S8037 (16%) (s8037-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: S8037 (16%) (s8037-il) Reynolds number: 100,000 Max Cl/Cd: 47 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s8037-il-100000.txt Download as CSV file: xf-s8037-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3463 0.10151 0.09682 -0.0449 1.0000 0.1492
-10.000 -0.3814 0.09758 0.09305 -0.0486 1.0000 0.1566
-9.750 -0.3899 0.09333 0.08891 -0.0487 1.0000 0.1596
-9.500 -0.3730 0.09115 0.08675 -0.0457 1.0000 0.1628
-9.250 -0.3821 0.08859 0.08432 -0.0444 1.0000 0.1665
-9.000 -0.4178 0.08784 0.08379 -0.0402 1.0000 0.1687
-8.750 -0.4618 0.08816 0.08428 -0.0346 1.0000 0.1694
-8.500 -0.6392 0.05795 0.05263 -0.0490 0.9746 0.0701
-8.250 -0.6346 0.05310 0.04741 -0.0490 0.9654 0.0673
-8.000 -0.6469 0.04765 0.04074 -0.0452 0.9544 0.0625
-7.750 -0.6213 0.04440 0.03750 -0.0466 0.9482 0.0644
-7.500 -0.6093 0.04112 0.03349 -0.0448 0.9401 0.0633
-7.250 -0.5861 0.03841 0.03037 -0.0446 0.9333 0.0633
-7.000 -0.5492 0.03580 0.02753 -0.0468 0.9295 0.0650
-6.750 -0.5325 0.03461 0.02620 -0.0452 0.9204 0.0679
-6.500 -0.4966 0.03275 0.02392 -0.0466 0.9156 0.0714
-6.250 -0.4500 0.03028 0.02133 -0.0500 0.9130 0.0754
-6.000 -0.4354 0.02955 0.02057 -0.0479 0.9034 0.0798
-5.750 -0.3926 0.02786 0.01886 -0.0506 0.8996 0.0886
-5.500 -0.3475 0.02619 0.01729 -0.0538 0.8969 0.1032
-5.250 -0.3408 0.02565 0.01683 -0.0501 0.8867 0.1162
-5.000 -0.3102 0.02417 0.01559 -0.0507 0.8822 0.1568
-4.750 -0.3070 0.02332 0.01515 -0.0466 0.8733 0.2072
-4.500 -0.3024 0.02177 0.01462 -0.0428 0.8662 0.3516
-4.250 -0.3001 0.02124 0.01491 -0.0376 0.8590 0.5142
-4.000 -0.2919 0.02141 0.01531 -0.0332 0.8507 0.5987
-3.750 -0.2585 0.02151 0.01545 -0.0327 0.8470 0.6650
-3.500 -0.2575 0.02206 0.01601 -0.0274 0.8372 0.6957
-3.250 -0.2242 0.02226 0.01617 -0.0271 0.8324 0.7345
-3.000 -0.1784 0.02242 0.01624 -0.0287 0.8296 0.7695
-2.750 -0.1806 0.02302 0.01683 -0.0232 0.8191 0.7919
-2.500 -0.1263 0.02335 0.01706 -0.0264 0.8158 0.8194
-2.250 -0.0695 0.02359 0.01713 -0.0300 0.8131 0.8448
-2.000 -0.0222 0.02435 0.01779 -0.0328 0.8068 0.8634
-1.750 0.0550 0.02484 0.01809 -0.0409 0.8027 0.8744
-1.500 0.1267 0.02487 0.01794 -0.0485 0.7991 0.8833
-1.250 0.1978 0.02478 0.01766 -0.0559 0.7959 0.8904
-1.000 0.2289 0.02521 0.01804 -0.0571 0.7874 0.9016
-0.750 0.2668 0.02515 0.01788 -0.0591 0.7815 0.9133
-0.500 0.3327 0.02488 0.01746 -0.0659 0.7779 0.9185
-0.250 0.3552 0.02537 0.01795 -0.0659 0.7679 0.9311
0.000 0.4098 0.02510 0.01757 -0.0709 0.7630 0.9385
0.250 0.4441 0.02534 0.01779 -0.0730 0.7548 0.9490
0.500 0.4829 0.02527 0.01767 -0.0754 0.7481 0.9591
0.750 0.5338 0.02495 0.01727 -0.0800 0.7426 0.9663
1.000 0.5689 0.02512 0.01745 -0.0825 0.7330 0.9764
1.250 0.6166 0.02464 0.01689 -0.0863 0.7277 0.9844
1.500 0.6549 0.02471 0.01700 -0.0896 0.7174 0.9941
1.750 0.7006 0.02410 0.01633 -0.0931 0.7113 1.0000
2.000 0.7036 0.02459 0.01687 -0.0899 0.7010 1.0000
2.250 0.7239 0.02436 0.01658 -0.0886 0.6949 1.0000
2.500 0.7254 0.02488 0.01714 -0.0850 0.6846 1.0000
2.750 0.7467 0.02457 0.01677 -0.0837 0.6783 1.0000
3.000 0.7470 0.02510 0.01736 -0.0798 0.6681 1.0000
