Falcon (falcon-il)
Falcon - Falcon airfoil used on the Carl Goldberg Falcon 56 Mk II R/C powerplane
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(falcon-il) Falcon Falcon airfoil used on the Carl Goldberg Falcon 56 Mk II R/C powerplane Max thickness 13.7% at 30.6% chord. Max camber 1.6% at 20.5% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
Falcon 1.000000 0.001341 0.997540 0.002771 0.990700 0.005630 0.980370 0.008009 0.966980 0.009693 0.950440 0.011476 0.930640 0.014067 0.907750 0.017515 0.882020 0.021591 0.853700 0.026066 0.823090 0.030766 0.790480 0.035592 0.756160 0.040484 0.720430 0.045383 0.683590 0.050226 0.645940 0.054959 0.607780 0.059549 0.569370 0.063971 0.530990 0.068160 0.492650 0.072038 0.454350 0.075505 0.416380 0.078438 0.378870 0.080744 0.342040 0.082344 0.306090 0.083164 0.271200 0.083128 0.237600 0.082152 0.205490 0.080166 0.175040 0.077132 0.146480 0.073093 0.119990 0.068108 0.095760 0.062165 0.073950 0.055183 0.054680 0.047083 0.038110 0.038051 0.024330 0.028709 0.013380 0.019785 0.005480 0.011706 0.000980 0.004376 0.000000 -.000696 0.000980 -.005669 0.005480 -.012170 0.013380 -.018018 0.024330 -.023266 0.038110 -.028023 0.054680 -.032271 0.073950 -.035913 0.095760 -.038975 0.119990 -.041626 0.146480 -.044049 0.175040 -.046382 0.205490 -.048684 0.237600 -.050851 0.271200 -.052590 0.306090 -.053613 0.342040 -.053923 0.378870 -.053679 0.416380 -.052991 0.454350 -.051900 0.492650 -.050413 0.530990 -.048566 0.569370 -.046410 0.607780 -.043982 0.645940 -.041285 0.683590 -.038292 0.720430 -.035020 0.756160 -.031565 0.790480 -.028055 0.823090 -.024610 0.853700 -.021308 0.882020 -.018186 0.907750 -.015284 0.930640 -.012699 0.950440 -.010626 0.966980 -.009205 0.980370 -.007986 0.990700 -.005860 0.997540 -.003005 1.000000 -.001550 |
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Polars for Falcon (falcon-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| falcon-il | 50,000 | 9 | 22.2 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| falcon-il | 50,000 | 5 | 30.2 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| falcon-il | 100,000 | 9 | 41.3 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| falcon-il | 100,000 | 5 | 44.3 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| falcon-il | 200,000 | 9 | 58.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| falcon-il | 200,000 | 5 | 58.8 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| falcon-il | 500,000 | 9 | 81.8 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| falcon-il | 500,000 | 5 | 78.6 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| falcon-il | 1,000,000 | 9 | 98.6 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| falcon-il | 1,000,000 | 5 | 92.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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