S8036 (16%) (s8036-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: S8036 (16%) (s8036-il) Reynolds number: 500,000 Max Cl/Cd: 87.28 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s8036-il-500000.txt Download as CSV file: xf-s8036-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -0.4599 0.11226 0.10981 -0.0464 1.0000 0.0162
-15.250 -0.6145 0.10640 0.10372 -0.0450 1.0000 0.0154
-15.000 -0.6910 0.08499 0.08201 -0.0583 1.0000 0.0149
-14.750 -0.7407 0.07246 0.06919 -0.0660 1.0000 0.0143
-14.500 -0.7701 0.06492 0.06145 -0.0701 1.0000 0.0143
-14.250 -0.8042 0.05768 0.05393 -0.0731 1.0000 0.0141
-14.000 -0.8454 0.05041 0.04624 -0.0746 1.0000 0.0138
-13.750 -0.8479 0.04801 0.04379 -0.0745 1.0000 0.0140
-13.500 -0.8639 0.04433 0.03988 -0.0738 1.0000 0.0139
-13.250 -0.8736 0.04146 0.03684 -0.0727 1.0000 0.0140
-13.000 -0.8796 0.03909 0.03432 -0.0711 1.0000 0.0141
-12.750 -0.8878 0.03655 0.03156 -0.0689 1.0000 0.0139
-12.500 -0.8858 0.03526 0.03022 -0.0670 1.0000 0.0143
-12.250 -0.8891 0.03325 0.02802 -0.0644 1.0000 0.0141
-12.000 -0.8885 0.03185 0.02652 -0.0618 1.0000 0.0143
-11.750 -0.8875 0.03058 0.02514 -0.0588 1.0000 0.0145
-11.500 -0.8863 0.02920 0.02363 -0.0556 1.0000 0.0145
-11.250 -0.8851 0.02814 0.02248 -0.0521 1.0000 0.0147
-11.000 -0.8849 0.02724 0.02150 -0.0482 1.0000 0.0148
-10.750 -0.8882 0.02646 0.02064 -0.0434 1.0000 0.0150
-10.500 -0.8692 0.02536 0.01942 -0.0429 0.9981 0.0153
-10.250 -0.8368 0.02425 0.01817 -0.0450 0.9947 0.0157
-10.000 -0.8069 0.02281 0.01663 -0.0465 0.9907 0.0161
-9.750 -0.7766 0.02151 0.01530 -0.0482 0.9857 0.0164
-9.500 -0.7494 0.02049 0.01427 -0.0490 0.9773 0.0168
-9.250 -0.7239 0.01964 0.01338 -0.0493 0.9650 0.0175
-9.000 -0.6969 0.01878 0.01247 -0.0497 0.9532 0.0182
-8.750 -0.6609 0.01803 0.01162 -0.0519 0.9459 0.0191
-8.500 -0.6261 0.01676 0.01036 -0.0543 0.9356 0.0203
-8.250 -0.5796 0.01597 0.00952 -0.0589 0.9273 0.0219
-8.000 -0.5352 0.01496 0.00845 -0.0632 0.9144 0.0242
-7.750 -0.4965 0.01437 0.00775 -0.0659 0.8962 0.0268
-7.500 -0.4724 0.01379 0.00710 -0.0656 0.8750 0.0302
-7.250 -0.4530 0.01337 0.00661 -0.0642 0.8568 0.0344
-7.000 -0.4342 0.01303 0.00621 -0.0625 0.8417 0.0399
-6.500 -0.3973 0.01240 0.00553 -0.0590 0.8171 0.0559
-6.250 -0.3780 0.01211 0.00523 -0.0574 0.8071 0.0673
-6.000 -0.3597 0.01178 0.00493 -0.0557 0.7974 0.0826
-5.500 -0.3219 0.01112 0.00440 -0.0524 0.7804 0.1303
-5.250 -0.3040 0.01072 0.00414 -0.0506 0.7729 0.1676
-5.000 -0.2876 0.01025 0.00388 -0.0485 0.7653 0.2200
-4.750 -0.2712 0.00977 0.00361 -0.0465 0.7586 0.2845