3.250 0.7704 0.02470 0.01690 -0.0787 0.6617 1.0000
3.500 0.7702 0.02524 0.01748 -0.0745 0.6513 1.0000
3.750 0.7966 0.02477 0.01695 -0.0737 0.6450 1.0000
4.000 0.7968 0.02533 0.01757 -0.0694 0.6345 1.0000
4.250 0.8275 0.02475 0.01693 -0.0691 0.6282 1.0000
4.500 0.8289 0.02530 0.01752 -0.0649 0.6174 1.0000
4.750 0.8648 0.02458 0.01673 -0.0654 0.6113 1.0000
5.000 0.8671 0.02510 0.01731 -0.0612 0.5999 1.0000
5.250 0.8959 0.02466 0.01684 -0.0607 0.5921 1.0000
5.500 0.9124 0.02465 0.01684 -0.0584 0.5817 1.0000
5.750 0.9276 0.02473 0.01695 -0.0560 0.5712 1.0000
6.000 0.9647 0.02399 0.01614 -0.0567 0.5629 1.0000
6.250 0.9737 0.02427 0.01648 -0.0533 0.5506 1.0000
6.500 0.9927 0.02423 0.01646 -0.0514 0.5394 1.0000
6.750 1.0255 0.02371 0.01586 -0.0515 0.5289 1.0000
7.000 1.0408 0.02376 0.01594 -0.0491 0.5161 1.0000
7.250 1.0553 0.02388 0.01609 -0.0465 0.5028 1.0000
7.500 1.0728 0.02391 0.01612 -0.0444 0.4895 1.0000
7.750 1.0916 0.02391 0.01610 -0.0424 0.4757 1.0000
8.000 1.1099 0.02396 0.01613 -0.0405 0.4614 1.0000
8.250 1.1264 0.02407 0.01620 -0.0382 0.4463 1.0000
8.500 1.1411 0.02428 0.01636 -0.0358 0.4310 1.0000
8.750 1.1538 0.02457 0.01661 -0.0330 0.4153 1.0000
9.000 1.1650 0.02493 0.01693 -0.0301 0.3996 1.0000
9.250 1.1758 0.02535 0.01730 -0.0272 0.3842 1.0000
9.500 1.1855 0.02585 0.01773 -0.0241 0.3689 1.0000
9.750 1.1956 0.02641 0.01822 -0.0212 0.3541 1.0000
10.000 1.2039 0.02704 0.01880 -0.0182 0.3397 1.0000
10.250 1.2032 0.02776 0.01955 -0.0137 0.3268 1.0000
10.500 1.2058 0.02854 0.02031 -0.0099 0.3140 1.0000
10.750 1.2121 0.02935 0.02109 -0.0068 0.3016 1.0000
11.000 1.2202 0.03017 0.02183 -0.0042 0.2891 1.0000
11.250 1.2323 0.03099 0.02254 -0.0022 0.2765 1.0000
11.500 1.2296 0.03210 0.02376 0.0016 0.2658 1.0000
11.750 1.2348 0.03319 0.02487 0.0041 0.2550 1.0000
12.000 1.2466 0.03419 0.02577 0.0058 0.2439 1.0000
12.250 1.2475 0.03542 0.02707 0.0085 0.2341 1.0000
12.500 1.2517 0.03676 0.02846 0.0107 0.2247 1.0000
12.750 1.2667 0.03778 0.02934 0.0118 0.2145 1.0000
13.000 1.2612 0.03947 0.03123 0.0146 0.2067 1.0000
13.250 1.2727 0.04071 0.03241 0.0158 0.1978 1.0000
13.500 1.2714 0.04238 0.03420 0.0179 0.1902 1.0000
13.750 1.2809 0.04382 0.03563 0.0191 0.1826 1.0000
14.000 1.2798 0.04565 0.03760 0.0209 0.1758 1.0000
14.250 1.2918 0.04707 0.03897 0.0219 0.1686 1.0000
14.500 1.2842 0.04938 0.04149 0.0237 0.1631 1.0000
14.750 1.3072 0.05037 0.04231 0.0240 0.1555 1.0000
15.000 1.2916 0.05329 0.04555 0.0259 0.1517 1.0000
15.250 1.2912 0.05539 0.04774 0.0270 0.1466 1.0000
15.500 1.3066 0.05691 0.04921 0.0276 0.1408 1.0000
15.750 1.2879 0.06044 0.05303 0.0288 0.1377 1.0000
16.000 1.2798 0.06339 0.05617 0.0296 0.1340 1.0000
16.250 1.3077 0.06410 0.05670 0.0300 0.1279 1.0000
16.500 1.2814 0.06858 0.06151 0.0306 0.1263 1.0000
16.750 1.2553 0.07350 0.06672 0.0307 0.1245 1.0000
17.000 1.2293 0.07879 0.07224 0.0302 0.1227 1.0000
17.250 1.1989 0.08510 0.07879 0.0290 0.1213 1.0000
17.500 1.0989 0.10204 0.09613 0.0226 0.1243 1.0000
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Polar data table (+)
Polar graphs
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