S8037 (16%) (s8037-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: S8037 (16%) (s8037-il) Reynolds number: 200,000 Max Cl/Cd: 68.95 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s8037-il-200000-n5.txt Download as CSV file: xf-s8037-il-200000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.5893 0.07216 0.06795 -0.0680 1.0000 0.0145
-13.000 -0.6284 0.06271 0.05825 -0.0741 1.0000 0.0145
-12.750 -0.6538 0.05675 0.05208 -0.0768 1.0000 0.0143
-12.500 -0.6748 0.05214 0.04728 -0.0779 1.0000 0.0143
-12.250 -0.6957 0.04807 0.04300 -0.0777 1.0000 0.0143
-12.000 -0.7120 0.04510 0.03982 -0.0764 1.0000 0.0147
-11.750 -0.7262 0.04253 0.03706 -0.0741 1.0000 0.0148
-11.500 -0.7383 0.04043 0.03478 -0.0710 1.0000 0.0149
-11.250 -0.7543 0.03858 0.03269 -0.0667 1.0000 0.0153
-11.000 -0.7529 0.03625 0.03003 -0.0651 0.9939 0.0155
-10.750 -0.7390 0.03432 0.02796 -0.0651 0.9755 0.0160
-10.500 -0.7195 0.03290 0.02644 -0.0655 0.9558 0.0164
-10.250 -0.6929 0.03116 0.02452 -0.0671 0.9419 0.0169
-10.000 -0.6619 0.02927 0.02238 -0.0694 0.9298 0.0174
-9.750 -0.6289 0.02748 0.02034 -0.0717 0.9168 0.0181
-9.500 -0.5945 0.02583 0.01839 -0.0741 0.9035 0.0188
-9.250 -0.5625 0.02448 0.01694 -0.0760 0.8893 0.0195
-9.000 -0.5343 0.02354 0.01590 -0.0770 0.8748 0.0204
-8.750 -0.5085 0.02269 0.01490 -0.0773 0.8613 0.0214
-8.500 -0.4861 0.02189 0.01389 -0.0767 0.8482 0.0226
-8.250 -0.4677 0.02112 0.01307 -0.0755 0.8362 0.0234
-8.000 -0.4490 0.02047 0.01234 -0.0742 0.8260 0.0242
-7.750 -0.4312 0.01987 0.01165 -0.0726 0.8161 0.0254
-7.500 -0.4129 0.01933 0.01097 -0.0710 0.8075 0.0267
-7.250 -0.3957 0.01878 0.01037 -0.0693 0.7990 0.0283
-7.000 -0.3770 0.01833 0.00985 -0.0678 0.7915 0.0300
-6.250 -0.3214 0.01697 0.00827 -0.0629 0.7706 0.0382
-6.000 -0.3021 0.01654 0.00781 -0.0614 0.7642 0.0434
-5.750 -0.2824 0.01613 0.00738 -0.0599 0.7585 0.0508
-5.500 -0.2628 0.01575 0.00700 -0.0584 0.7520 0.0616
-5.250 -0.2428 0.01536 0.00663 -0.0570 0.7464 0.0771
-4.750 -0.2031 0.01461 0.00603 -0.0542 0.7348 0.1253
-4.500 -0.1841 0.01418 0.00573 -0.0527 0.7296 0.1645
-4.250 -0.1672 0.01363 0.00545 -0.0508 0.7247 0.2266
-4.000 -0.1534 0.01301 0.00521 -0.0484 0.7189 0.3124
-3.750 -0.1385 0.01251 0.00503 -0.0460 0.7137 0.3954
-3.500 -0.1207 0.01219 0.00491 -0.0439 0.7094 0.4628
-3.250 -0.1017 0.01198 0.00487 -0.0420 0.7038 0.5144
-3.000 -0.0804 0.01186 0.00482 -0.0405 0.6986 0.5557
-2.750 -0.0572 0.01179 0.00475 -0.0394 0.6942 0.5888
-2.500 -0.0347 0.01173 0.00473 -0.0381 0.6893 0.6179
-2.250 -0.0115 0.01168 0.00471 -0.0370 0.6839 0.6422
-2.000 0.0129 0.01164 0.00466 -0.0361 0.6792 0.6640
-1.750 0.0372 0.01162 0.00463 -0.0351 0.6747 0.6864
-1.500 0.0605 0.01160 0.00464 -0.0340 0.6691 0.7077
-1.250 0.0855 0.01158 0.00461 -0.0332 0.6641 0.7250
-0.750 0.1374 0.01156 0.00458 -0.0321 0.6540 0.7528
-0.500 0.1636 0.01154 0.00456 -0.0317 0.6486 0.7654
-0.250 0.1907 0.01154 0.00450 -0.0314 0.6441 0.7780
0.000 0.2169 0.01155 0.00452 -0.0310 0.6383 0.7906
0.250 0.2448 0.01155 0.00454 -0.0309 0.6327 0.8031
0.500 0.2739 0.01156 0.00452 -0.0311 0.6279 0.8161
0.750 0.3021 0.01159 0.00457 -0.0311 0.6221 0.8298
1.000 0.3327 0.01162 0.00461 -0.0316 0.6160 0.8429
1.250 0.3675 0.01167 0.00462 -0.0330 0.6110 0.8547
1.500 0.4010 0.01174 0.00473 -0.0342 0.6040 0.8669
1.750 0.4355 0.01181 0.00477 -0.0356 0.5975 0.8792
2.000 0.4752 0.01191 0.00487 -0.0381 0.5906 0.8881
2.250 0.5111 0.01201 0.00496 -0.0398 0.5832 0.8985
