FX 66-182 AIRFOIL (fx66182-il)
FX 66-182 AIRFOIL - Wortmann FX 66-182 airfoil
| Details | Dat file | Parser | |
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(fx66182-il) FX 66-182 AIRFOIL Wortmann FX 66-182 airfoil Max thickness 18.2% at 33.9% chord. Max camber 3.8% at 37.1% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
FX 66-182 AIRFOIL
44. 44.
0.0000000 0.0000000
0.0010700 0.0061600
0.0042800 0.0121100
0.0096100 0.0186600
0.0170400 0.0268600
0.0265300 0.0349200
0.0380600 0.0433500
0.0515600 0.0520100
0.0669900 0.0607600
0.0842700 0.0694900
0.1033200 0.0780500
0.1240800 0.0863500
0.1464500 0.0942600
0.1703300 0.1016900
0.1956200 0.1085000
0.2222100 0.1146000
0.2500000 0.1198400
0.2786600 0.1240900
0.3086600 0.1270500
0.3392800 0.1287400
0.3705900 0.1289700
0.4024500 0.1277400
0.4347400 0.1249200
0.4673000 0.1206500
0.5000000 0.1151200
0.5327000 0.1087300
0.5652600 0.1018500
0.5975500 0.0947600
0.6294100 0.0875500
0.6607200 0.0803200
0.6913400 0.0731500
0.7211400 0.0661400
0.7500000 0.0593400
0.7777900 0.0528200
0.8043801 0.0466200
0.8296700 0.0407800
0.8535500 0.0353100
0.8759201 0.0302600
0.9157300 0.0213900
0.9484400 0.0139600
0.9734700 0.0075900
0.9903900 0.0025800
0.9989300 0.0001600
1.0000000 0.0000000
0.0000000 0.0000000
0.0010700 -.0034000
0.0042800 -.0074100
0.0096100 -.0115800
0.0170400 -.0151400
0.0265300 -.0191100
0.0380600 -.0229800
0.0515600 -.0267400
0.0669900 -.0303500
0.0842700 -.0337900
0.1033200 -.0370200
0.1240800 -.0400400
0.1464500 -.0428000
0.1703300 -.0453200
0.1956200 -.0475200
0.2222100 -.0494400
0.2500000 -.0509800
0.2786600 -.0521800
0.3086600 -.0529200
0.3392800 -.0532100
0.3705900 -.0528800
0.4024500 -.0519800
0.4347400 -.0503700
0.4673000 -.0479600
0.5000000 -.0446400
0.5327000 -.0405000
0.5652600 -.0357300
0.5975500 -.0307200
0.6294100 -.0257500
0.6607200 -.0211200
0.6913400 -.0169300
0.7211400 -.0132600
0.7500000 -.0101000
0.7777900 -.0074400
0.8043801 -.0052200
0.8296700 -.0034200
0.8535500 -.0020100
0.8759201 -.0009700
0.9157300 0.0001900
0.9484400 0.0006300
0.9734700 0.0006800
0.9903900 0.0005100
0.9989300 0.0001600
1.0000000 0.0000000
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Polars for FX 66-182 AIRFOIL (fx66182-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx66182-il | 50,000 | 9 | 4.7 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66182-il | 50,000 | 5 | 8.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66182-il | 100,000 | 9 | 5.9 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66182-il | 100,000 | 5 | 30.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66182-il | 200,000 | 9 | 61.8 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66182-il | 200,000 | 5 | 67.9 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66182-il | 500,000 | 9 | 107.3 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66182-il | 500,000 | 5 | 104.4 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66182-il | 1,000,000 | 9 | 134.6 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66182-il | 1,000,000 | 5 | 128.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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