TSAGI 12% AIRFOIL (tsagi12-il)
TSAGI 12% AIRFOIL - TSAGI 12% airfoil
| Details | Dat file | Parser | |
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(tsagi12-il) TSAGI 12% AIRFOIL TSAGI 12% airfoil Max thickness 11.9% at 30% chord. Max camber 2% at 30% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
TSAGI 12% AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125000 0.0167000
0.0250000 0.0248000
0.0500000 0.0371000
0.0750000 0.0462000
0.1000000 0.0538000
0.1500000 0.0652000
0.2000000 0.0728000
0.3000000 0.0794000
0.4000000 0.0770000
0.5000000 0.0698000
0.6000000 0.0581000
0.7000000 0.0443000
0.8000000 0.0294000
0.9000000 0.0147000
0.9500000 0.0073000
1.0000000 0.0000000
0.0000000 0.0000000
0.0125000 -.0127000
0.0250000 -.0178000
0.0500000 -.0242000
0.0750000 -.0277000
0.1000000 -.0308000
0.1500000 -.0347000
0.2000000 -.0370000
0.3000000 -.0396000
0.4000000 -.0407000
0.5000000 -.0402000
0.6000000 -.0384000
0.7000000 -.0342000
0.8000000 -.0275000
0.9000000 -.0168000
0.9500000 -.0097000
1.0000000 0.0000000
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Similar airfoils
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Polars for TSAGI 12% AIRFOIL (tsagi12-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| tsagi12-il | 50,000 | 9 | 31.4 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| tsagi12-il | 50,000 | 5 | 32.3 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| tsagi12-il | 100,000 | 9 | 49.6 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| tsagi12-il | 100,000 | 5 | 49.7 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| tsagi12-il | 200,000 | 9 | 66.6 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| tsagi12-il | 200,000 | 5 | 65.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| tsagi12-il | 500,000 | 9 | 88.5 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| tsagi12-il | 500,000 | 5 | 76.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| tsagi12-il | 1,000,000 | 9 | 91.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| tsagi12-il | 1,000,000 | 5 | 86.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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