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-196 V1 AIRFOIL (fx66196v-il)

FX 66-S-196 V1 AIRFOIL - Wortmann FX 66-S-196 V1 airfoil


Airfoil fx66196v-il
Details Dat file Parser  
(fx66196v-il) FX 66-S-196 V1 AIRFOIL
Wortmann FX 66-S-196 V1 airfoil
Max thickness 19.6% at 37.1% chord.
Max camber 4% at 46.7% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
FX 66-S-196 V1 AIRFOIL
       44.       44.

 0.0000000 0.0000000
 0.0010700 0.0062100
 0.0042800 0.0122300
 0.0096100 0.0191800
 0.0170200 0.0269200
 0.0265300 0.0352000
 0.0380600 0.0438300
 0.0515600 0.0527300
 0.0669900 0.0617000
 0.0842700 0.0706700
 0.1033200 0.0794600
 0.1240800 0.0880300
 0.1464500 0.0962100
 0.1703300 0.1039800
 0.1956200 0.1111400
 0.2222100 0.1177200
 0.2500000 0.1234800
 0.2786600 0.1284800
 0.3086600 0.1324300
 0.3392800 0.1353700
 0.3705900 0.1369000
 0.4024500 0.1369100
 0.4347400 0.1346700
 0.4673000 0.1309500
 0.5000000 0.1258500
 0.5327000 0.1199500
 0.5652600 0.1132100
 0.5975500 0.1060700
 0.6294100 0.0984400
 0.6607200 0.0906700
 0.6913400 0.0827200
 0.7211400 0.0748200
 0.7500000 0.0669900
 0.7777900 0.0593600
 0.8043801 0.0519700
 0.8296700 0.0450100
 0.8535500 0.0384500
 0.8759201 0.0324200
 0.9157300 0.0219300
 0.9484400 0.0135700
 0.9734700 0.0072900
 0.9903900 0.0028400
 0.9989300 0.0003900
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0010700 -.0035400
 0.0042800 -.0078400
 0.0096100 -.0121100
 0.0170400 -.0163900
 0.0265300 -.0206500
 0.0380600 -.0248900
 0.0515600 -.0290300
 0.0669900 -.0330700
 0.0842700 -.0369500
 0.1033200 -.0406300
 0.1240800 -.0441000
 0.1464500 -.0472900
 0.1703300 -.0502200
 0.1956200 -.0527900
 0.2222100 -.0550300
 0.2500000 -.0568100
 0.2786600 -.0582000
 0.3086600 -.0590100
 0.3392800 -.0593100
 0.3705900 -.0588000
 0.4024500 -.0574300
 0.4347400 -.0545100
 0.4673000 -.0507600
 0.5000000 -.0462800
 0.5327000 -.0416100
 0.5652600 -.0366700
 0.5975500 -.0318600
 0.6294100 -.0270700
 0.6607200 -.0225600
 0.6913400 -.0182700
 0.7211400 -.0143500
 0.7500000 -.0108000
 0.7777900 -.0076400
 0.8043801 -.0048900
 0.8296700 -.0026000
 0.8535500 -.0006800
 0.8759201 0.0008000
 0.9157300 0.0025400
 0.9484400 0.0028800
 0.9734700 0.0020600
 0.9903900 0.0006600
 0.9989300 -.0001700
 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 66-S-196 AIRFOILPreviewDetails
FX S 02-196 AIRFOILPreviewDetails
HAM-STD HS1-620 AIRFOILPreviewDetails
NACA 5-H-20 AIRFOILPreviewDetails
EPPLER 1098 AIRFOILPreviewDetails
EPPLER 604 AIRFOILPreviewDetails
WORTMANN FX 66-17AII-182 AIRFOIL (ASPreviewDetails
GOE 424 AIRFOILPreviewDetails
GOE 420 AIRFOILPreviewDetails
EPPLER 603 AIRFOILPreviewDetails

Polars for FX 66-S-196 V1 AIRFOIL (fx66196v-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   fx66196v-il50,00094.6 at α=10.75°Mach=0 Ncrit=9Xfoil predictionDetails
   fx66196v-il50,00057.8 at α=12°Mach=0 Ncrit=5Xfoil predictionDetails
   fx66196v-il100,00095.7 at α=9.25°Mach=0 Ncrit=9Xfoil predictionDetails
   fx66196v-il100,000526.3 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   fx66196v-il200,000949.9 at α=11°Mach=0 Ncrit=9Xfoil predictionDetails
   fx66196v-il200,000561.6 at α=9.5°Mach=0 Ncrit=5Xfoil predictionDetails
   fx66196v-il500,0009110.1 at α=9.5°Mach=0 Ncrit=9Xfoil predictionDetails
   fx66196v-il500,0005104.5 at α=8.5°Mach=0 Ncrit=5Xfoil predictionDetails
   fx66196v-il1,000,0009139 at α=9°Mach=0 Ncrit=9Xfoil predictionDetails
   fx66196v-il1,000,0005132.7 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit