NACA 747A315 (naca747a315-il)
NACA 747A315 - NACA 747A315 airfoil
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(naca747a315-il) NACA 747A315 NACA 747A315 airfoil Max thickness 15% at 40.2% chord. Max camber 2.5% at 35% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
NACA 747A315 1.00000 0.00000 0.95004 0.00481 0.90016 0.01289 0.85038 0.02257 0.80073 0.03295 0.75130 0.04336 0.70241 0.05354 0.65366 0.06365 0.60435 0.07324 0.55463 0.08206 0.50447 0.08964 0.45375 0.09572 0.40200 0.09962 0.35001 0.09982 0.29867 0.09731 0.24758 0.09242 0.19668 0.08503 0.14599 0.07497 0.09558 0.06140 0.07053 0.05286 0.04564 0.04264 0.02109 0.02935 0.00911 0.02065 0.00449 0.01599 0.00229 0.01305 0.00000 0.00000 0.00771 -0.01031 0.01051 -0.01207 0.01589 -0.01473 0.02891 -0.01927 0.05436 -0.02518 0.07947 -0.02952 0.10442 -0.03304 0.15401 -0.03843 0.20332 -0.04247 0.25242 -0.04546 0.30133 -0.04773 0.34999 -0.04926 0.39800 -0.05020 0.44625 -0.05040 0.49553 -0.05014 0.54537 -0.04930 0.59565 -0.04772 0.64634 -0.04509 0.69759 -0.04110 0.74870 -0.03502 0.79927 -0.02743 0.84962 -0.01915 0.89984 -0.01097 0.94996 -0.00405 1.00000 0.00000 |
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Polars for NACA 747A315 (naca747a315-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca747a315-il | 50,000 | 9 | 20.2 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca747a315-il | 50,000 | 5 | 17.3 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca747a315-il | 100,000 | 9 | 44.4 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca747a315-il | 100,000 | 5 | 46.4 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca747a315-il | 200,000 | 9 | 72 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca747a315-il | 200,000 | 5 | 61.6 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca747a315-il | 500,000 | 9 | 89.8 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca747a315-il | 500,000 | 5 | 85.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca747a315-il | 1,000,000 | 9 | 111.5 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca747a315-il | 1,000,000 | 5 | 100.3 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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