S8036 (16%) (s8036-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: S8036 (16%) (s8036-il) Reynolds number: 100,000 Max Cl/Cd: 47.95 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s8036-il-100000-n5.txt Download as CSV file: xf-s8036-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.5026 0.11066 0.10503 -0.0470 1.0000 0.0267
-13.500 -0.5236 0.10113 0.09550 -0.0516 1.0000 0.0263
-13.250 -0.5715 0.08653 0.08078 -0.0604 1.0000 0.0259
-13.000 -0.6079 0.07698 0.07107 -0.0663 1.0000 0.0255
-12.750 -0.6370 0.07012 0.06404 -0.0697 1.0000 0.0253
-12.500 -0.6639 0.06446 0.05818 -0.0716 1.0000 0.0252
-12.250 -0.6851 0.06006 0.05358 -0.0721 1.0000 0.0250
-12.000 -0.7061 0.05612 0.04943 -0.0716 1.0000 0.0251
-11.750 -0.7234 0.05283 0.04594 -0.0701 1.0000 0.0252
-11.500 -0.7389 0.04999 0.04287 -0.0678 1.0000 0.0254
-11.250 -0.7521 0.04753 0.04019 -0.0648 1.0000 0.0256
-11.000 -0.7619 0.04543 0.03789 -0.0614 1.0000 0.0257
-10.750 -0.7717 0.04346 0.03570 -0.0573 1.0000 0.0261
-10.500 -0.7795 0.04173 0.03375 -0.0529 1.0000 0.0264
-10.250 -0.7852 0.04021 0.03201 -0.0485 1.0000 0.0267
-10.000 -0.7865 0.03904 0.03082 -0.0447 1.0000 0.0272
-9.750 -0.7875 0.03803 0.02978 -0.0408 1.0000 0.0276
-9.500 -0.7890 0.03719 0.02890 -0.0369 0.9996 0.0283
-9.250 -0.7587 0.03538 0.02686 -0.0389 0.9922 0.0302
-9.000 -0.7283 0.03357 0.02483 -0.0406 0.9845 0.0318
-8.750 -0.7000 0.03211 0.02333 -0.0419 0.9748 0.0333
-8.500 -0.6720 0.03063 0.02172 -0.0428 0.9648 0.0353
-8.250 -0.6438 0.02926 0.02025 -0.0437 0.9552 0.0374
-8.000 -0.6141 0.02810 0.01905 -0.0451 0.9468 0.0411
-7.750 -0.5881 0.02694 0.01784 -0.0455 0.9365 0.0445
-7.500 -0.5572 0.02585 0.01663 -0.0468 0.9292 0.0498
-7.250 -0.5305 0.02481 0.01563 -0.0474 0.9196 0.0557
-7.000 -0.5018 0.02381 0.01460 -0.0483 0.9114 0.0637
-6.750 -0.4749 0.02286 0.01365 -0.0488 0.9021 0.0740
-6.500 -0.4488 0.02200 0.01278 -0.0490 0.8930 0.0877
-6.250 -0.4230 0.02113 0.01197 -0.0492 0.8842 0.1059
-6.000 -0.3996 0.02038 0.01129 -0.0489 0.8746 0.1313
-5.750 -0.3759 0.01953 0.01061 -0.0486 0.8661 0.1672
-5.500 -0.3582 0.01876 0.01006 -0.0473 0.8561 0.2168
-5.250 -0.3396 0.01787 0.00952 -0.0460 0.8480 0.2916
-5.000 -0.3273 0.01720 0.00923 -0.0434 0.8381 0.3733
-4.750 -0.3079 0.01670 0.00907 -0.0417 0.8307 0.4569
-4.500 -0.2891 0.01657 0.00910 -0.0396 0.8220 0.5154
-4.250 -0.2655 0.01652 0.00906 -0.0384 0.8148 0.5607
