Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

Falcon (falcon-il)

Falcon - Falcon airfoil used on the Carl Goldberg Falcon 56 Mk II R/C powerplane


Airfoil falcon-il
Details Dat file Parser  
(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
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

Gottingen 765 airfoil (recovered).PreviewDetails
EPPLER 326 AIRFOILPreviewDetails
EPPLER 340 AIRFOILPreviewDetails
GOE 617 AIRFOILPreviewDetails
EPPLER 327 AIRFOILPreviewDetails
MH 106 13.07%PreviewDetails
EPPLER 325 AIRFOILPreviewDetails
FAUVEL 14% AIRFOILPreviewDetails
EPPLER 335 AIRFOILPreviewDetails
MH 91 14.98%PreviewDetails

Polars for Falcon (falcon-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   falcon-il50,000922.2 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   falcon-il50,000530.2 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   falcon-il100,000941.3 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   falcon-il100,000544.3 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   falcon-il200,000958.1 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   falcon-il200,000558.8 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
   falcon-il500,000981.8 at α=7°Mach=0 Ncrit=9Xfoil predictionDetails
   falcon-il500,000578.6 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
   falcon-il1,000,000998.6 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   falcon-il1,000,000592.4 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit