S8036 (16%) (s8036-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: S8036 (16%) (s8036-il) Reynolds number: 200,000 Max Cl/Cd: 70.23 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s8036-il-200000.txt Download as CSV file: xf-s8036-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: S8036 (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
------ -------- --------- --------- -------- -------- --------
-12.250 -0.3870 0.09112 0.08765 -0.0550 1.0000 0.0444
-12.000 -0.7316 0.05892 0.05398 -0.0714 1.0000 0.0314
-11.750 -0.7387 0.05560 0.05059 -0.0698 1.0000 0.0312
-11.500 -0.7474 0.05271 0.04764 -0.0676 1.0000 0.0309
-11.250 -0.7641 0.05024 0.04504 -0.0639 1.0000 0.0307
-11.000 -0.7806 0.04823 0.04291 -0.0592 1.0000 0.0305
-10.750 -0.8005 0.04641 0.04097 -0.0533 1.0000 0.0304
-10.500 -0.8158 0.04443 0.03883 -0.0479 1.0000 0.0302
-10.250 -0.8307 0.04270 0.03696 -0.0422 1.0000 0.0301
-10.000 -0.8497 0.04139 0.03550 -0.0356 1.0000 0.0301
-9.750 -0.8490 0.03918 0.03303 -0.0330 0.9972 0.0300
-9.500 -0.8231 0.03600 0.02938 -0.0348 0.9906 0.0304
-9.250 -0.7954 0.03365 0.02643 -0.0363 0.9837 0.0314
-9.000 -0.7635 0.03113 0.02386 -0.0382 0.9775 0.0324
-8.750 -0.7265 0.02930 0.02193 -0.0408 0.9730 0.0334
-8.500 -0.6935 0.02761 0.02009 -0.0423 0.9655 0.0346
-8.250 -0.6548 0.02600 0.01826 -0.0447 0.9610 0.0361
-8.000 -0.6211 0.02433 0.01660 -0.0463 0.9542 0.0381
-7.750 -0.5840 0.02314 0.01540 -0.0486 0.9490 0.0411
-7.500 -0.5490 0.02186 0.01414 -0.0506 0.9435 0.0454
-7.250 -0.5157 0.02068 0.01292 -0.0521 0.9363 0.0507
-7.000 -0.4771 0.01946 0.01173 -0.0548 0.9320 0.0587
-6.750 -0.4489 0.01844 0.01077 -0.0555 0.9224 0.0689
-6.500 -0.4142 0.01736 0.00977 -0.0575 0.9161 0.0850
-6.250 -0.3898 0.01647 0.00897 -0.0574 0.9050 0.1060
-6.000 -0.3631 0.01550 0.00817 -0.0577 0.8964 0.1411
-5.750 -0.3460 0.01466 0.00758 -0.0562 0.8849 0.1916
-5.500 -0.3344 0.01379 0.00710 -0.0536 0.8737 0.2706
-5.250 -0.3220 0.01295 0.00670 -0.0509 0.8645 0.3749
-5.000 -0.3133 0.01253 0.00662 -0.0471 0.8535 0.4575
-4.750 -0.2932 0.01232 0.00659 -0.0453 0.8461 0.5263
-4.500 -0.2767 0.01234 0.00668 -0.0427 0.8364 0.5685
-4.250 -0.2520 0.01240 0.00670 -0.0416 0.8298 0.6022
-4.000 -0.2330 0.01251 0.00679 -0.0395 0.8211 0.6268
-3.750 -0.2087 0.01260 0.00678 -0.0384 0.8143 0.6481
-3.500 -0.1856 0.01271 0.00685 -0.0371 0.8073 0.6658
-3.250 -0.1625 0.01281 0.00691 -0.0358 0.8001 0.6824
-3.000 -0.1341 0.01291 0.00695 -0.0354 0.7947 0.6979
-2.750 -0.1115 0.01302 0.00708 -0.0340 0.7873 0.7116
-2.500 -0.0857 0.01310 0.00711 -0.0332 0.7810 0.7248
-2.250 -0.0583 0.01321 0.00714 -0.0327 0.7761 0.7389
-2.000 -0.0387 0.01332 0.00726 -0.0308 0.7687 0.7528
-1.750 -0.0094 0.01339 0.00731 -0.0307 0.7629 0.7634
-1.500 0.0173 0.01343 0.00728 -0.0302 0.7579 0.7740
-1.250 0.0405 0.01349 0.00736 -0.0291 0.7508 0.7832
-1.000 0.0670 0.01348 0.00728 -0.0287 0.7451 0.7920
-0.750 0.0958 0.01353 0.00728 -0.0287 0.7400 0.8001
-0.500 0.1170 0.01353 0.00729 -0.0274 0.7330 0.8089
-0.250 0.1466 0.01354 0.00727 -0.0275 0.7275 0.8165
0.000 0.1716 0.01356 0.00723 -0.0269 0.7221 0.8256
0.250 0.1978 0.01361 0.00732 -0.0264 0.7153 0.8331
0.500 0.2232 0.01358 0.00724 -0.0258 0.7098 0.8426
0.750 0.2543 0.01365 0.00731 -0.0264 0.7043 0.8496
1.000 0.2751 0.01366 0.00733 -0.0249 0.6973 0.8598
1.250 0.3102 0.01368 0.00733 -0.0262 0.6919 0.8662
1.500 0.3330 0.01372 0.00737 -0.0252 0.6855 0.8767
1.750 0.3673 0.01378 0.00746 -0.0264 0.6784 0.8831
2.000 0.4004 0.01379 0.00740 -0.0273 0.6730 0.8921
2.250 0.4322 0.01390 0.00758 -0.0282 0.6648 0.8992