-4.000 -0.2426 0.01655 0.00904 -0.0370 0.8075 0.5936
-3.750 -0.2194 0.01661 0.00905 -0.0357 0.7998 0.6199
-3.500 -0.1919 0.01664 0.00897 -0.0352 0.7943 0.6440
-3.250 -0.1721 0.01673 0.00901 -0.0333 0.7860 0.6635
-3.000 -0.1469 0.01679 0.00898 -0.0324 0.7797 0.6829
-2.750 -0.1215 0.01688 0.00901 -0.0314 0.7736 0.7008
-2.500 -0.0975 0.01698 0.00907 -0.0303 0.7665 0.7158
-2.250 -0.0675 0.01702 0.00903 -0.0303 0.7611 0.7278
-2.000 -0.0437 0.01705 0.00899 -0.0294 0.7548 0.7391
-1.750 -0.0190 0.01708 0.00896 -0.0286 0.7482 0.7494
-1.500 0.0108 0.01706 0.00885 -0.0288 0.7431 0.7582
-1.250 0.0340 0.01710 0.00884 -0.0278 0.7367 0.7677
-1.000 0.0603 0.01713 0.00882 -0.0274 0.7305 0.7760
-0.750 0.0893 0.01712 0.00873 -0.0275 0.7256 0.7851
-0.500 0.1141 0.01718 0.00877 -0.0269 0.7190 0.7934
-0.250 0.1399 0.01722 0.00877 -0.0264 0.7128 0.8023
0.000 0.1709 0.01721 0.00870 -0.0269 0.7079 0.8102
0.250 0.1958 0.01730 0.00879 -0.0264 0.7011 0.8186
0.500 0.2227 0.01733 0.00880 -0.0262 0.6948 0.8271
0.750 0.2571 0.01735 0.00876 -0.0273 0.6900 0.8343
1.000 0.2794 0.01746 0.00890 -0.0264 0.6826 0.8439
1.250 0.3121 0.01753 0.00896 -0.0273 0.6765 0.8512
1.500 0.3422 0.01755 0.00894 -0.0277 0.6712 0.8605
1.750 0.3724 0.01771 0.00916 -0.0283 0.6634 0.8679
2.000 0.4027 0.01773 0.00916 -0.0288 0.6575 0.8775
2.250 0.4377 0.01788 0.00934 -0.0303 0.6503 0.8841
2.500 0.4660 0.01795 0.00942 -0.0304 0.6429 0.8944
2.750 0.5055 0.01802 0.00949 -0.0327 0.6360 0.8999
3.000 0.5344 0.01814 0.00966 -0.0330 0.6271 0.9097
3.250 0.5730 0.01817 0.00968 -0.0351 0.6196 0.9157
3.500 0.6055 0.01829 0.00987 -0.0362 0.6097 0.9241
3.750 0.6409 0.01834 0.00993 -0.0378 0.6004 0.9314
4.000 0.6765 0.01837 0.00996 -0.0394 0.5898 0.9386
4.250 0.7083 0.01846 0.01012 -0.0404 0.5776 0.9474
4.500 0.7409 0.01851 0.01018 -0.0414 0.5656 0.9569
4.750 0.7760 0.01852 0.01020 -0.0430 0.5528 0.9650
5.000 0.8080 0.01859 0.01030 -0.0441 0.5390 0.9749
5.250 0.8404 0.01870 0.01045 -0.0454 0.5238 0.9849
5.500 0.8751 0.01879 0.01058 -0.0472 0.5072 0.9939
5.750 0.9046 0.01887 0.01067 -0.0480 0.4899 1.0000
6.000 0.9111 0.01900 0.01078 -0.0442 0.4748 1.0000
6.250 0.9184 0.01917 0.01092 -0.0406 0.4588 1.0000
6.500 0.9261 0.01938 0.01107 -0.0369 0.4413 1.0000
6.750 0.9332 0.01965 0.01128 -0.0333 0.4222 1.0000
7.000 0.9399 0.01998 0.01155 -0.0295 0.4020 1.0000
7.250 0.9458 0.02036 0.01186 -0.0257 0.3815 1.0000
