PT40 (pt40-il)
PT40 - Great Plane PT-40 trainer airfoil
| Details | Dat file | Parser | |
|
(pt40-il) PT40 Great Plane PT-40 trainer airfoil Max thickness 11.6% at 27.1% chord. Max camber 2.9% at 41.6% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
PT40 1.000000 0.001356 0.997540 0.001963 0.990700 0.003687 0.980370 0.006189 0.966980 0.009283 0.950440 0.012906 0.930640 0.016996 0.907750 0.021447 0.882020 0.026182 0.853700 0.031153 0.823090 0.036316 0.790480 0.041628 0.756160 0.047029 0.720430 0.052435 0.683590 0.057749 0.645940 0.062857 0.607780 0.067611 0.569370 0.071880 0.530990 0.075601 0.492650 0.078789 0.454350 0.081431 0.416380 0.083445 0.378870 0.084740 0.342040 0.085252 0.306090 0.084987 0.271200 0.084026 0.237600 0.082474 0.205490 0.080395 0.175040 0.077784 0.146480 0.074578 0.119990 0.070658 0.095760 0.065886 0.073950 0.060130 0.054680 0.053385 0.038110 0.046061 0.024330 0.038699 0.013380 0.030716 0.005480 0.020620 0.000980 0.008495 0.000000 -0.000736 0.000980 -0.009818 0.005480 -0.021336 0.013380 -0.030819 0.024330 -0.037450 0.038110 -0.040671 0.054680 -0.041138 0.073950 -0.040299 0.095760 -0.039114 0.119990 -0.037979 0.146480 -0.036898 0.175040 -0.035785 0.205490 -0.034591 0.237600 -0.033303 0.271200 -0.031924 0.306090 -0.030468 0.342040 -0.028957 0.378870 -0.027409 0.416380 -0.025838 0.454350 -0.024252 0.492650 -0.022652 0.530990 -0.021046 0.569370 -0.019428 0.607780 -0.017799 0.645940 -0.016172 0.683590 -0.014562 0.720430 -0.012988 0.756160 -0.011467 0.790480 -0.010016 0.823090 -0.008651 0.853700 -0.007383 0.882020 -0.006223 0.907750 -0.005176 0.930640 -0.004246 0.950440 -0.003437 0.966980 -0.002751 0.980370 -0.002186 0.990700 -0.001745 0.997540 -0.001453 1.000000 -0.001348 |
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
|
Polars for PT40 (pt40-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| pt40-il | 50,000 | 9 | 32.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pt40-il | 50,000 | 5 | 33.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| pt40-il | 100,000 | 9 | 48.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pt40-il | 100,000 | 5 | 46.3 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| pt40-il | 200,000 | 9 | 64.3 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pt40-il | 200,000 | 5 | 57.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| pt40-il | 500,000 | 9 | 78.8 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pt40-il | 500,000 | 5 | 76.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| pt40-il | 1,000,000 | 9 | 95 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pt40-il | 1,000,000 | 5 | 89.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||