050 0.01519 0.85072 0.02254 0.80074 0.02974 0.75061 0.03624 0.70052 0.04227 0.65041 0.04772 0.60028 0.05245 0.55012 0.05637 0.49994 0.05943 0.44975 0.06151 0.39955 0.06247 0.34935 0.06219 0.29916 0.06060 0.24898 0.05764 0.19882 0.05328 0.14869 0.04729 0.09863 0.03917 0.07364 0.03400 0.04869 0.02769 0.02384 0.01944 0.01151 0.01367 0.00664 0.01058 0.00423 0.00868 0.00000 0.00000 0.00577 -0.00756 0.00836 -0.00900 0.01349 -0.01125 0.02616 -0.01522 0.05131 -0.02047 0.07636 -0.02428 0.10137 -0.02725 0.15131 -0.03167 0.20118 -0.03468 0.25102 -0.03662 0.30084 -0.03764 0.35065 -0.03771 0.40045 -0.03689 0.45025 -0.03523 0.50006 -0.03283 0.54988 -0.02985 0.59972 -0.02641 0.64959 -0.02262 0.69948 -0.01861 0.74939 -0.01464 0.79926 -0.01104 0.84928 -0.00812 0.89950 -0.00539 0.94974 -0.00279 1.00000 -0.00021 |
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Polars for NACA 63A210 (naca63a210-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca63a210-il | 50,000 | 9 | 28.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca63a210-il | 50,000 | 5 | 31.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca63a210-il | 100,000 | 9 | 37.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca63a210-il | 100,000 | 5 | 40.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca63a210-il | 200,000 | 9 | 44.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca63a210-il | 200,000 | 5 | 48.3 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca63a210-il | 500,000 | 9 | 52 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca63a210-il | 500,000 | 5 | 58.3 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca63a210-il | 1,000,000 | 9 | 58.5 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca63a210-il | 1,000,000 | 5 | 70.4 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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