S3016-095-87 (s3016-il)
S3016-095-87 - Selig S3016 low Reynolds number airfoil
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(s3016-il) S3016-095-87 Selig S3016 low Reynolds number airfoil Max thickness 9.5% at 28.9% chord. Max camber 1.8% at 43.1% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
S3016-095-87 1.00000 0.00000 0.99664 0.00017 0.98669 0.00085 0.97048 0.00233 0.94843 0.00476 0.92107 0.00821 0.88898 0.01266 0.85274 0.01798 0.81299 0.02400 0.77035 0.03047 0.72541 0.03706 0.67865 0.04337 0.63040 0.04917 0.58106 0.05437 0.53112 0.05885 0.48109 0.06252 0.43144 0.06528 0.38265 0.06707 0.33517 0.06783 0.28946 0.06755 0.24593 0.06624 0.20504 0.06396 0.16726 0.06066 0.13288 0.05631 0.10216 0.05092 0.07529 0.04459 0.05240 0.03743 0.03358 0.02964 0.01892 0.02146 0.00839 0.01321 0.00203 0.00544 0.00007 -.00095 0.00391 -.00606 0.01386 -.01088 0.02891 -.01543 0.04888 -.01941 0.07362 -.02271 0.10296 -.02526 0.13666 -.02705 0.17444 -.02807 0.21598 -.02839 0.26085 -.02810 0.30857 -.02729 0.35862 -.02604 0.41044 -.02442 0.46345 -.02251 0.51705 -.02040 0.57061 -.01816 0.62352 -.01588 0.67514 -.01363 0.72484 -.01147 0.77202 -.00946 0.81607 -.00763 0.85645 -.00602 0.89264 -.00462 0.92414 -.00344 0.95055 -.00242 0.97154 -.00148 0.98700 -.00063 0.99668 -.00012 1.00000 0.00000 |
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Polars for S3016-095-87 (s3016-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s3016-il | 50,000 | 9 | 31.8 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3016-il | 50,000 | 5 | 34.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3016-il | 100,000 | 9 | 49.2 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3016-il | 100,000 | 5 | 48.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3016-il | 200,000 | 9 | 65.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3016-il | 200,000 | 5 | 61 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3016-il | 500,000 | 9 | 85.5 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3016-il | 500,000 | 5 | 78.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3016-il | 1,000,000 | 9 | 99.1 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3016-il | 1,000,000 | 5 | 93.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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