S3016-095-87 (s3016-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: S3016-095-87 (s3016-il) Reynolds number: 100,000 Max Cl/Cd: 49.17 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s3016-il-100000.txt Download as CSV file: xf-s3016-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4573 0.09994 0.09523 -0.0130 1.0000 0.1060
-8.750 -0.4689 0.09680 0.09218 -0.0178 1.0000 0.1112
-8.500 -0.4921 0.09337 0.08890 -0.0254 1.0000 0.1122
-8.250 -0.4532 0.08942 0.08485 -0.0177 1.0000 0.1206
-8.000 -0.4668 0.08598 0.08155 -0.0225 1.0000 0.1248
-7.750 -0.4976 0.08146 0.07707 -0.0337 1.0000 0.1263
-7.500 -0.4595 0.07879 0.07445 -0.0232 1.0000 0.1334
-7.250 -0.4965 0.07428 0.06982 -0.0368 1.0000 0.1405
-7.000 -0.4648 0.07060 0.06635 -0.0294 1.0000 0.1448
-6.750 -0.4818 0.06666 0.06229 -0.0354 1.0000 0.1554
-6.500 -0.4643 0.06357 0.05934 -0.0315 1.0000 0.1589
-5.750 -0.4893 0.04591 0.04014 -0.0332 1.0000 0.0989
-5.500 -0.4786 0.03741 0.03115 -0.0311 1.0000 0.0688
-5.250 -0.4681 0.03379 0.02716 -0.0291 1.0000 0.0648
-5.000 -0.4543 0.03003 0.02245 -0.0266 1.0000 0.0603
-4.750 -0.4380 0.02820 0.02052 -0.0252 1.0000 0.0631
-4.500 -0.4199 0.02644 0.01844 -0.0237 1.0000 0.0653
-4.250 -0.3997 0.02456 0.01619 -0.0222 1.0000 0.0661
-4.000 -0.3782 0.02298 0.01430 -0.0208 1.0000 0.0680
-3.750 -0.3565 0.02196 0.01298 -0.0195 1.0000 0.0718
-3.500 -0.3357 0.02059 0.01171 -0.0185 1.0000 0.0782
-3.250 -0.3145 0.01970 0.01068 -0.0172 1.0000 0.0841
-3.000 -0.2950 0.01872 0.00982 -0.0160 1.0000 0.0951
-2.750 -0.2702 0.01771 0.00899 -0.0157 0.9982 0.1271
-2.500 -0.2371 0.01571 0.00848 -0.0175 0.9920 0.3793
-2.250 -0.2039 0.01495 0.00874 -0.0185 0.9846 0.6131
-2.000 -0.1213 0.01432 0.00892 -0.0265 0.9855 0.9800
-1.750 -0.0675 0.01460 0.00879 -0.0324 0.9785 1.0000
-1.500 -0.0168 0.01488 0.00874 -0.0376 0.9704 1.0000
-1.250 0.0257 0.01508 0.00870 -0.0410 0.9599 1.0000
-1.000 0.0695 0.01528 0.00868 -0.0446 0.9498 1.0000
-0.750 0.1256 0.01543 0.00865 -0.0504 0.9426 1.0000
-0.500 0.1678 0.01553 0.00862 -0.0534 0.9313 1.0000
-0.250 0.2125 0.01559 0.00857 -0.0567 0.9205 1.0000
0.000 0.2574 0.01558 0.00848 -0.0599 0.9099 1.0000
0.250 0.3039 0.01546 0.00829 -0.0630 0.8999 1.0000
0.500 0.3364 0.01543 0.00820 -0.0634 0.8862 1.0000
0.750 0.3654 0.01540 0.00812 -0.0629 0.8720 1.0000
1.000 0.3913 0.01537 0.00805 -0.0618 0.8576 1.0000
1.250 0.4154 0.01534 0.00798 -0.0603 0.8431 1.0000
1.500 0.4384 0.01531 0.00791 -0.0585 0.8284 1.0000
1.750 0.4604 0.01527 0.00784 -0.0566 0.8131 1.0000
2.000 0.4818 0.01526 0.00782 -0.0546 0.7966 1.0000
2.250 0.5037 0.01521 0.00775 -0.0526 0.7801 1.0000
