WORTMANN FX 05-188 AIRFOIL (fx05188-il)
WORTMANN FX 05-188 AIRFOIL - Wortmann FX 05-188 airfoil
| Details | Dat file | Parser | |
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(fx05188-il) WORTMANN FX 05-188 AIRFOIL Wortmann FX 05-188 airfoil Max thickness 18.8% 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 05-188 AIRFOIL
25.0 25.0
0.0000000 0.0000000
0.0042800 0.0140100
0.0170400 0.0270500
0.0380600 0.0416400
0.0669900 0.0559900
0.1033300 0.0706900
0.1464400 0.0844100
0.1956200 0.0967800
0.2500000 0.1070800
0.3086600 0.1146200
0.3705900 0.1186500
0.4347400 0.1193400
0.5000000 0.1159000
0.5652600 0.1087400
0.6294100 0.0979700
0.6913400 0.0834800
0.7500000 0.0687800
0.8043800 0.0533800
0.8535600 0.0401200
0.8966700 0.0289400
0.9330100 0.0195100
0.9616400 0.0121200
0.9829600 0.0061600
0.9957200 0.0020200
1.0000000 0.0000000
0.0000000 0.0000000
0.0042800 -.0111500
0.0170400 -.0197800
0.0380600 -.0286000
0.0669900 -.0372200
0.1033300 -.0456000
0.1464400 -.0531700
0.1956200 -.0598600
0.2500000 -.0651900
0.3086600 -.0686400
0.3705900 -.0695000
0.4347400 -.0680700
0.5000000 -.0634800
0.5652600 -.0563300
0.6294100 -.0463000
0.6913400 -.0328400
0.7500000 -.0204300
0.8043800 -.0088900
0.8535600 -.0009300
0.8966700 0.0036400
0.9330100 0.0054600
0.9616400 0.0049100
0.9829600 0.0033900
0.9957200 0.0011800
1.0000000 0.0000000
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Polars for WORTMANN FX 05-188 AIRFOIL (fx05188-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx05188-il | 50,000 | 9 | 17.1 at α=14.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx05188-il | 50,000 | 5 | 14.2 at α=13° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx05188-il | 100,000 | 9 | 27.8 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx05188-il | 100,000 | 5 | 29.4 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx05188-il | 200,000 | 9 | 60.5 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx05188-il | 200,000 | 5 | 64.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx05188-il | 500,000 | 9 | 99.5 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx05188-il | 500,000 | 5 | 97.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx05188-il | 1,000,000 | 9 | 126.9 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx05188-il | 1,000,000 | 5 | 117.9 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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