NACA 747A415 (naca747a415-il)
NACA 747A415 - NACA 747A415 airfoil
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(naca747a415-il) NACA 747A415 NACA 747A415 airfoil Max thickness 15% at 40.2% chord. Max camber 3% at 35% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
NACA 747A415 1.00000 0.00000 0.95015 0.00639 0.90037 0.01546 0.85066 0.02592 0.80107 0.03692 0.75164 0.04783 0.70273 0.05838 0.65393 0.06878 0.60454 0.07859 0.55474 0.08753 0.50447 0.09516 0.45364 0.10121 0.40176 0.10499 0.34964 0.10497 0.29818 0.10216 0.24698 0.09687 0.19598 0.08897 0.14521 0.07827 0.09476 0.06390 0.06972 0.05488 0.04487 0.04411 0.02041 0.03016 0.00852 0.02106 0.00398 0.01622 0.00183 0.01318 0.00000 0.00000 0.00817 -0.00994 0.01102 -0.01160 0.01648 -0.01406 0.02959 -0.01822 0.05513 -0.02349 0.08028 -0.02730 0.10524 -0.03038 0.15479 -0.03501 0.20402 -0.03845 0.25302 -0.04095 0.30182 -0.04286 0.35036 -0.04411 0.39824 -0.04485 0.44636 -0.04493 0.49553 -0.04462 0.54526 -0.04381 0.59546 -0.04235 0.64607 -0.03992 0.69727 -0.03622 0.74836 -0.03053 0.79893 -0.02344 0.84934 -0.01578 0.89963 -0.00838 0.94985 -0.00247 1.00000 0.00000 |
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Polars for NACA 747A415 (naca747a415-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca747a415-il | 50,000 | 9 | 19 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca747a415-il | 50,000 | 5 | 17 at α=1° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca747a415-il | 100,000 | 9 | 37.4 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca747a415-il | 100,000 | 5 | 44.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca747a415-il | 200,000 | 9 | 73.8 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca747a415-il | 200,000 | 5 | 66.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca747a415-il | 500,000 | 9 | 97.5 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca747a415-il | 500,000 | 5 | 92.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca747a415-il | 1,000,000 | 9 | 120.6 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca747a415-il | 1,000,000 | 5 | 110.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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