FX 66-S-196 AIRFOIL (fx66s196-il)
FX 66-S-196 AIRFOIL - Wortmann FX 66-S-196 airfoil
| Details | Dat file | Parser | |
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(fx66s196-il) FX 66-S-196 AIRFOIL Wortmann FX 66-S-196 airfoil Max thickness 19.6% at 37.1% chord. Max camber 3.8% at 43.5% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
FX 66-S-196 AIRFOIL
44. 44.
0.0000000 0.0000000
0.0010700 0.0064400
0.0042800 0.0123900
0.0096100 0.0194100
0.0170400 0.0270000
0.0265300 0.0352300
0.0380600 0.0436200
0.0515600 0.0524000
0.0669900 0.0610800
0.0842700 0.0699000
0.1033200 0.0784100
0.1240800 0.0868400
0.1464500 0.0947600
0.1703300 0.1024100
0.1956200 0.1093700
0.2222100 0.1158700
0.2500000 0.1215000
0.2786600 0.1265100
0.3086600 0.1304400
0.3392800 0.1335100
0.3705900 0.1352300
0.4024500 0.1356700
0.4347400 0.1343000
0.4673000 0.1314500
0.5000000 0.1267200
0.5327000 0.1209800
0.5652600 0.1141400
0.5975500 0.1068300
0.6294100 0.0988600
0.6607200 0.0908100
0.6913400 0.0825100
0.7211400 0.0744700
0.7500000 0.0664700
0.7777900 0.0588300
0.8043801 0.0513400
0.8296700 0.0444200
0.8535500 0.0378000
0.8759201 0.0318500
0.9157300 0.0214200
0.9484400 0.0131300
0.9734700 0.0069300
0.9903900 0.0025600
0.9989300 0.0002200
1.0000000 0.0000000
0.0000000 0.0000000
0.0010700 -.0034100
0.0042800 -.0079000
0.0096100 -.0122100
0.0170400 -.0166800
0.0265300 -.0209700
0.0380600 -.0253700
0.0515600 -.0295000
0.0669900 -.0336500
0.0842700 -.0374700
0.1033200 -.0412600
0.1240800 -.0446800
0.1464500 -.0481000
0.1703300 -.0508900
0.1956200 -.0536300
0.2222100 -.0558800
0.2500000 -.0579000
0.2786600 -.0593700
0.3086600 -.0605300
0.3392800 -.0610400
0.3705900 -.0611100
0.4024500 -.0602900
0.4347400 -.0587700
0.4673000 -.0568100
0.5000000 -.0520500
0.5327000 -.0471500
0.5652600 -.0419400
0.5975500 -.0364600
0.6294100 -.0313000
0.6607200 -.0262500
0.6913400 -.0215800
0.7211400 -.0171700
0.7500000 -.0133800
0.7777900 -.0098600
0.8043801 -.0069500
0.8296700 -.0043400
0.8535500 -.0023100
0.8759201 -.0005600
0.9157300 0.0015100
0.9484400 0.0021000
0.9734700 0.0015000
0.9903900 0.0002600
0.9989300 -.0003800
1.0000000 0.0000000
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Polars for FX 66-S-196 AIRFOIL (fx66s196-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx66s196-il | 50,000 | 9 | 4.5 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66s196-il | 50,000 | 5 | 9.5 at α=16° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66s196-il | 100,000 | 9 | 14.8 at α=14.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66s196-il | 100,000 | 5 | 20 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66s196-il | 200,000 | 9 | 37.2 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66s196-il | 200,000 | 5 | 59.7 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66s196-il | 500,000 | 9 | 105.4 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66s196-il | 500,000 | 5 | 103.5 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66s196-il | 1,000,000 | 9 | 137.4 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66s196-il | 1,000,000 | 5 | 130.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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