-4.500 -0.2563 0.00924 0.00339 -0.0441 0.7516 0.3589
-4.250 -0.2402 0.00882 0.00321 -0.0419 0.7453 0.4290
-4.000 -0.2220 0.00853 0.00310 -0.0399 0.7395 0.4873
-3.750 -0.2018 0.00835 0.00304 -0.0382 0.7331 0.5310
-3.500 -0.1795 0.00827 0.00301 -0.0370 0.7273 0.5652
-3.250 -0.1557 0.00825 0.00299 -0.0360 0.7220 0.5900
-3.000 -0.1315 0.00822 0.00297 -0.0351 0.7164 0.6082
-2.750 -0.1065 0.00821 0.00293 -0.0344 0.7109 0.6227
-2.500 -0.0806 0.00824 0.00291 -0.0339 0.7058 0.6358
-2.250 -0.0559 0.00824 0.00290 -0.0331 0.7003 0.6493
-2.000 -0.0307 0.00824 0.00289 -0.0324 0.6950 0.6618
-1.750 -0.0040 0.00827 0.00287 -0.0320 0.6899 0.6721
-1.500 0.0207 0.00828 0.00287 -0.0312 0.6845 0.6832
-1.250 0.0462 0.00826 0.00288 -0.0306 0.6790 0.6945
-1.000 0.0725 0.00829 0.00287 -0.0301 0.6740 0.7044
-0.750 0.0984 0.00830 0.00288 -0.0297 0.6689 0.7130
-0.500 0.1243 0.00829 0.00286 -0.0292 0.6633 0.7209
-0.250 0.1511 0.00829 0.00285 -0.0288 0.6583 0.7282
0.000 0.1774 0.00834 0.00285 -0.0285 0.6533 0.7355
0.250 0.2038 0.00829 0.00285 -0.0281 0.6477 0.7420
0.500 0.2300 0.00830 0.00284 -0.0277 0.6424 0.7493
0.750 0.2570 0.00833 0.00284 -0.0275 0.6371 0.7563
1.000 0.2824 0.00830 0.00286 -0.0269 0.6310 0.7638
1.250 0.3080 0.00831 0.00284 -0.0263 0.6251 0.7718
1.500 0.3347 0.00832 0.00287 -0.0260 0.6193 0.7792
1.750 0.3595 0.00831 0.00288 -0.0254 0.6128 0.7876
2.000 0.3858 0.00831 0.00289 -0.0250 0.6065 0.7952
2.250 0.4106 0.00832 0.00292 -0.0243 0.5997 0.8044
2.500 0.4359 0.00830 0.00293 -0.0237 0.5922 0.8132
2.750 0.4603 0.00832 0.00295 -0.0229 0.5847 0.8237
3.000 0.4852 0.00829 0.00299 -0.0222 0.5762 0.8339
3.250 0.5100 0.00832 0.00303 -0.0216 0.5685 0.8456
3.500 0.5344 0.00832 0.00308 -0.0208 0.5603 0.8589
3.750 0.5608 0.00834 0.00315 -0.0204 0.5521 0.8728
4.000 0.5888 0.00836 0.00323 -0.0205 0.5433 0.8880
4.250 0.6205 0.00843 0.00334 -0.0213 0.5335 0.9036
4.500 0.6573 0.00856 0.00348 -0.0233 0.5222 0.9178
4.750 0.6966 0.00870 0.00364 -0.0259 0.5080 0.9297
5.000 0.7387 0.00890 0.00382 -0.0291 0.4917 0.9372
5.250 0.7770 0.00912 0.00401 -0.0315 0.4749 0.9454
5.500 0.8138 0.00941 0.00424 -0.0336 0.4564 0.9520
5.750 0.8453 0.00969 0.00449 -0.0346 0.4373 0.9611
6.000 0.8745 0.01002 0.00475 -0.0351 0.4150 0.9714
6.250 0.9083 0.01043 0.00506 -0.0367 0.3876 0.9777
6.500 0.9391 0.01093 0.00541 -0.0379 0.3578 0.9852
6.750 0.9729 0.01145 0.00578 -0.0397 0.3265 0.9909
7.250 1.0411 0.01258 0.00660 -0.0439 0.2627 0.9998
7.500 1.0457 0.01292 0.00686 -0.0397 0.2447 1.0000
