I.S.A. 571 (isa571-il)
I.S.A. 571 - I.S.A. 571 airfoil
| Details | Dat file | Parser | |
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(isa571-il) I.S.A. 571 I.S.A. 571 airfoil Max thickness 7.4% at 30% chord. Max camber 3.6% at 30% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
I.S.A. 571 1.0000 0.0030 0.9500 0.0150 0.9000 0.0250 0.8000 0.0410 0.7000 0.0532 0.6000 0.0632 0.5000 0.0717 0.4000 0.0772 0.3000 0.0802 0.2000 0.0780 0.1500 0.0725 0.1000 0.0640 0.0750 0.0570 0.0500 0.0487 0.0250 0.0355 0.0125 0.0267 0.0000 0.0100 0.0125 0.0024 0.0250 0.0000 0.0500 0.0000 0.0750 0.0000 0.1000 0.0020 0.1500 0.0040 0.2000 0.0055 0.3000 0.0065 0.4000 0.0070 0.5000 0.0070 0.6000 0.0062 0.7000 0.0055 0.8000 0.0044 0.9000 0.0025 0.9500 0.0015 1.0000 0.0000 |
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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 I.S.A. 571 (isa571-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| isa571-il | 50,000 | 9 | 35.4 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| isa571-il | 50,000 | 5 | 39.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| isa571-il | 100,000 | 9 | 51.6 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| isa571-il | 100,000 | 5 | 54.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| isa571-il | 200,000 | 9 | 69.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| isa571-il | 200,000 | 5 | 70.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| isa571-il | 500,000 | 9 | 93.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| isa571-il | 500,000 | 5 | 89.1 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| isa571-il | 1,000,000 | 9 | 109.4 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| isa571-il | 1,000,000 | 5 | 100.5 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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