WORTMANN FX 05-191 AIRFOIL (fx05191-il)
WORTMANN FX 05-191 AIRFOIL - Wortmann FX 05-191 airfoil
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(fx05191-il) WORTMANN FX 05-191 AIRFOIL Wortmann FX 05-191 airfoil Max thickness 19.1% at 37.1% chord. Max camber 2.6% at 50% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
WORTMANN FX 05-191 AIRFOIL
25.0 25.0
0.0000000 0.0000000
0.0042800 0.0131300
0.0170400 0.0269600
0.0380600 0.0414100
0.0669900 0.0555800
0.1033300 0.0702000
0.1464400 0.0839900
0.1956200 0.0964800
0.2500000 0.1071300
0.3086600 0.1151600
0.3705900 0.1199800
0.4347400 0.1209100
0.5000000 0.1179800
0.5652600 0.1117000
0.6294100 0.1026600
0.6913400 0.0912800
0.7500000 0.0764200
0.8043800 0.0597500
0.8535600 0.0445200
0.8966700 0.0316100
0.9330100 0.0204300
0.9616400 0.0124200
0.9829600 0.0060800
0.9957200 0.0019100
1.0000000 0.0000000
0.0000000 0.0000000
0.0042800 -.0102700
0.0170400 -.0196800
0.0380600 -.0283700
0.0669900 -.0368100
0.1033300 -.0451000
0.1464400 -.0527600
0.1956200 -.0595700
0.2500000 -.0652500
0.3086600 -.0691800
0.3705900 -.0708300
0.4347400 -.0696400
0.5000000 -.0655700
0.5652600 -.0592900
0.6294100 -.0509900
0.6913400 -.0406400
0.7500000 -.0280800
0.8043800 -.0152600
0.8535600 -.0053200
0.8966700 0.0009700
0.9330100 0.0045400
0.9616400 0.0046000
0.9829600 0.0034700
0.9957200 0.0012900
1.0000000 0.0000000
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Polars for WORTMANN FX 05-191 AIRFOIL (fx05191-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx05191-il | 50,000 | 9 | 18.1 at α=13.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx05191-il | 50,000 | 5 | 14 at α=13° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx05191-il | 100,000 | 9 | 27.6 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx05191-il | 100,000 | 5 | 29.2 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx05191-il | 200,000 | 9 | 55.6 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx05191-il | 200,000 | 5 | 57.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx05191-il | 500,000 | 9 | 89.4 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx05191-il | 500,000 | 5 | 89.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx05191-il | 1,000,000 | 9 | 118.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx05191-il | 1,000,000 | 5 | 112.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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