DU 86-137/25 AIRFOIL (du861372-il)
DU 86-137/25 AIRFOIL - Delft University DU 86-137/25 Airfoil
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(du861372-il) DU 86-137/25 AIRFOIL Delft University DU 86-137/25 Airfoil Max thickness 13.6% at 41.6% chord. Max camber 0.3% at 1.6% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
DU 86-137/25 AIRFOIL
24.0 17.0
0.0000000 0.0000000
0.0013248 0.0050461
0.0044717 0.0094186
0.0095787 0.0138426
0.0164958 0.0183179
0.0251730 0.0227745
0.0476677 0.0314815
0.0766932 0.0397133
0.1117794 0.0472594
0.1524067 0.0538597
0.1980050 0.0593335
0.2979470 0.0635972
0.3014651 0.0664599
0.3577769 0.0679714
0.4159799 0.0680342
0.4455118 0.0674958
0.5048665 0.0652194
0.5929860 0.0585138
0.6500642 0.0514254
0.7050142 0.0415553
0.7622559 0.0296667
0.8168343 0.0220965
0.9074373 0.0107725
1.0000000 0.0000000
0.0000000 0.0000000
0.0028942 -.0076934
0.0075974 -.0116402
0.0143074 -.0112452
0.0451316 -.0284035
0.0740791 -.0365126
0.1029262 -.0441418
0.1499337 -.0511076
0.2453367 -.0620680
0.2985821 -.0656890
0.3545166 -.0678380
0.4123400 -.0684256
0.6177524 -.0571940
0.7016879 -.0452816
0.8077582 -.0247126
0.9012113 -.0086931
1.0000000 0.0000000
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Polars for DU 86-137/25 AIRFOIL (du861372-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| du861372-il | 50,000 | 9 | 28.9 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| du861372-il | 50,000 | 5 | 23.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| du861372-il | 100,000 | 9 | 33.4 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| du861372-il | 100,000 | 5 | 27.1 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| du861372-il | 200,000 | 9 | 32.8 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| du861372-il | 200,000 | 5 | 35.5 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| du861372-il | 500,000 | 9 | 46.7 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| du861372-il | 500,000 | 5 | 48.9 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| du861372-il | 1,000,000 | 9 | 58.4 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| du861372-il | 1,000,000 | 5 | 59.9 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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