BOEING 103 AIRFOIL (boe103-il)
BOEING 103 AIRFOIL - Boeing 103 airfoil
| Details | Dat file | Parser | |
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(boe103-il) BOEING 103 AIRFOIL Boeing 103 airfoil Max thickness 12.7% at 30% chord. Max camber 3.6% at 40% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
BOEING 103 AIRFOIL
18. 17.
0.0000000 0.0000000
0.0125000 0.0265900
0.0187500 0.0345800
0.0250000 0.0397700
0.0500000 0.0555000
0.0750000 0.0653000
0.1000000 0.0730000
0.1500000 0.0845000
0.2000000 0.0920000
0.3000000 0.0984800
0.4000000 0.0984400
0.5000000 0.0922000
0.6000000 0.0809600
0.7000000 0.0661200
0.8000000 0.0476800
0.9000000 0.0266400
0.9500000 0.0151200
1.0000000 0.0012000
0.0000000 0.0000000
0.0125000 -.0130000
0.0250000 -.0169600
0.0500000 -.0223200
0.0750000 -.0255000
0.1000000 -.0272400
0.1500000 -.0285600
0.2000000 -.0288800
0.3000000 -.0287200
0.4000000 -.0265000
0.5000000 -.0228000
0.6000000 -.0184400
0.7000000 -.0134800
0.8000000 -.0089200
0.9000000 -.0043600
0.9500000 -.0020800
1.0000000 0.0000000
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Polars for BOEING 103 AIRFOIL (boe103-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| boe103-il | 50,000 | 9 | 32.6 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| boe103-il | 50,000 | 5 | 35 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| boe103-il | 100,000 | 9 | 53.1 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| boe103-il | 100,000 | 5 | 52.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| boe103-il | 200,000 | 9 | 72 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| boe103-il | 200,000 | 5 | 66.6 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| boe103-il | 500,000 | 9 | 94.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| boe103-il | 500,000 | 5 | 81.1 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| boe103-il | 1,000,000 | 9 | 107.9 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| boe103-il | 1,000,000 | 5 | 89 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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