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

FX 66-S-161 AIRFOIL (fx66s161-il)

FX 66-S-161 AIRFOIL - Wortmann FX 66-S-161 airfoil


Airfoil fx66s161-il
Details Dat file Parser  
(fx66s161-il) FX 66-S-161 AIRFOIL
Wortmann FX 66-S-161 airfoil
Max thickness 16.1% at 33.9% chord.
Max camber 3.9% at 43.5% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
FX 66-S-161 AIRFOIL
       44.       44.

 0.0000000 0.0000000
 0.0010700 0.0053600
 0.0042800 0.0110500
 0.0096100 0.0175500
 0.0170400 0.0248300
 0.0265300 0.0326100
 0.0380600 0.0407100
 0.0515600 0.0490300
 0.0669900 0.0573900
 0.0842700 0.0657100
 0.1033200 0.0738200
 0.1240800 0.0816500
 0.1464500 0.0890300
 0.1703300 0.0959200
 0.1956200 0.1021200
 0.2222100 0.1075500
 0.2500000 0.1119600
 0.2786600 0.1153100
 0.3086600 0.1174800
 0.3392800 0.1186400
 0.3705900 0.1184200
 0.4024500 0.1169400
 0.4347400 0.1139100
 0.4673000 0.1097600
 0.5000000 0.1046800
 0.5327000 0.0991000
 0.5652600 0.0929200
 0.5975500 0.0864900
 0.6294100 0.0798700
 0.6607200 0.0733200
 0.6913400 0.0667800
 0.7211400 0.0604000
 0.7500000 0.0542300
 0.7777900 0.0482800
 0.8043801 0.0425900
 0.8296700 0.0372600
 0.8535500 0.0321900
 0.8759201 0.0275300
 0.9157300 0.0192400
 0.9484400 0.0123600
 0.9734700 0.0068200
 0.9903900 0.0026200
 0.9989300 0.0003200
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0010700 -.0033000
 0.0042800 -.0070300
 0.0096100 -.0107900
 0.0170400 -.0144100
 0.0265300 -.0179900
 0.0380600 -.0214200
 0.0515600 -.0247400
 0.0669900 -.0278600
 0.0842700 -.0308300
 0.1033200 -.0335400
 0.1240800 -.0360600
 0.1464500 -.0382600
 0.1703300 -.0402200
 0.1956200 -.0417800
 0.2222100 -.0430600
 0.2500000 -.0438700
 0.2786600 -.0441100
 0.3086600 -.0435100
 0.3392800 -.0425300
 0.3705900 -.0409000
 0.4024500 -.0387600
 0.4347400 -.0357200
 0.4673000 -.0322400
 0.5000000 -.0284000
 0.5327000 -.0247000
 0.5652600 -.0210100
 0.5975500 -.0175800
 0.6294100 -.0142400
 0.6607200 -.0112500
 0.6913400 -.0085300
 0.7211400 -.0061800
 0.7500000 -.0041200
 0.7777900 -.0023700
 0.8043801 -.0009100
 0.8296700 0.0001600
 0.8535500 0.0010100
 0.8759201 0.0015100
 0.9157300 0.0019300
 0.9484400 0.0017100
 0.9734700 0.0012200
 0.9903900 0.0006200
 0.9989300 0.0001100
 1.0000000 0.0000000
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

FX 63-158 AIRFOILPreviewDetails
EPPLER 855 AIRFOILPreviewDetails
FX S 02/1-158 AIRFOILPreviewDetails
AH 93-156PreviewDetails
AH 83-159PreviewDetails
GOE 425 AIRFOILPreviewDetails
HORSTMANN AND QUAST HQ-300 GD(MOD 2)PreviewDetails
EPPLER 432 AIRFOILPreviewDetails
FX 66-S-171 AIRFOILPreviewDetails
AH 93-157PreviewDetails

Polars for FX 66-S-161 AIRFOIL (fx66s161-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   fx66s161-il50,00095.3 at α=9°Mach=0 Ncrit=9Xfoil predictionDetails
   fx66s161-il50,000516.2 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
   fx66s161-il100,000916.6 at α=2°Mach=0 Ncrit=9Xfoil predictionDetails
   fx66s161-il100,000542.4 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   fx66s161-il200,000973.8 at α=10°Mach=0 Ncrit=9Xfoil predictionDetails
   fx66s161-il200,000575.7 at α=9.25°Mach=0 Ncrit=5Xfoil predictionDetails
   fx66s161-il500,0009116 at α=8.5°Mach=0 Ncrit=9Xfoil predictionDetails
   fx66s161-il500,0005114.9 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
   fx66s161-il1,000,0009148.7 at α=7.5°Mach=0 Ncrit=9Xfoil predictionDetails
   fx66s161-il1,000,0005134.5 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit