S8037 (16%) (s8037-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: S8037 (16%) (s8037-il) Reynolds number: 200,000 Max Cl/Cd: 71.33 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s8037-il-200000.txt Download as CSV file: xf-s8037-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: S8037 (16%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3843 0.09334 0.08996 -0.0537 1.0000 0.0702
-10.500 -0.4360 0.08086 0.07754 -0.0648 1.0000 0.0717
-10.250 -0.4540 0.07586 0.07257 -0.0663 1.0000 0.0713
-10.000 -0.4930 0.07159 0.06832 -0.0666 1.0000 0.0714
-9.750 -0.6270 0.04916 0.04473 -0.0664 0.9765 0.0362
-9.500 -0.6262 0.04339 0.03846 -0.0668 0.9629 0.0348
-9.250 -0.6145 0.03934 0.03394 -0.0671 0.9525 0.0350
-9.000 -0.5952 0.03507 0.02912 -0.0679 0.9458 0.0345
-8.750 -0.5727 0.03181 0.02539 -0.0683 0.9365 0.0345
-8.500 -0.5409 0.02892 0.02209 -0.0699 0.9306 0.0350
-8.250 -0.5105 0.02688 0.01973 -0.0709 0.9217 0.0358
-8.000 -0.4751 0.02513 0.01764 -0.0726 0.9148 0.0372
-7.750 -0.4436 0.02349 0.01592 -0.0738 0.9054 0.0395
-7.500 -0.4092 0.02228 0.01462 -0.0753 0.8975 0.0415
-7.250 -0.3820 0.02127 0.01348 -0.0753 0.8873 0.0434
-7.000 -0.3519 0.02008 0.01221 -0.0759 0.8796 0.0460
-6.750 -0.3322 0.01946 0.01161 -0.0745 0.8690 0.0493
-6.500 -0.3080 0.01886 0.01086 -0.0738 0.8610 0.0527
-6.250 -0.2927 0.01800 0.01008 -0.0717 0.8515 0.0571
-6.000 -0.2740 0.01736 0.00939 -0.0699 0.8441 0.0639
-5.750 -0.2593 0.01680 0.00884 -0.0675 0.8353 0.0742
-5.500 -0.2433 0.01607 0.00818 -0.0653 0.8288 0.0962
-5.250 -0.2324 0.01541 0.00774 -0.0623 0.8203 0.1312
-5.000 -0.2181 0.01471 0.00730 -0.0600 0.8137 0.1906
-4.750 -0.2087 0.01401 0.00702 -0.0568 0.8066 0.2769
-4.500 -0.2000 0.01334 0.00681 -0.0532 0.7996 0.3847
-4.250 -0.1872 0.01292 0.00676 -0.0501 0.7942 0.4845
-4.000 -0.1745 0.01280 0.00687 -0.0469 0.7869 0.5540
-3.750 -0.1551 0.01276 0.00690 -0.0448 0.7812 0.6026
-3.500 -0.1332 0.01280 0.00693 -0.0432 0.7760 0.6358
-3.250 -0.1129 0.01283 0.00700 -0.0413 0.7692 0.6617
-3.000 -0.0892 0.01286 0.00698 -0.0401 0.7639 0.6861
-2.750 -0.0652 0.01293 0.00700 -0.0389 0.7590 0.7079
-2.500 -0.0431 0.01298 0.00709 -0.0374 0.7524 0.7279
-2.250 -0.0175 0.01301 0.00708 -0.0365 0.7472 0.7473
-2.000 0.0092 0.01307 0.00710 -0.0359 0.7426 0.7656
-1.750 0.0314 0.01315 0.00721 -0.0344 0.7359 0.7837
-1.500 0.0584 0.01319 0.00722 -0.0337 0.7306 0.8024
-1.250 0.0884 0.01325 0.00722 -0.0338 0.7263 0.8185
-1.000 0.1121 0.01331 0.00732 -0.0328 0.7194 0.8328
-0.750 0.1405 0.01332 0.00728 -0.0326 0.7141 0.8469
-0.500 0.1763 0.01339 0.00725 -0.0339 0.7100 0.8589
-0.250 0.2065 0.01350 0.00741 -0.0343 0.7029 0.8700
0.000 0.2392 0.01354 0.00740 -0.0352 0.6974 0.8817
0.500 0.3161 0.01383 0.00761 -0.0393 0.6859 0.8997
0.750 0.3599 0.01396 0.00768 -0.0424 0.6803 0.9063
1.000 0.3982 0.01408 0.00771 -0.0444 0.6752 0.9148
1.250 0.4426 0.01425 0.00790 -0.0478 0.6676 0.9190
1.500 0.4835 0.01432 0.00788 -0.0503 0.6618 0.9254
1.750 0.5211 0.01447 0.00803 -0.0523 0.6547 0.9321
2.000 0.5633 0.01454 0.00806 -0.0552 0.6476 0.9373
2.250 0.5991 0.01461 0.00807 -0.0568 0.6417 0.9457
2.500 0.6405 0.01468 0.00817 -0.0597 0.6332 0.9511
2.750 0.6774 0.01469 0.00807 -0.0616 0.6271 0.9593
3.000 0.7177 0.01473 0.00818 -0.0644 0.6177 0.9653
3.250 0.7567 0.01471 0.00807 -0.0667 0.6111 0.9727
3.500 0.7964 0.01472 0.00815 -0.0695 0.6015 0.9799
