S3016-095-87 (s3016-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: S3016-095-87 (s3016-il) Reynolds number: 50,000 Max Cl/Cd: 34.93 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s3016-il-50000-n5.txt Download as CSV file: xf-s3016-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S3016-095-87
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4879 0.08952 0.08287 -0.0269 1.0000 0.0437
-8.750 -0.4868 0.08519 0.07859 -0.0289 1.0000 0.0434
-8.500 -0.4886 0.08046 0.07394 -0.0318 1.0000 0.0430
-8.250 -0.4933 0.07553 0.06906 -0.0351 1.0000 0.0426
-8.000 -0.4978 0.07069 0.06422 -0.0377 1.0000 0.0422
-7.750 -0.5027 0.06583 0.05929 -0.0400 1.0000 0.0420
-7.500 -0.5060 0.06116 0.05449 -0.0416 1.0000 0.0419
-7.250 -0.5076 0.05661 0.04972 -0.0424 1.0000 0.0422
-7.000 -0.5069 0.05238 0.04516 -0.0425 1.0000 0.0428
-6.750 -0.5042 0.04851 0.04084 -0.0417 1.0000 0.0436
-6.500 -0.4989 0.04507 0.03710 -0.0404 1.0000 0.0445
-6.250 -0.4906 0.04232 0.03417 -0.0388 1.0000 0.0458
-6.000 -0.4808 0.03956 0.03105 -0.0370 1.0000 0.0466
-5.750 -0.4692 0.03702 0.02817 -0.0352 1.0000 0.0475
-5.500 -0.4558 0.03467 0.02547 -0.0333 1.0000 0.0487
-5.250 -0.4407 0.03265 0.02309 -0.0315 1.0000 0.0513
-5.000 -0.4239 0.03090 0.02085 -0.0298 1.0000 0.0553
-4.750 -0.4067 0.02913 0.01892 -0.0282 1.0000 0.0586
-4.500 -0.3884 0.02765 0.01728 -0.0266 1.0000 0.0616
-4.250 -0.3692 0.02633 0.01574 -0.0250 1.0000 0.0653
-4.000 -0.3499 0.02514 0.01431 -0.0233 1.0000 0.0703
-3.750 -0.3313 0.02423 0.01333 -0.0220 1.0000 0.0806
-3.500 -0.3114 0.02327 0.01232 -0.0208 1.0000 0.0942
-3.250 -0.2904 0.02219 0.01132 -0.0199 1.0000 0.1180
-3.000 -0.2592 0.02088 0.01059 -0.0216 0.9944 0.2192
-2.750 -0.2284 0.01976 0.01035 -0.0231 0.9866 0.3923
-2.500 -0.1995 0.01901 0.01022 -0.0231 0.9784 0.5477
-2.250 -0.1694 0.01850 0.01023 -0.0224 0.9711 0.7069
-2.000 -0.1003 0.01826 0.01011 -0.0284 0.9699 0.9149
-1.750 -0.0352 0.01830 0.00966 -0.0361 0.9653 1.0000
-1.500 0.0060 0.01846 0.00945 -0.0394 0.9560 1.0000
-1.250 0.0425 0.01861 0.00931 -0.0417 0.9450 1.0000
-1.000 0.0798 0.01877 0.00919 -0.0441 0.9342 1.0000
-0.750 0.1190 0.01892 0.00912 -0.0467 0.9242 1.0000
-0.500 0.1593 0.01906 0.00907 -0.0493 0.9144 1.0000
-0.250 0.1915 0.01922 0.00907 -0.0503 0.9021 1.0000
0.000 0.2230 0.01937 0.00910 -0.0511 0.8896 1.0000
0.250 0.2538 0.01953 0.00915 -0.0517 0.8768 1.0000
0.500 0.2836 0.01967 0.00920 -0.0519 0.8636 1.0000
0.750 0.3124 0.01980 0.00926 -0.0519 0.8500 1.0000
1.000 0.3402 0.01992 0.00932 -0.0516 0.8360 1.0000
1.250 0.3671 0.02002 0.00938 -0.0510 0.8213 1.0000
1.500 0.3935 0.02009 0.00942 -0.0503 0.8061 1.0000
