SELIG 3002-099-83 (s3002-il)
SELIG 3002-099-83 - Selig S3002 low Reynolds number airfoil
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(s3002-il) SELIG 3002-099-83 Selig S3002 low Reynolds number airfoil Max thickness 9.9% at 30.6% chord. Max camber 2.3% at 49.8% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
SELIG 3002-099-83 1.00000 0.00000 0.99676 0.00048 0.98723 0.00205 0.97191 0.00483 0.95131 0.00867 0.92576 0.01330 0.89553 0.01862 0.86104 0.02463 0.82286 0.03124 0.78161 0.03825 0.73787 0.04538 0.69214 0.05226 0.64481 0.05868 0.59634 0.06441 0.54711 0.06930 0.49758 0.07328 0.44820 0.07627 0.39944 0.07823 0.35178 0.07915 0.30572 0.07900 0.26173 0.07776 0.22026 0.07537 0.18165 0.07181 0.14619 0.06711 0.11417 0.06135 0.08583 0.05460 0.06135 0.04701 0.04087 0.03873 0.02450 0.03000 0.01234 0.02105 0.00440 0.01211 0.00048 0.00360 0.00051 -.00333 0.00602 -.00831 0.01778 -.01223 0.03507 -.01544 0.05763 -.01796 0.08522 -.01976 0.11761 -.02087 0.15449 -.02145 0.19537 -.02159 0.23976 -.02136 0.28711 -.02078 0.33684 -.01988 0.38835 -.01869 0.44102 -.01717 0.49424 -.01527 0.54750 -.01294 0.60027 -.01020 0.65199 -.00697 0.70250 -.00311 0.75186 0.00081 0.79932 0.00382 0.84366 0.00550 0.88373 0.00590 0.91863 0.00527 0.94770 0.00402 0.97052 0.00257 0.98688 0.00125 0.99672 0.00033 1.00000 0.00000 |
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Polars for SELIG 3002-099-83 (s3002-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s3002-il | 50,000 | 9 | 35.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3002-il | 50,000 | 5 | 39.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3002-il | 100,000 | 9 | 56.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3002-il | 100,000 | 5 | 55.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3002-il | 200,000 | 9 | 76.6 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3002-il | 200,000 | 5 | 70.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3002-il | 500,000 | 9 | 99.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3002-il | 500,000 | 5 | 89.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3002-il | 1,000,000 | 9 | 112.5 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3002-il | 1,000,000 | 5 | 100.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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