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

FX 67-K-170/17 AIRFOIL (fx67k170-il)

FX 67-K-170/17 AIRFOIL - Wortmann FX 67-K-170/17 airfoil


Airfoil fx67k170-il
Details Dat file Parser  
(fx67k170-il) FX 67-K-170/17 AIRFOIL
Wortmann FX 67-K-170/17 airfoil
Max thickness 17% at 40.2% chord.
Max camber 5.1% at 43.5% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
FX 67-K-170/17 AIRFOIL
       44.       44.

 0.0000000 0.0000000
 0.0010700 0.0065300
 0.0042800 0.0129200
 0.0096100 0.0201200
 0.0170400 0.0276500
 0.0265300 0.0348700
 0.0380600 0.0430900
 0.0515600 0.0515800
 0.0669900 0.0601100
 0.0842700 0.0685600
 0.1033200 0.0768500
 0.1240800 0.0849000
 0.1464500 0.0926300
 0.1703300 0.0999400
 0.1956200 0.1067700
 0.2222100 0.1130500
 0.2500000 0.1187000
 0.2788600 0.1236500
 0.3086600 0.1278300
 0.3392800 0.1311900
 0.3705900 0.1337000
 0.4024500 0.1352600
 0.4347400 0.1357100
 0.4673000 0.1349000
 0.5000000 0.1327400
 0.5327000 0.1291900
 0.5652600 0.1242900
 0.5975500 0.1180800
 0.6294100 0.1106300
 0.6607200 0.1020800
 0.6913400 0.0926300
 0.7211400 0.0825900
 0.7500000 0.0723300
 0.7777900 0.0622900
 0.8043801 0.0528700
 0.8296700 0.0443700
 0.8535500 0.0368900
 0.8759201 0.0304000
 0.9157300 0.0199100
 0.9484400 0.0120100
 0.9734700 0.0063100
 0.9903900 0.0024300
 0.9989300 0.0002700
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0010700 -.0021700
 0.0042800 -.0051400
 0.0096100 -.0081500
 0.0170400 -.0105700
 0.0265300 -.0132100
 0.0380600 -.0158000
 0.0515600 -.0182700
 0.0669900 -.0206200
 0.0842700 -.0228200
 0.1033200 -.0249000
 0.1240800 -.0268200
 0.1464500 -.0285600
 0.1703300 -.0301100
 0.1956200 -.0314600
 0.2222100 -.0326100
 0.2500000 -.0335400
 0.2788600 -.0342500
 0.3086600 -.0347400
 0.3392800 -.0349900
 0.3705900 -.0350100
 0.4024500 -.0348000
 0.4347400 -.0343500
 0.4673000 -.0336500
 0.5000000 -.0327200
 0.5327000 -.0315500
 0.5652600 -.0301200
 0.5975500 -.0284400
 0.6294100 -.0265400
 0.6607200 -.0243700
 0.6913400 -.0218700
 0.7211400 -.0189600
 0.7500000 -.0157200
 0.7777900 -.0123600
 0.8043801 -.0091300
 0.8296700 -.0062500
 0.8535500 -.0038600
 0.8759201 -.0019700
 0.9157300 0.0003700
 0.9484400 0.0012400
 0.9734700 0.0010500
 0.9903900 0.0004400
 0.9989300 0.0000500
 1.0000000 0.0000000
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

GOE 423 AIRFOILPreviewDetails
WORTMANN FX 73-170 APreviewDetails
EPPLER 654 AIRFOILPreviewDetails
EPPLER 584 AIRFOILPreviewDetails
EPPLER 656 AIRFOILPreviewDetails
EPPLER 583 AIRFOILPreviewDetails
FX 84-W-175PreviewDetails
WORTMANN FX 057-816PreviewDetails
AH 95-160PreviewDetails
WORTMANN FX 08-S-176 AIRFOILPreviewDetails

Polars for FX 67-K-170/17 AIRFOIL (fx67k170-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   fx67k170-il50,00095 at α=11.75°Mach=0 Ncrit=9Xfoil predictionDetails
   fx67k170-il50,000511.8 at α=14.75°Mach=0 Ncrit=5Xfoil predictionDetails
   fx67k170-il100,000920.1 at α=13.5°Mach=0 Ncrit=9Xfoil predictionDetails
   fx67k170-il100,000519.9 at α=12.5°Mach=0 Ncrit=5Xfoil predictionDetails
   fx67k170-il200,000936.6 at α=11.5°Mach=0 Ncrit=9Xfoil predictionDetails
   fx67k170-il200,000548.2 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   fx67k170-il500,0009116.9 at α=8°Mach=0 Ncrit=9Xfoil predictionDetails
   fx67k170-il500,0005111.4 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   fx67k170-il1,000,0009152.7 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   fx67k170-il1,000,0005141.3 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit