S3016-095-87 (s3016-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: S3016-095-87 (s3016-il) Reynolds number: 200,000 Max Cl/Cd: 61.02 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s3016-il-200000-n5.txt Download as CSV file: xf-s3016-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4932 0.08640 0.08302 -0.0184 1.0000 0.0141
-9.000 -0.4983 0.08091 0.07758 -0.0216 1.0000 0.0139
-8.750 -0.5061 0.07492 0.07166 -0.0255 1.0000 0.0136
-8.500 -0.5648 0.05326 0.04989 -0.0419 1.0000 0.0117
-8.250 -0.5774 0.04671 0.04302 -0.0443 1.0000 0.0116
-8.000 -0.5765 0.04290 0.03899 -0.0447 1.0000 0.0119
-7.750 -0.5757 0.03857 0.03431 -0.0442 1.0000 0.0120
-7.500 -0.5734 0.03506 0.03045 -0.0426 1.0000 0.0121
-7.250 -0.5578 0.03169 0.02665 -0.0428 0.9921 0.0124
-7.000 -0.5314 0.02849 0.02299 -0.0445 0.9831 0.0128
-6.750 -0.5048 0.02585 0.01991 -0.0455 0.9743 0.0134
-6.500 -0.4764 0.02356 0.01721 -0.0464 0.9670 0.0142
-6.250 -0.4477 0.02178 0.01505 -0.0469 0.9594 0.0154
-6.000 -0.4182 0.02061 0.01356 -0.0473 0.9523 0.0169
-5.750 -0.3915 0.01892 0.01172 -0.0476 0.9448 0.0184
-5.500 -0.3647 0.01785 0.01053 -0.0475 0.9370 0.0196
-5.250 -0.3380 0.01690 0.00944 -0.0472 0.9297 0.0211
-5.000 -0.3122 0.01633 0.00873 -0.0468 0.9214 0.0233
-4.500 -0.2639 0.01469 0.00693 -0.0453 0.9057 0.0274
-4.250 -0.2388 0.01421 0.00635 -0.0446 0.8986 0.0299
-4.000 -0.2138 0.01380 0.00584 -0.0440 0.8905 0.0331
-3.750 -0.1890 0.01329 0.00526 -0.0432 0.8832 0.0376
-3.500 -0.1638 0.01289 0.00481 -0.0425 0.8754 0.0460
-3.250 -0.1391 0.01238 0.00440 -0.0418 0.8678 0.0763
-3.000 -0.1147 0.01190 0.00410 -0.0412 0.8601 0.1300
-2.750 -0.0902 0.01142 0.00389 -0.0406 0.8522 0.1995
-2.500 -0.0658 0.01101 0.00370 -0.0399 0.8448 0.2695
-2.250 -0.0412 0.01063 0.00353 -0.0394 0.8363 0.3397
-2.000 -0.0177 0.01019 0.00340 -0.0384 0.8289 0.4320
-1.750 0.0052 0.00975 0.00333 -0.0374 0.8197 0.5330
-1.500 0.0287 0.00944 0.00325 -0.0362 0.8115 0.6108
-1.250 0.0523 0.00916 0.00317 -0.0349 0.8027 0.6833
-1.000 0.0765 0.00891 0.00312 -0.0336 0.7931 0.7579
-0.750 0.1047 0.00872 0.00308 -0.0329 0.7841 0.8331
-0.500 0.1448 0.00863 0.00302 -0.0349 0.7740 0.8979
-0.250 0.1898 0.00859 0.00292 -0.0381 0.7619 0.9401
0.000 0.2304 0.00859 0.00281 -0.0405 0.7481 0.9680
0.250 0.2705 0.00859 0.00270 -0.0429 0.7337 0.9877
0.500 0.3083 0.00859 0.00260 -0.0450 0.7189 1.0000
0.750 0.3325 0.00863 0.00254 -0.0442 0.7037 1.0000
1.000 0.3568 0.00868 0.00249 -0.0433 0.6878 1.0000
1.250 0.3814 0.00875 0.00247 -0.0426 0.6704 1.0000
1.500 0.4060 0.00883 0.00246 -0.0418 0.6520 1.0000
1.750 0.4306 0.00893 0.00246 -0.0411 0.6332 1.0000
2.000 0.4553 0.00906 0.00249 -0.0403 0.6128 1.0000
2.250 0.4799 0.00920 0.00253 -0.0396 0.5916 1.0000
2.500 0.5045 0.00936 0.00259 -0.0389 0.5692 1.0000
2.750 0.5289 0.00955 0.00267 -0.0381 0.5457 1.0000