3.750 0.8381 0.01463 0.00798 -0.0726 0.5940 0.9859
4.000 0.8779 0.01456 0.00796 -0.0754 0.5833 0.9932
4.250 0.9208 0.01439 0.00779 -0.0789 0.5736 0.9991
4.500 0.9410 0.01433 0.00770 -0.0778 0.5647 1.0000
4.750 0.9547 0.01434 0.00774 -0.0754 0.5553 1.0000
5.000 0.9718 0.01432 0.00766 -0.0736 0.5467 1.0000
5.250 0.9845 0.01438 0.00778 -0.0709 0.5363 1.0000
5.500 1.0005 0.01443 0.00779 -0.0688 0.5266 1.0000
5.750 1.0157 0.01449 0.00785 -0.0665 0.5160 1.0000
6.000 1.0298 0.01461 0.00800 -0.0640 0.5046 1.0000
6.250 1.0452 0.01473 0.00810 -0.0617 0.4933 1.0000
6.500 1.0613 0.01488 0.00818 -0.0595 0.4819 1.0000
6.750 1.0743 0.01506 0.00839 -0.0568 0.4686 1.0000
7.000 1.0874 0.01526 0.00860 -0.0541 0.4548 1.0000
7.250 1.0999 0.01551 0.00882 -0.0512 0.4403 1.0000
7.500 1.1117 0.01578 0.00906 -0.0483 0.4256 1.0000
7.750 1.1224 0.01609 0.00935 -0.0452 0.4104 1.0000
8.000 1.1319 0.01645 0.00966 -0.0418 0.3951 1.0000
8.250 1.1402 0.01684 0.01001 -0.0383 0.3800 1.0000
8.500 1.1471 0.01728 0.01040 -0.0346 0.3652 1.0000
8.750 1.1517 0.01775 0.01082 -0.0306 0.3508 1.0000
9.000 1.1529 0.01822 0.01122 -0.0258 0.3377 1.0000
9.250 1.1545 0.01873 0.01169 -0.0214 0.3246 1.0000
9.500 1.1573 0.01929 0.01224 -0.0173 0.3113 1.0000
9.750 1.1608 0.01994 0.01286 -0.0136 0.2984 1.0000
10.000 1.1643 0.02067 0.01356 -0.0101 0.2858 1.0000
10.250 1.1680 0.02150 0.01434 -0.0069 0.2743 1.0000
10.500 1.1719 0.02239 0.01519 -0.0039 0.2626 1.0000
10.750 1.1768 0.02330 0.01613 -0.0013 0.2510 1.0000
11.000 1.1818 0.02432 0.01713 0.0012 0.2404 1.0000
11.250 1.1857 0.02546 0.01818 0.0036 0.2305 1.0000
11.500 1.1914 0.02654 0.01935 0.0056 0.2202 1.0000
11.750 1.1966 0.02775 0.02054 0.0075 0.2111 1.0000
12.000 1.2009 0.02905 0.02182 0.0094 0.2020 1.0000
12.250 1.2067 0.03034 0.02316 0.0110 0.1931 1.0000
12.500 1.2109 0.03176 0.02449 0.0127 0.1852 1.0000
12.750 1.2163 0.03316 0.02602 0.0140 0.1770 1.0000
13.000 1.2206 0.03467 0.02746 0.0155 0.1698 1.0000
13.250 1.2251 0.03622 0.02912 0.0167 0.1623 1.0000
13.500 1.2294 0.03781 0.03063 0.0179 0.1557 1.0000
13.750 1.2336 0.03947 0.03243 0.0189 0.1491 1.0000
14.000 1.2376 0.04116 0.03403 0.0200 0.1430 1.0000
14.250 1.2415 0.04294 0.03595 0.0209 0.1371 1.0000
14.500 1.2448 0.04479 0.03782 0.0218 0.1316 1.0000
14.750 1.2495 0.04657 0.03961 0.0226 0.1264 1.0000
15.000 1.2522 0.04858 0.04174 0.0232 0.1213 1.0000
15.250 1.2562 0.05046 0.04356 0.0239 0.1166 1.0000
15.500 1.2595 0.05253 0.04574 0.0245 0.1122 1.0000
15.750 1.2611 0.05480 0.04810 0.0248 0.1078 1.0000
16.000 1.2661 0.05667 0.04993 0.0253 0.1038 1.0000
16.250 1.2682 0.05896 0.05234 0.0257 0.1001 1.0000
16.500 1.2689 0.06149 0.05498 0.0258 0.0965 1.0000
16.750 1.2716 0.06375 0.05727 0.0259 0.0933 1.0000
17.000 1.2789 0.06546 0.05894 0.0265 0.0899 1.0000
17.250 1.2764 0.06849 0.06217 0.0262 0.0873 1.0000
17.500 1.2758 0.07131 0.06510 0.0260 0.0844 1.0000
17.750 1.2776 0.07382 0.06763 0.0258 0.0818 1.0000
18.000 1.2869 0.07528 0.06905 0.0264 0.0788 1.0000
18.250 1.2795 0.07915 0.07315 0.0256 0.0770 1.0000
18.500 1.2743 0.08277 0.07694 0.0247 0.0749 1.0000
18.750 1.2725 0.08593 0.08018 0.0240 0.0727 1.0000
19.000 1.2754 0.08839 0.08264 0.0236 0.0706 1.0000
19.250 1.2794 0.09062 0.08488 0.0237 0.0682 1.0000
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Polar data table (+)
Polar graphs
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