FX 66-S-171 AIRFOIL (fx66s171-il)
FX 66-S-171 AIRFOIL - Wortmann FX 66-S-171 airfoil
| Details | Dat file | Parser | |
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(fx66s171-il) FX 66-S-171 AIRFOIL Wortmann FX 66-S-171 airfoil Max thickness 17.1% 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-171 AIRFOIL
44. 44.
0.0000000 0.0000000
0.0010700 0.0056800
0.0042800 0.0116100
0.0096100 0.0184000
0.0170400 0.0259600
0.0265300 0.0340500
0.0380600 0.0424600
0.0515600 0.0511100
0.0669900 0.0597900
0.0842700 0.0684300
0.1033200 0.0768400
0.1240800 0.0849700
0.1464500 0.0926400
0.1703300 0.0998000
0.1956200 0.1062300
0.2222100 0.1118700
0.2500000 0.1164400
0.2786600 0.1199100
0.3086600 0.1221300
0.3392800 0.1233100
0.3705900 0.1230500
0.4024500 0.1214700
0.4347400 0.1182800
0.4673000 0.1139200
0.5000000 0.1085900
0.5327000 0.1027500
0.5652600 0.0962800
0.5975500 0.0895600
0.6294100 0.0826600
0.6607200 0.0758200
0.6913400 0.0690100
0.7211400 0.0623600
0.7500000 0.0559400
0.7777900 0.0497700
0.8043801 0.0438600
0.8296700 0.0383400
0.8535500 0.0331000
0.8759201 0.0282800
0.9157300 0.0197300
0.9484400 0.0126600
0.9734700 0.0069700
0.9903900 0.0026700
0.9989300 0.0003200
1.0000000 0.0000000
0.0000000 0.0000000
0.0010700 -.0034800
0.0042800 -.0074400
0.0096100 -.0115000
0.0170400 -.0154700
0.0265300 -.0194200
0.0380600 -.0232300
0.0515600 -.0269500
0.0669900 -.0304500
0.0842700 -.0338100
0.1033200 -.0368800
0.1240800 -.0397600
0.1464500 -.0422800
0.1703300 -.0445500
0.1956200 -.0463800
0.2222100 -.0479100
0.2500000 -.0489000
0.2786600 -.0492900
0.3086600 -.0487500
0.3392800 -.0477800
0.3705900 -.0460900
0.4024500 -.0438200
0.4347400 -.0405800
0.4673000 -.0368300
0.5000000 -.0327000
0.5327000 -.0286900
0.5652600 -.0246700
0.5975500 -.0209200
0.6294100 -.0172500
0.6607200 -.0139600
0.6913400 -.0109400
0.7211400 -.0083100
0.7500000 -.0059800
0.7777900 -.0039900
0.8043801 -.0023000
0.8296700 -.0010200
0.8535500 0.0000200
0.8759201 0.0006800
0.9157300 0.0013800
0.9484400 0.0013700
0.9734700 0.0010400
0.9903900 0.0005600
0.9989300 0.0001100
1.0000000 0.0000000
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Polars for FX 66-S-171 AIRFOIL (fx66s171-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx66s171-il | 50,000 | 9 | 5 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66s171-il | 50,000 | 5 | 12.7 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66s171-il | 100,000 | 9 | 13.3 at α=1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66s171-il | 100,000 | 5 | 39.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66s171-il | 200,000 | 9 | 70.3 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66s171-il | 200,000 | 5 | 72.4 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66s171-il | 500,000 | 9 | 113.9 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66s171-il | 500,000 | 5 | 113.4 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66s171-il | 1,000,000 | 9 | 147.6 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66s171-il | 1,000,000 | 5 | 133.8 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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