7.750 1.0493 0.01328 0.00715 -0.0353 0.2289 1.0000
8.000 1.0507 0.01365 0.00744 -0.0303 0.2148 1.0000
8.250 1.0512 0.01400 0.00774 -0.0252 0.2017 1.0000
8.500 1.0551 0.01438 0.00807 -0.0209 0.1897 1.0000
8.750 1.0600 0.01482 0.00847 -0.0168 0.1783 1.0000
9.000 1.0654 0.01532 0.00892 -0.0130 0.1682 1.0000
9.250 1.0727 0.01582 0.00939 -0.0097 0.1587 1.0000
9.500 1.0809 0.01635 0.00991 -0.0067 0.1502 1.0000
9.750 1.0874 0.01700 0.01052 -0.0035 0.1424 1.0000
10.000 1.0974 0.01757 0.01111 -0.0010 0.1357 1.0000
10.250 1.1045 0.01833 0.01183 0.0017 0.1290 1.0000
10.500 1.1145 0.01901 0.01254 0.0039 0.1231 1.0000
10.750 1.1236 0.01979 0.01332 0.0060 0.1178 1.0000
11.000 1.1297 0.02080 0.01431 0.0084 0.1130 1.0000
11.250 1.1423 0.02151 0.01508 0.0099 0.1092 1.0000
11.500 1.1515 0.02246 0.01603 0.0116 0.1049 1.0000
11.750 1.1563 0.02373 0.01729 0.0136 0.1010 1.0000
12.000 1.1689 0.02456 0.01819 0.0148 0.0982 1.0000
12.250 1.1796 0.02555 0.01923 0.0161 0.0951 1.0000
12.500 1.1875 0.02676 0.02045 0.0174 0.0922 1.0000
12.750 1.1903 0.02837 0.02206 0.0191 0.0889 1.0000
13.000 1.2026 0.02935 0.02312 0.0200 0.0869 1.0000
13.250 1.2134 0.03047 0.02430 0.0209 0.0844 1.0000
13.500 1.2213 0.03181 0.02568 0.0219 0.0820 1.0000
13.750 1.2256 0.03348 0.02735 0.0230 0.0795 1.0000
14.000 1.2296 0.03519 0.02910 0.0240 0.0773 1.0000
14.250 1.2399 0.03645 0.03045 0.0247 0.0756 1.0000
14.500 1.2482 0.03790 0.03196 0.0253 0.0735 1.0000
14.750 1.2549 0.03952 0.03363 0.0260 0.0715 1.0000
15.000 1.2569 0.04158 0.03570 0.0267 0.0692 1.0000
15.250 1.2592 0.04364 0.03781 0.0274 0.0673 1.0000
15.500 1.2675 0.04525 0.03952 0.0277 0.0658 1.0000
15.750 1.2740 0.04705 0.04139 0.0280 0.0640 1.0000
16.000 1.2788 0.04906 0.04346 0.0282 0.0623 1.0000
16.250 1.2802 0.05144 0.04585 0.0284 0.0604 1.0000
16.500 1.2786 0.05406 0.04849 0.0288 0.0586 1.0000
16.750 1.2850 0.05606 0.05062 0.0287 0.0574 1.0000
17.000 1.2895 0.05829 0.05293 0.0286 0.0560 1.0000
17.250 1.2938 0.06059 0.05530 0.0284 0.0543 1.0000
17.500 1.2941 0.06334 0.05809 0.0280 0.0527 1.0000
17.750 1.2921 0.06633 0.06111 0.0278 0.0516 1.0000
18.000 1.2918 0.06920 0.06405 0.0274 0.0501 1.0000
18.250 1.2935 0.07194 0.06689 0.0269 0.0490 1.0000
18.500 1.2941 0.07485 0.06990 0.0263 0.0480 1.0000
18.750 1.2942 0.07786 0.07300 0.0255 0.0469 1.0000
19.000 1.2927 0.08113 0.07632 0.0247 0.0457 1.0000
19.250 1.2877 0.08483 0.08005 0.0237 0.0446 1.0000
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Polar data table (+)
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