1.750 0.4196 0.02014 0.00944 -0.0494 0.7904 1.0000
2.000 0.4454 0.02017 0.00945 -0.0484 0.7744 1.0000
2.250 0.4710 0.02017 0.00945 -0.0472 0.7583 1.0000
2.500 0.4934 0.02027 0.00956 -0.0458 0.7394 1.0000
2.750 0.5174 0.02030 0.00961 -0.0444 0.7211 1.0000
3.000 0.5424 0.02028 0.00962 -0.0431 0.7031 1.0000
3.250 0.5656 0.02035 0.00971 -0.0417 0.6825 1.0000
3.500 0.5899 0.02036 0.00973 -0.0403 0.6618 1.0000
3.750 0.6134 0.02044 0.00982 -0.0388 0.6393 1.0000
4.000 0.6379 0.02047 0.00988 -0.0374 0.6166 1.0000
4.250 0.6610 0.02063 0.01005 -0.0360 0.5910 1.0000
4.500 0.6841 0.02082 0.01023 -0.0346 0.5643 1.0000
4.750 0.7071 0.02106 0.01044 -0.0332 0.5365 1.0000
5.000 0.7297 0.02137 0.01077 -0.0318 0.5079 1.0000
5.250 0.7518 0.02176 0.01111 -0.0305 0.4787 1.0000
5.500 0.7736 0.02222 0.01152 -0.0291 0.4498 1.0000
5.750 0.7949 0.02276 0.01202 -0.0279 0.4214 1.0000
6.000 0.8159 0.02337 0.01260 -0.0266 0.3942 1.0000
6.250 0.8367 0.02405 0.01330 -0.0254 0.3682 1.0000
6.500 0.8573 0.02478 0.01401 -0.0243 0.3443 1.0000
6.750 0.8775 0.02556 0.01477 -0.0231 0.3212 1.0000
7.000 0.8976 0.02640 0.01566 -0.0221 0.2994 1.0000
7.250 0.9173 0.02728 0.01653 -0.0209 0.2791 1.0000
7.500 0.9370 0.02822 0.01753 -0.0199 0.2599 1.0000
7.750 0.9559 0.02920 0.01866 -0.0187 0.2411 1.0000
8.000 0.9745 0.03024 0.01975 -0.0176 0.2240 1.0000
8.250 0.9926 0.03131 0.02087 -0.0165 0.2080 1.0000
8.500 1.0102 0.03248 0.02214 -0.0153 0.1927 1.0000
8.750 1.0266 0.03370 0.02350 -0.0140 0.1777 1.0000
9.000 1.0431 0.03501 0.02492 -0.0128 0.1646 1.0000
9.250 1.0576 0.03634 0.02636 -0.0115 0.1517 1.0000
9.500 1.0711 0.03778 0.02800 -0.0101 0.1396 1.0000
9.750 1.0836 0.03943 0.02988 -0.0086 0.1282 1.0000
10.000 1.0931 0.04113 0.03178 -0.0070 0.1173 1.0000
10.250 1.1020 0.04296 0.03377 -0.0054 0.1080 1.0000
10.500 1.1087 0.04459 0.03536 -0.0037 0.0993 1.0000
10.750 1.1085 0.04682 0.03797 -0.0016 0.0910 1.0000
11.000 1.1099 0.04896 0.04018 0.0002 0.0844 1.0000
11.250 1.1061 0.05149 0.04297 0.0018 0.0780 1.0000
11.500 1.1041 0.05401 0.04553 0.0030 0.0726 1.0000
11.750 1.0960 0.05760 0.04947 0.0038 0.0682 1.0000
12.000 1.0908 0.06043 0.05235 0.0041 0.0638 1.0000
12.250 1.0827 0.06423 0.05629 0.0039 0.0607 1.0000
12.500 1.0668 0.06941 0.06181 0.0027 0.0587 1.0000
12.750 1.0500 0.07509 0.06775 0.0007 0.0575 1.0000
13.000 1.0303 0.08170 0.07459 -0.0024 0.0569 1.0000
13.250 1.0063 0.08979 0.08289 -0.0068 0.0573 1.0000
13.500 0.9792 0.09940 0.09266 -0.0124 0.0587 1.0000
13.750 0.9519 0.11003 0.10336 -0.0186 0.0603 1.0000
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Polar data table (+)
Polar graphs
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