FX 66-S-161 AIRFOIL (fx66s161-il)
FX 66-S-161 AIRFOIL - Wortmann FX 66-S-161 airfoil
| Details | Dat file | Parser | |
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(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
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Polars for FX 66-S-161 AIRFOIL (fx66s161-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx66s161-il | 50,000 | 9 | 5.3 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66s161-il | 50,000 | 5 | 16.2 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66s161-il | 100,000 | 9 | 16.6 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66s161-il | 100,000 | 5 | 42.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66s161-il | 200,000 | 9 | 73.8 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66s161-il | 200,000 | 5 | 75.7 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66s161-il | 500,000 | 9 | 116 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66s161-il | 500,000 | 5 | 114.9 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66s161-il | 1,000,000 | 9 | 148.7 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66s161-il | 1,000,000 | 5 | 134.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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