TRAINER60 (trainer60-il)
TRAINER60 - Great Planes R/C Trainer 60 airfoil
| Details | Dat file | Parser | |
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(trainer60-il) TRAINER60 Great Planes R/C Trainer 60 airfoil Max thickness 18.3% at 27.1% chord. Max camber 0.1% at 1.3% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
TRAINER60 1.000000 0.003185 0.997540 0.005714 0.990700 0.010009 0.980370 0.011484 0.966980 0.010387 0.950440 0.010252 0.930640 0.010684 0.907750 0.012469 0.882020 0.016609 0.853700 0.021789 0.823090 0.027109 0.790480 0.032331 0.756160 0.037557 0.720430 0.042964 0.683590 0.048611 0.645940 0.054465 0.607780 0.060510 0.569370 0.066568 0.530990 0.072239 0.492650 0.077322 0.454350 0.081829 0.416380 0.085729 0.378870 0.088950 0.342040 0.091378 0.306090 0.092819 0.271200 0.093034 0.237600 0.091969 0.205490 0.089867 0.175040 0.086976 0.146480 0.083240 0.119990 0.078439 0.095760 0.072371 0.073950 0.065050 0.054680 0.056881 0.038110 0.048398 0.024330 0.039859 0.013380 0.031019 0.005480 0.021182 0.000980 0.009788 0.000000 0.001166 0.000980 -0.007076 0.005480 -0.017397 0.013380 -0.026742 0.024330 -0.035600 0.038110 -0.044257 0.054680 -0.052773 0.073950 -0.060946 0.095760 -0.068412 0.119990 -0.074764 0.146480 -0.079792 0.175040 -0.083671 0.205490 -0.086674 0.237600 -0.088864 0.271200 -0.090048 0.306090 -0.090043 0.342040 -0.088848 0.378870 -0.086658 0.416380 -0.083707 0.454350 -0.080022 0.492650 -0.075530 0.530990 -0.070300 0.569370 -0.064622 0.607780 -0.058941 0.645940 -0.053447 0.683590 -0.048006 0.720430 -0.042495 0.756160 -0.037036 0.790480 -0.031861 0.823090 -0.026990 0.853700 -0.022223 0.882020 -0.017468 0.907750 -0.013184 0.930640 -0.010637 0.950440 -0.011123 0.966980 -0.013591 0.980370 -0.014815 0.990700 -0.012156 0.997540 -0.006587 0.999997 -0.003499 |
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
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Polars for TRAINER60 (trainer60-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| trainer60-il | 50,000 | 9 | 15.3 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| trainer60-il | 50,000 | 5 | 24.5 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| trainer60-il | 100,000 | 9 | 36.7 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| trainer60-il | 100,000 | 5 | 38.8 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| trainer60-il | 200,000 | 9 | 51.7 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| trainer60-il | 200,000 | 5 | 50.9 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| trainer60-il | 500,000 | 9 | 73.1 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| trainer60-il | 500,000 | 5 | 65.8 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| trainer60-il | 1,000,000 | 9 | 85.4 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| trainer60-il | 1,000,000 | 5 | 79.3 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||