2.500 0.5505 0.01212 0.00505 -0.0423 0.5763 0.9064
2.750 0.5862 0.01223 0.00517 -0.0440 0.5679 0.9153
3.000 0.6240 0.01236 0.00526 -0.0462 0.5603 0.9222
3.250 0.6567 0.01250 0.00540 -0.0472 0.5513 0.9314
3.500 0.6914 0.01265 0.00553 -0.0487 0.5429 0.9385
3.750 0.7225 0.01280 0.00568 -0.0495 0.5337 0.9472
4.000 0.7548 0.01296 0.00584 -0.0506 0.5246 0.9552
4.250 0.7866 0.01312 0.00597 -0.0516 0.5149 0.9631
4.500 0.8162 0.01329 0.00616 -0.0522 0.5041 0.9722
4.750 0.8494 0.01346 0.00631 -0.0536 0.4928 0.9790
5.000 0.8816 0.01364 0.00646 -0.0548 0.4806 0.9857
5.250 0.9155 0.01383 0.00663 -0.0564 0.4677 0.9916
5.500 0.9499 0.01401 0.00681 -0.0582 0.4536 0.9967
5.750 0.9791 0.01420 0.00698 -0.0589 0.4394 1.0000
6.000 0.9926 0.01441 0.00716 -0.0564 0.4272 1.0000
6.250 1.0056 0.01465 0.00737 -0.0537 0.4144 1.0000
6.500 1.0179 0.01492 0.00760 -0.0509 0.4012 1.0000
6.750 1.0299 0.01521 0.00786 -0.0481 0.3877 1.0000
7.000 1.0412 0.01553 0.00815 -0.0451 0.3735 1.0000
7.250 1.0513 0.01589 0.00846 -0.0420 0.3592 1.0000
7.500 1.0602 0.01627 0.00881 -0.0387 0.3449 1.0000
7.750 1.0677 0.01669 0.00918 -0.0351 0.3306 1.0000
8.000 1.0723 0.01711 0.00956 -0.0310 0.3174 1.0000
8.250 1.0745 0.01754 0.00994 -0.0265 0.3052 1.0000
8.500 1.0774 0.01803 0.01039 -0.0223 0.2928 1.0000
8.750 1.0828 0.01855 0.01089 -0.0186 0.2807 1.0000
9.000 1.0886 0.01912 0.01145 -0.0153 0.2696 1.0000
9.250 1.0937 0.01979 0.01209 -0.0120 0.2590 1.0000
9.500 1.1000 0.02049 0.01279 -0.0091 0.2483 1.0000
9.750 1.1073 0.02123 0.01353 -0.0065 0.2384 1.0000
10.000 1.1128 0.02211 0.01439 -0.0038 0.2288 1.0000
10.250 1.1200 0.02299 0.01528 -0.0016 0.2190 1.0000
10.500 1.1268 0.02395 0.01625 0.0006 0.2098 1.0000
10.750 1.1321 0.02506 0.01734 0.0027 0.2009 1.0000
11.000 1.1404 0.02607 0.01839 0.0044 0.1921 1.0000
11.250 1.1457 0.02730 0.01961 0.0062 0.1839 1.0000
11.500 1.1532 0.02847 0.02080 0.0078 0.1755 1.0000
11.750 1.1591 0.02977 0.02213 0.0093 0.1684 1.0000
12.000 1.1655 0.03109 0.02347 0.0107 0.1604 1.0000
12.250 1.1711 0.03251 0.02491 0.0120 0.1541 1.0000
12.500 1.1775 0.03392 0.02636 0.0132 0.1470 1.0000
12.750 1.1816 0.03554 0.02799 0.0144 0.1413 1.0000
13.000 1.1884 0.03699 0.02952 0.0154 0.1349 1.0000
13.250 1.1912 0.03879 0.03133 0.0164 0.1295 1.0000
13.500 1.1975 0.04037 0.03298 0.0172 0.1241 1.0000
13.750 1.2015 0.04217 0.03482 0.0180 0.1188 1.0000
14.000 1.2039 0.04416 0.03684 0.0188 0.1143 1.0000
14.250 1.2095 0.04593 0.03869 0.0194 0.1094 1.0000
14.500 1.2117 0.04807 0.04086 0.0200 0.1049 1.0000
14.750 1.2140 0.05024 0.04310 0.0204 0.1011 1.0000
15.000 1.2185 0.05225 0.04519 0.0208 0.0971 1.0000
15.250 1.2197 0.05464 0.04764 0.0210 0.0934 1.0000
15.500 1.2194 0.05725 0.05027 0.0212 0.0903 1.0000
15.750 1.2233 0.05947 0.05261 0.0213 0.0867 1.0000
16.000 1.2244 0.06204 0.05525 0.0213 0.0834 1.0000
16.250 1.2226 0.06497 0.05822 0.0212 0.0806 1.0000
16.500 1.2226 0.06775 0.06108 0.0210 0.0780 1.0000
16.750 1.2242 0.07040 0.06384 0.0208 0.0753 1.0000
17.000 1.2239 0.07334 0.06687 0.0204 0.0729 1.0000
17.250 1.2209 0.07664 0.07022 0.0199 0.0705 1.0000
17.500 1.2171 0.08008 0.07369 0.0193 0.0684 1.0000
17.750 1.2178 0.08301 0.07676 0.0187 0.0664 1.0000
18.000 1.2165 0.08625 0.08012 0.0180 0.0643 1.0000
18.250 1.2134 0.08978 0.08374 0.0171 0.0623 1.0000
18.500 1.2092 0.09348 0.08750 0.0161 0.0606 1.0000
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Polar data table (+)
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