2.500 0.5261 0.01513 0.00765 -0.0507 0.7631 1.0000
2.750 0.5491 0.01501 0.00751 -0.0488 0.7459 1.0000
3.000 0.5726 0.01487 0.00735 -0.0470 0.7285 1.0000
3.250 0.5954 0.01481 0.00729 -0.0453 0.7079 1.0000
3.500 0.6190 0.01471 0.00715 -0.0436 0.6869 1.0000
3.750 0.6423 0.01469 0.00711 -0.0419 0.6631 1.0000
4.000 0.6660 0.01468 0.00704 -0.0404 0.6382 1.0000
4.250 0.6894 0.01475 0.00703 -0.0388 0.6105 1.0000
4.500 0.7125 0.01490 0.00711 -0.0374 0.5796 1.0000
4.750 0.7353 0.01513 0.00727 -0.0360 0.5471 1.0000
5.000 0.7580 0.01545 0.00745 -0.0346 0.5139 1.0000
5.250 0.7803 0.01587 0.00775 -0.0333 0.4795 1.0000
5.500 0.8023 0.01636 0.00811 -0.0321 0.4459 1.0000
5.750 0.8243 0.01692 0.00855 -0.0309 0.4147 1.0000
6.000 0.8462 0.01753 0.00904 -0.0298 0.3852 1.0000
6.250 0.8679 0.01819 0.00961 -0.0287 0.3574 1.0000
6.500 0.8896 0.01889 0.01025 -0.0277 0.3315 1.0000
6.750 0.9112 0.01965 0.01092 -0.0267 0.3078 1.0000
7.000 0.9326 0.02043 0.01166 -0.0257 0.2853 1.0000
7.250 0.9538 0.02127 0.01250 -0.0248 0.2639 1.0000
7.500 0.9748 0.02213 0.01333 -0.0238 0.2438 1.0000
7.750 0.9959 0.02310 0.01422 -0.0228 0.2253 1.0000
8.000 1.0158 0.02402 0.01525 -0.0217 0.2067 1.0000
8.250 1.0359 0.02503 0.01633 -0.0206 0.1899 1.0000
8.500 1.0554 0.02605 0.01736 -0.0195 0.1738 1.0000
8.750 1.0746 0.02716 0.01848 -0.0184 0.1588 1.0000
9.000 1.0929 0.02831 0.01964 -0.0173 0.1442 1.0000
9.250 1.1102 0.02955 0.02090 -0.0160 0.1301 1.0000
9.500 1.1261 0.03087 0.02223 -0.0147 0.1162 1.0000
9.750 1.1391 0.03219 0.02370 -0.0130 0.1026 1.0000
10.000 1.1499 0.03362 0.02523 -0.0111 0.0895 1.0000
10.250 1.1585 0.03521 0.02689 -0.0092 0.0771 1.0000
10.500 1.1642 0.03665 0.02849 -0.0068 0.0669 1.0000
10.750 1.1695 0.03891 0.03106 -0.0045 0.0586 1.0000
11.000 1.1763 0.04145 0.03361 -0.0027 0.0523 1.0000
11.250 1.1791 0.04410 0.03663 -0.0003 0.0486 1.0000
11.500 1.1812 0.04644 0.03911 0.0019 0.0454 1.0000
11.750 1.1858 0.05048 0.04318 0.0030 0.0428 1.0000
12.000 1.1727 0.05302 0.04611 0.0058 0.0417 1.0000
12.250 1.1604 0.05627 0.04970 0.0074 0.0408 1.0000
12.500 1.1461 0.06004 0.05377 0.0083 0.0403 1.0000
12.750 1.1292 0.06436 0.05837 0.0083 0.0400 1.0000
13.000 1.1102 0.06931 0.06358 0.0073 0.0401 1.0000
13.250 1.0883 0.07493 0.06944 0.0052 0.0399 1.0000
13.500 1.0653 0.08147 0.07619 0.0020 0.0405 1.0000
13.750 1.0410 0.08895 0.08385 -0.0022 0.0412 1.0000
14.000 1.0176 0.09709 0.09211 -0.0070 0.0421 1.0000
14.250 0.9947 0.10578 0.10090 -0.0123 0.0426 1.0000
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Polar data table (+)
Polar graphs
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