BE50 (original) (be50-il)
BE50 (original) - Verbitsky BE50 free flight airfoil (original)
| Details | Dat file | Parser | |
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(be50-il) BE50 (original) Verbitsky BE50 free flight airfoil (original) Max thickness 7.3% at 25% chord. Max camber 4.1% at 45% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
BE50 (original) 1.00000 0.00260 0.95000 0.01270 0.90000 0.02276 0.80000 0.03956 0.70000 0.05314 0.60000 0.06489 0.55000 0.06991 0.50000 0.07407 0.45000 0.07783 0.40000 0.07992 0.35000 0.08090 0.30000 0.08126 0.25000 0.08087 0.20000 0.07837 0.15000 0.07308 0.10000 0.06403 0.07500 0.05727 0.05000 0.04838 0.02500 0.03639 0.01500 0.03011 0.01000 0.02600 0.00000 0.01271 0.01000 0.00400 0.01500 0.00274 0.02500 0.00156 0.05000 0.00003 0.07500 0.00000 0.10000 0.00053 0.15000 0.00294 0.20000 0.00571 0.25000 0.00812 0.30000 0.01048 0.35000 0.01310 0.40000 0.01617 0.45000 0.01847 0.50000 0.02021 0.55000 0.02136 0.60000 0.02129 0.70000 0.01936 0.80000 0.01492 0.90000 0.00856 0.95000 0.00471 1.00000 0.00000 |
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Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
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Polars for BE50 (original) (be50-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| be50-il | 50,000 | 9 | 38.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| be50-il | 50,000 | 5 | 43.1 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| be50-il | 100,000 | 9 | 59.7 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| be50-il | 100,000 | 5 | 59.7 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| be50-il | 200,000 | 9 | 79.8 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| be50-il | 200,000 | 5 | 73.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| be50-il | 500,000 | 9 | 102.1 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| be50-il | 500,000 | 5 | 95.4 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| be50-il | 1,000,000 | 9 | 118.2 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| be50-il | 1,000,000 | 5 | 110.1 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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