BOEING BACXXX AIRFOIL (bacxxx-il)
BOEING BACXXX AIRFOIL - Boeing Commercial Airplane Company BACXXX Energy Efficient Transport Program airfoil
| Details | Dat file | Parser | |
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(bacxxx-il) BOEING BACXXX AIRFOIL Boeing Commercial Airplane Company BACXXX Energy Efficient Transport Program airfoil Max thickness 11.3% at 35% chord. Max camber 1.4% at 15% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
BOEING BACXXX AIRFOIL
31. 31.
0.0000 0.0000
0.0005 0.0037
0.0010 0.0050
0.0025 0.0078
0.0050 0.0112
0.0150 0.0207
0.0200 0.0242
0.0250 0.0271
0.0375 0.0334
0.0500 0.0384
0.0750 0.0465
0.1000 0.0521
0.1250 0.0566
0.1500 0.0599
0.2000 0.0643
0.2500 0.0665
0.3000 0.0674
0.3500 0.0673
0.4000 0.0667
0.4500 0.0654
0.5000 0.0636
0.5500 0.0613
0.6000 0.0585
0.6500 0.0548
0.7000 0.0503
0.7500 0.0450
0.8000 0.0384
0.8500 0.0307
0.9000 0.0218
0.9500 0.0116
1.0000 0.0004
0.0000 0.0000
0.0005 -.0018
0.0010 -.0027
0.0025 -.0043
0.0050 -.0058
0.0150 -.0098
0.0200 -.0112
0.0250 -.0125
0.0375 -.0152
0.0500 -.0175
0.0750 -.0216
0.1000 -.0254
0.1250 -.0288
0.1500 -.0320
0.2000 -.0375
0.2500 -.0417
0.3000 -.0445
0.3500 -.0458
0.4000 -.0457
0.4500 -.0443
0.5000 -.0417
0.5500 -.0383
0.6000 -.0344
0.6500 -.0303
0.7000 -.0260
0.7500 -.0218
0.8000 -.0174
0.8500 -.0132
0.9000 -.0090
0.9500 -.0047
1.0000 -.0004
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Polars for BOEING BACXXX AIRFOIL (bacxxx-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| bacxxx-il | 50,000 | 9 | 31.2 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| bacxxx-il | 50,000 | 5 | 30.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| bacxxx-il | 100,000 | 9 | 44 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| bacxxx-il | 100,000 | 5 | 42.7 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| bacxxx-il | 200,000 | 9 | 58.4 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| bacxxx-il | 200,000 | 5 | 55.2 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| bacxxx-il | 500,000 | 9 | 75.2 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| bacxxx-il | 500,000 | 5 | 72.8 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| bacxxx-il | 1,000,000 | 9 | 90.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| bacxxx-il | 1,000,000 | 5 | 86.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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