7.500 0.9503 0.02082 0.01220 -0.0216 0.3609 1.0000
7.750 0.9535 0.02133 0.01260 -0.0174 0.3410 1.0000
8.000 0.9538 0.02186 0.01304 -0.0127 0.3219 1.0000
8.250 0.9544 0.02245 0.01355 -0.0083 0.3039 1.0000
8.500 0.9557 0.02313 0.01415 -0.0042 0.2866 1.0000
8.750 0.9576 0.02389 0.01484 -0.0004 0.2699 1.0000
9.000 0.9608 0.02472 0.01560 0.0030 0.2548 1.0000
9.250 0.9643 0.02563 0.01645 0.0061 0.2404 1.0000
9.500 0.9684 0.02660 0.01736 0.0089 0.2276 1.0000
10.000 0.9786 0.02870 0.01941 0.0137 0.2042 1.0000
10.250 0.9848 0.02980 0.02050 0.0157 0.1943 1.0000
10.500 0.9897 0.03103 0.02167 0.0177 0.1855 1.0000
10.750 0.9979 0.03215 0.02284 0.0193 0.1765 1.0000
11.000 1.0036 0.03344 0.02407 0.0211 0.1697 1.0000
11.250 1.0125 0.03461 0.02533 0.0224 0.1620 1.0000
11.500 1.0185 0.03598 0.02664 0.0239 0.1558 1.0000
11.750 1.0279 0.03720 0.02794 0.0251 0.1495 1.0000
12.000 1.0354 0.03855 0.02932 0.0263 0.1440 1.0000
12.250 1.0433 0.03993 0.03069 0.0274 0.1391 1.0000
12.500 1.0519 0.04129 0.03215 0.0284 0.1338 1.0000
12.750 1.0590 0.04276 0.03364 0.0294 0.1292 1.0000
13.000 1.0676 0.04418 0.03506 0.0303 0.1253 1.0000
13.250 1.0756 0.04570 0.03671 0.0311 0.1209 1.0000
13.500 1.0824 0.04728 0.03836 0.0319 0.1171 1.0000
13.750 1.0901 0.04881 0.03986 0.0327 0.1138 1.0000
14.000 1.0969 0.05054 0.04175 0.0333 0.1103 1.0000
14.250 1.1026 0.05235 0.04368 0.0339 0.1068 1.0000
14.500 1.1077 0.05420 0.04558 0.0343 0.1037 1.0000
14.750 1.1152 0.05585 0.04722 0.0349 0.1010 1.0000
15.000 1.1184 0.05807 0.04962 0.0352 0.0982 1.0000
15.250 1.1215 0.06032 0.05203 0.0354 0.0954 1.0000
15.500 1.1245 0.06257 0.05438 0.0356 0.0929 1.0000
15.750 1.1281 0.06474 0.05659 0.0357 0.0906 1.0000
16.000 1.1345 0.06670 0.05856 0.0359 0.0885 1.0000
16.250 1.1303 0.06999 0.06210 0.0356 0.0863 1.0000
16.500 1.1269 0.07324 0.06556 0.0351 0.0842 1.0000
16.750 1.1247 0.07641 0.06886 0.0346 0.0822 1.0000
17.000 1.1243 0.07935 0.07189 0.0340 0.0804 1.0000
17.250 1.1275 0.08181 0.07437 0.0337 0.0787 1.0000
17.500 1.1245 0.08523 0.07790 0.0329 0.0772 1.0000
17.750 1.1094 0.09060 0.08354 0.0311 0.0759 1.0000
18.000 1.0906 0.09673 0.08992 0.0286 0.0746 1.0000
18.250 1.0694 0.10350 0.09692 0.0257 0.0734 1.0000
18.500 1.0415 0.11178 0.10541 0.0216 0.0724 1.0000
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Polar data table (+)
Polar graphs
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