NACA 63(2)-215 MOD B (n63215b-il)
NACA 63(2)-215 MOD B - NACA-NASA/AMES/Hicks 63(2)-215 MOD B airfoil
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(n63215b-il) NACA 63(2)-215 MOD B NACA-NASA/AMES/Hicks 63(2)-215 MOD B airfoil Max thickness 15% at 30% chord. Max camber 1.5% at 10% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
NACA 63(2)-215 MOD B 60.0000 60.0000 0.0 0.0 0.0002 0.0034 0.0004 0.0051 0.0006 0.0064 0.0008 0.0075 0.0010 0.0085 0.0020 0.0125 0.0030 0.0156 0.0040 0.0182 0.0050 0.0205 0.0100 0.0293 0.0200 0.0408 0.0300 0.0489 0.0400 0.0550 0.0500 0.0599 0.0600 0.0640 0.0700 0.0673 0.0800 0.0702 0.0900 0.0727 0.1000 0.0748 0.1250 0.0788 0.1500 0.0816 0.1750 0.0835 0.2000 0.0847 0.2250 0.0855 0.2500 0.0859 0.2750 0.0860 0.3000 0.0859 0.3250 0.0856 0.3500 0.0853 0.3750 0.0852 0.4000 0.0845 0.4250 0.0835 0.4500 0.0819 0.4750 0.0800 0.5000 0.0777 0.5250 0.0750 0.5500 0.0720 0.5750 0.0688 0.6000 0.0653 0.6250 0.0615 0.6500 0.0576 0.6750 0.0534 0.7000 0.0491 0.7250 0.0447 0.7500 0.0402 0.7750 0.0357 0.8000 0.0311 0.8250 0.0266 0.8500 0.0222 0.8750 0.0179 0.9000 0.0137 0.9250 0.0098 0.9500 0.0062 0.9600 0.0048 0.9700 0.0036 0.9800 0.0023 0.9900 0.0012 0.9950 0.0006 1.0000 0.0000 0.0 0.0 0.0002 -.0011 0.0004 -.0022 0.0006 -.0031 0.0008 -.0037 0.0010 -.0042 0.0020 -.0063 0.0030 -.0079 0.0040 -.0093 0.0050 -.0104 0.0100 -.0150 0.0200 -.0211 0.0300 -.0256 0.0400 -.0294 0.0500 -.0328 0.0600 -.0357 0.0700 -.0384 0.0800 -.0408 0.0900 -.0430 0.1000 -.0450 0.1250 -.0494 0.1500 -.0531 0.1750 -.0562 0.2000 -.0588 0.2250 -.0609 0.2500 -.0625 0.2750 -.0637 0.3000 -.0645 0.3250 -.0648 0.3500 -.0647 0.3750 -.0641 0.4000 -.0632 0.4250 -.0618 0.4500 -.0601 0.4750 -.0580 0.5000 -.0556 0.5250 -.0530 0.5500 -.0501 0.5750 -.0470 0.6000 -.0438 0.6250 -.0404 0.6500 -.0368 0.6750 -.0332 0.7000 -.0295 0.7250 -.0258 0.7500 -.0221 0.7750 -.0185 0.8000 -.0150 0.8250 -.0117 0.8500 -.0086 0.8750 -.0058 0.9000 -.0033 0.9250 -.0013 0.9500 0.0001 0.9600 0.0005 0.9700 0.0007 0.9800 0.0008 0.9900 0.0006 0.9950 0.0003 1.0000 0.0000 |
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Polars for NACA 63(2)-215 MOD B (n63215b-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| n63215b-il | 50,000 | 9 | 25.9 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63215b-il | 50,000 | 5 | 24.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63215b-il | 100,000 | 9 | 32.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63215b-il | 100,000 | 5 | 35.3 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63215b-il | 200,000 | 9 | 44.4 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63215b-il | 200,000 | 5 | 47.9 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63215b-il | 500,000 | 9 | 66.4 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63215b-il | 500,000 | 5 | 68.3 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63215b-il | 1,000,000 | 9 | 86.3 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63215b-il | 1,000,000 | 5 | 83.9 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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