3.000 0.5533 0.00975 0.00279 -0.0374 0.5207 1.0000
3.250 0.5776 0.00998 0.00291 -0.0367 0.4942 1.0000
3.500 0.6018 0.01024 0.00305 -0.0360 0.4675 1.0000
3.750 0.6258 0.01052 0.00324 -0.0353 0.4395 1.0000
4.000 0.6497 0.01082 0.00344 -0.0346 0.4120 1.0000
4.250 0.6735 0.01114 0.00365 -0.0339 0.3847 1.0000
4.500 0.6973 0.01149 0.00390 -0.0332 0.3582 1.0000
4.750 0.7209 0.01185 0.00419 -0.0326 0.3329 1.0000
5.000 0.7446 0.01221 0.00448 -0.0319 0.3095 1.0000
5.250 0.7682 0.01259 0.00479 -0.0313 0.2879 1.0000
5.500 0.7917 0.01298 0.00512 -0.0307 0.2678 1.0000
5.750 0.8150 0.01340 0.00547 -0.0300 0.2493 1.0000
6.000 0.8386 0.01378 0.00587 -0.0294 0.2320 1.0000
6.250 0.8620 0.01419 0.00626 -0.0288 0.2155 1.0000
6.500 0.8851 0.01461 0.00667 -0.0281 0.1998 1.0000
6.750 0.9081 0.01505 0.00710 -0.0274 0.1847 1.0000
7.000 0.9310 0.01550 0.00756 -0.0268 0.1711 1.0000
7.250 0.9535 0.01598 0.00804 -0.0261 0.1572 1.0000
7.500 0.9757 0.01648 0.00858 -0.0253 0.1438 1.0000
7.750 0.9976 0.01700 0.00913 -0.0245 0.1319 1.0000
8.000 1.0191 0.01756 0.00970 -0.0237 0.1197 1.0000
8.250 1.0401 0.01815 0.01031 -0.0229 0.1081 1.0000
8.500 1.0604 0.01879 0.01097 -0.0220 0.0974 1.0000
9.000 1.0999 0.02013 0.01239 -0.0200 0.0763 1.0000
9.250 1.1186 0.02085 0.01314 -0.0190 0.0650 1.0000
9.500 1.1361 0.02168 0.01393 -0.0179 0.0525 1.0000
9.750 1.1529 0.02252 0.01479 -0.0167 0.0425 1.0000
10.000 1.1685 0.02345 0.01573 -0.0153 0.0333 1.0000
10.250 1.1823 0.02448 0.01679 -0.0138 0.0257 1.0000
10.500 1.1935 0.02566 0.01802 -0.0119 0.0199 1.0000
10.750 1.2001 0.02698 0.01939 -0.0095 0.0159 1.0000
11.000 1.2054 0.02833 0.02090 -0.0070 0.0137 1.0000
11.250 1.2100 0.02977 0.02248 -0.0048 0.0122 1.0000
11.500 1.2109 0.03158 0.02439 -0.0026 0.0110 1.0000
11.750 1.2115 0.03348 0.02644 -0.0008 0.0103 1.0000
12.000 1.2132 0.03541 0.02854 0.0007 0.0096 1.0000
12.250 1.2160 0.03733 0.03061 0.0017 0.0087 1.0000
12.500 1.2162 0.03961 0.03302 0.0026 0.0082 1.0000
12.750 1.2142 0.04224 0.03581 0.0031 0.0080 1.0000
13.000 1.2099 0.04529 0.03901 0.0032 0.0077 1.0000
13.250 1.1999 0.04925 0.04311 0.0026 0.0073 1.0000
13.500 1.1919 0.05324 0.04727 0.0017 0.0072 1.0000
13.750 1.1829 0.05766 0.05185 0.0003 0.0071 1.0000
14.000 1.1738 0.06236 0.05672 -0.0016 0.0070 1.0000
14.250 1.1631 0.06759 0.06214 -0.0038 0.0069 1.0000
14.500 1.1519 0.07315 0.06785 -0.0065 0.0069 1.0000
14.750 1.1401 0.07915 0.07402 -0.0095 0.0068 1.0000
15.000 1.1279 0.08539 0.08041 -0.0127 0.0069 1.0000
15.250 1.1145 0.09213 0.08730 -0.0162 0.0069 1.0000
15.500 1.1009 0.09914 0.09446 -0.0200 0.0068 1.0000
15.750 1.0870 0.10637 0.10183 -0.0238 0.0068 1.0000
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Polar data table (+)
Polar graphs
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