NACA 2.5411 (naca2411-il)
NACA 2.5411 - NACA 2411 airfoil
| Details | Dat file | Parser | |
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(naca2411-il) NACA 2.5411 NACA 2411 airfoil Max thickness 11% at 29.5% chord. Max camber 2.5% at 39.6% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
NACA 2.5411 1.00000 0.00000 0.99730 0.00059 0.98918 0.00235 0.97578 0.00520 0.95720 0.00906 0.93365 0.01380 0.90535 0.01927 0.87260 0.02532 0.83577 0.03175 0.79520 0.03839 0.75138 0.04506 0.70475 0.05158 0.65583 0.05777 0.60513 0.06347 0.55322 0.06852 0.50067 0.07276 0.44807 0.07606 0.39597 0.07830 0.34455 0.07912 0.29485 0.07831 0.24745 0.07588 0.20292 0.07193 0.16175 0.06659 0.12448 0.06006 0.09148 0.05253 0.06317 0.04427 0.03985 0.03553 0.02170 0.02654 0.00897 0.01752 0.00172 0.00862 0.00000 0.00000 0.00375 -0.00794 0.01290 -0.01483 0.02723 -0.02061 0.04662 -0.02531 0.07080 -0.02893 0.09948 -0.03151 0.13238 -0.03310 0.16912 -0.03379 0.20932 -0.03368 0.25255 -0.03291 0.29842 -0.03165 0.34642 -0.03005 0.39612 -0.02830 0.44740 -0.02637 0.49933 -0.02415 0.55132 -0.02174 0.60280 -0.01925 0.65320 -0.01677 0.70198 -0.01436 0.74862 -0.01208 0.79257 -0.00994 0.83337 -0.00798 0.87053 -0.00621 0.90368 -0.00463 0.93238 -0.00326 0.95633 -0.00211 0.97528 -0.00120 0.98895 -0.00054 0.99723 -0.00013 1.00000 0.00000 |
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Polars for NACA 2.5411 (naca2411-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca2411-il | 50,000 | 9 | 34.3 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2411-il | 50,000 | 5 | 35.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2411-il | 100,000 | 9 | 52.9 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2411-il | 100,000 | 5 | 52.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2411-il | 200,000 | 9 | 71.2 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2411-il | 200,000 | 5 | 67.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2411-il | 500,000 | 9 | 95.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2411-il | 500,000 | 5 | 86.6 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2411-il | 1,000,000 | 9 | 113.7 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2411-il | 1,000,000 | 5 | 97.7 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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