2.500 0.4689 0.01394 0.00758 -0.0298 0.6580 0.9067
2.750 0.5030 0.01403 0.00769 -0.0311 0.6504 0.9141
3.000 0.5442 0.01408 0.00773 -0.0337 0.6420 0.9191
3.250 0.5754 0.01412 0.00777 -0.0343 0.6337 0.9284
3.500 0.6203 0.01413 0.00775 -0.0377 0.6239 0.9314
3.750 0.6602 0.01420 0.00785 -0.0402 0.6134 0.9361
4.000 0.6951 0.01419 0.00777 -0.0415 0.6048 0.9442
4.250 0.7354 0.01426 0.00790 -0.0441 0.5931 0.9485
4.500 0.7707 0.01430 0.00795 -0.0457 0.5825 0.9563
4.750 0.8109 0.01430 0.00791 -0.0483 0.5716 0.9619
5.000 0.8435 0.01435 0.00802 -0.0494 0.5580 0.9713
5.250 0.8838 0.01435 0.00804 -0.0522 0.5428 0.9770
5.500 0.9206 0.01438 0.00808 -0.0543 0.5267 0.9849
5.750 0.9603 0.01438 0.00807 -0.0571 0.5079 0.9920
6.000 1.0008 0.01439 0.00805 -0.0601 0.4873 0.9986
6.250 1.0134 0.01443 0.00807 -0.0577 0.4692 1.0000
6.500 1.0174 0.01452 0.00812 -0.0535 0.4519 1.0000
6.750 1.0215 0.01467 0.00823 -0.0492 0.4332 1.0000
7.000 1.0255 0.01490 0.00838 -0.0449 0.4125 1.0000
7.250 1.0289 0.01523 0.00859 -0.0404 0.3902 1.0000
7.500 1.0322 0.01561 0.00888 -0.0359 0.3663 1.0000
7.750 1.0329 0.01611 0.00923 -0.0310 0.3431 1.0000
8.000 1.0341 0.01662 0.00964 -0.0263 0.3195 1.0000
8.250 1.0310 0.01716 0.01006 -0.0207 0.2990 1.0000
8.500 1.0268 0.01774 0.01052 -0.0150 0.2804 1.0000
8.750 1.0248 0.01842 0.01107 -0.0100 0.2628 1.0000
9.000 1.0252 0.01914 0.01171 -0.0057 0.2460 1.0000
9.250 1.0264 0.01996 0.01243 -0.0017 0.2309 1.0000
9.500 1.0294 0.02080 0.01321 0.0018 0.2171 1.0000
9.750 1.0345 0.02166 0.01404 0.0048 0.2047 1.0000
10.000 1.0397 0.02260 0.01494 0.0075 0.1939 1.0000
10.250 1.0437 0.02369 0.01592 0.0103 0.1846 1.0000
10.500 1.0520 0.02461 0.01689 0.0124 0.1752 1.0000
10.750 1.0588 0.02571 0.01793 0.0145 0.1675 1.0000
11.000 1.0676 0.02670 0.01895 0.0163 0.1601 1.0000
11.250 1.0759 0.02785 0.02003 0.0181 0.1536 1.0000
11.500 1.0855 0.02887 0.02112 0.0196 0.1473 1.0000
11.750 1.0951 0.03001 0.02218 0.0211 0.1418 1.0000
12.000 1.1056 0.03108 0.02334 0.0225 0.1367 1.0000
12.250 1.1148 0.03221 0.02451 0.0238 0.1317 1.0000
12.500 1.1284 0.03330 0.02547 0.0249 0.1268 1.0000
12.750 1.1364 0.03452 0.02686 0.0262 0.1230 1.0000
13.000 1.1463 0.03570 0.02810 0.0272 0.1191 1.0000
13.250 1.1571 0.03688 0.02926 0.0283 0.1154 1.0000
13.500 1.1697 0.03808 0.03049 0.0292 0.1118 1.0000
13.750 1.1771 0.03947 0.03202 0.0303 0.1085 1.0000
14.000 1.1852 0.04082 0.03343 0.0312 0.1052 1.0000
14.250 1.1983 0.04199 0.03455 0.0320 0.1020 1.0000
14.500 1.2084 0.04345 0.03610 0.0328 0.0991 1.0000
14.750 1.2126 0.04516 0.03797 0.0337 0.0965 1.0000
15.000 1.2192 0.04675 0.03964 0.0344 0.0937 1.0000
15.250 1.2282 0.04817 0.04105 0.0350 0.0911 1.0000
15.500 1.2428 0.04955 0.04243 0.0357 0.0882 1.0000
15.750 1.2423 0.05175 0.04485 0.0364 0.0864 1.0000
16.000 1.2437 0.05392 0.04717 0.0369 0.0843 1.0000
16.250 1.2472 0.05590 0.04923 0.0373 0.0821 1.0000
16.500 1.2553 0.05750 0.05083 0.0376 0.0799 1.0000
16.750 1.2688 0.05912 0.05244 0.0383 0.0776 1.0000
17.000 1.2618 0.06215 0.05571 0.0384 0.0764 1.0000
17.250 1.2565 0.06522 0.05899 0.0384 0.0750 1.0000
17.500 1.2506 0.06843 0.06238 0.0381 0.0735 1.0000
17.750 1.2477 0.07142 0.06549 0.0378 0.0721 1.0000
18.000 1.2485 0.07400 0.06814 0.0375 0.0706 1.0000
18.250 1.2562 0.07589 0.07002 0.0375 0.0691 1.0000
18.500 1.2567 0.07892 0.07313 0.0375 0.0676 1.0000
18.750 1.2384 0.08397 0.07843 0.0360 0.0670 1.0000
19.000 1.2181 0.08963 0.08433 0.0341 0.0664 1.0000
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Polar data table (+)
Polar graphs
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