S8036 (16%) (s8036-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: S8036 (16%) (s8036-il) Reynolds number: 200,000 Max Cl/Cd: 61.75 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s8036-il-200000-n5.txt Download as CSV file: xf-s8036-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.6857 0.08242 0.07779 -0.0607 1.0000 0.0143
-14.500 -0.7205 0.07283 0.06794 -0.0664 1.0000 0.0141
-14.250 -0.7435 0.06627 0.06117 -0.0697 1.0000 0.0141
-14.000 -0.7637 0.06071 0.05539 -0.0719 1.0000 0.0140
-13.750 -0.7769 0.05654 0.05105 -0.0730 1.0000 0.0142
-13.500 -0.7881 0.05286 0.04718 -0.0735 1.0000 0.0142
-13.250 -0.7984 0.04950 0.04365 -0.0734 1.0000 0.0144
-13.000 -0.8062 0.04656 0.04054 -0.0728 1.0000 0.0145
-12.750 -0.8112 0.04404 0.03785 -0.0718 1.0000 0.0146
-12.500 -0.8152 0.04186 0.03550 -0.0705 1.0000 0.0150
-12.250 -0.8166 0.03981 0.03331 -0.0689 1.0000 0.0149
-12.000 -0.8185 0.03792 0.03123 -0.0669 1.0000 0.0153
-11.750 -0.8191 0.03625 0.02934 -0.0646 1.0000 0.0157
-11.500 -0.8176 0.03467 0.02763 -0.0622 1.0000 0.0159
-11.250 -0.8154 0.03347 0.02642 -0.0597 1.0000 0.0162
-11.000 -0.8131 0.03243 0.02533 -0.0569 1.0000 0.0165
-10.750 -0.8117 0.03147 0.02433 -0.0537 1.0000 0.0168
-10.500 -0.8112 0.03059 0.02340 -0.0501 1.0000 0.0172
-10.000 -0.7794 0.02829 0.02089 -0.0485 0.9937 0.0182
-9.750 -0.7533 0.02699 0.01945 -0.0494 0.9857 0.0187
-9.250 -0.7118 0.02477 0.01713 -0.0491 0.9573 0.0200
-9.000 -0.6849 0.02376 0.01605 -0.0499 0.9463 0.0209
-8.750 -0.6570 0.02272 0.01490 -0.0507 0.9348 0.0222
-8.500 -0.6253 0.02171 0.01385 -0.0525 0.9248 0.0239
-8.250 -0.5891 0.02079 0.01284 -0.0550 0.9155 0.0261
-8.000 -0.5560 0.01988 0.01188 -0.0569 0.9033 0.0288
-7.750 -0.5227 0.01905 0.01095 -0.0587 0.8909 0.0319
-7.500 -0.4903 0.01833 0.01016 -0.0602 0.8786 0.0360
-7.250 -0.4616 0.01769 0.00946 -0.0610 0.8655 0.0415
-7.000 -0.4368 0.01716 0.00889 -0.0608 0.8520 0.0481
-6.750 -0.4138 0.01668 0.00837 -0.0603 0.8397 0.0567
-6.500 -0.3913 0.01624 0.00789 -0.0595 0.8288 0.0672
-6.250 -0.3725 0.01581 0.00748 -0.0580 0.8177 0.0797
-6.000 -0.3529 0.01540 0.00708 -0.0567 0.8082 0.0962
-5.500 -0.3155 0.01459 0.00637 -0.0536 0.7903 0.1438
-5.000 -0.2813 0.01366 0.00571 -0.0499 0.7747 0.2240
-4.750 -0.2670 0.01313 0.00541 -0.0475 0.7666 0.2830
-4.500 -0.2526 0.01260 0.00514 -0.0451 0.7600 0.3537
-4.250 -0.2385 0.01217 0.00498 -0.0425 0.7528 0.4219
-4.000 -0.2211 0.01189 0.00489 -0.0403 0.7461 0.4797
-3.750 -0.2005 0.01175 0.00483 -0.0387 0.7404 0.5240
-3.500 -0.1792 0.01167 0.00481 -0.0372 0.7338 0.5573
-3.250 -0.1560 0.01164 0.00477 -0.0361 0.7279 0.5838
-3.000 -0.1320 0.01164 0.00472 -0.0351 0.7228 0.6060
-2.750 -0.1087 0.01163 0.00471 -0.0340 0.7166 0.6248
-2.500 -0.0843 0.01163 0.00467 -0.0331 0.7110 0.6410
-2.250 -0.0591 0.01165 0.00465 -0.0323 0.7062 0.6575
-2.000 -0.0354 0.01165 0.00467 -0.0313 0.7003 0.6729
-1.750 -0.0106 0.01167 0.00464 -0.0305 0.6950 0.6857
-1.500 0.0158 0.01168 0.00459 -0.0301 0.6903 0.6961
-1.250 0.0409 0.01168 0.00458 -0.0295 0.6846 0.7049
-1.000 0.0664 0.01168 0.00455 -0.0289 0.6790 0.7133
-0.750 0.0930 0.01168 0.00450 -0.0285 0.6742 0.7210
-0.500 0.1190 0.01169 0.00450 -0.0281 0.6687 0.7285
-0.250 0.1438 0.01170 0.00448 -0.0274 0.6629 0.7367
0.000 0.1708 0.01170 0.00447 -0.0271 0.6576 0.7438
0.250 0.1962 0.01172 0.00446 -0.0266 0.6524 0.7523
0.500 0.2220 0.01172 0.00449 -0.0261 0.6462 0.7592
0.750 0.2482 0.01174 0.00448 -0.0257 0.6409 0.7671
1.000 0.2744 0.01176 0.00449 -0.0253 0.6355 0.7744
1.250 0.2998 0.01177 0.00455 -0.0248 0.6291 0.7822
1.500 0.3259 0.01179 0.00454 -0.0243 0.6235 0.7905
1.750 0.3522 0.01182 0.00460 -0.0240 0.6173 0.7985
2.000 0.3770 0.01184 0.00463 -0.0233 0.6103 0.8077
2.250 0.4050 0.01186 0.00465 -0.0233 0.6043 0.8163
2.500 0.4296 0.01189 0.00474 -0.0226 0.5964 0.8262
2.750 0.4576 0.01192 0.00478 -0.0225 0.5894 0.8360
3.000 0.4844 0.01196 0.00488 -0.0223 0.5811 0.8464
3.250 0.5124 0.01201 0.00492 -0.0223 0.5728 0.8578
3.500 0.5430 0.01208 0.00505 -0.0229 0.5625 0.8684
3.750 0.5738 0.01216 0.00513 -0.0235 0.5521 0.8797
4.000 0.6067 0.01226 0.00525 -0.0246 0.5402 0.8908
4.250 0.6417 0.01239 0.00541 -0.0262 0.5276 0.9009
4.500 0.6754 0.01253 0.00558 -0.0275 0.5152 0.9119
4.750 0.7124 0.01271 0.00575 -0.0296 0.5013 0.9199
5.000 0.7459 0.01290 0.00593 -0.0309 0.4858 0.9297
5.250 0.7815 0.01312 0.00614 -0.0327 0.4678 0.9375
5.500 0.8129 0.01338 0.00635 -0.0337 0.4468 0.9471
5.750 0.8405 0.01371 0.00660 -0.0340 0.4241 0.9584
6.000 0.8682 0.01406 0.00689 -0.0343 0.3986 0.9696
6.250 0.8941 0.01451 0.00723 -0.0344 0.3725 0.9818
6.500 0.9229 0.01503 0.00762 -0.0353 0.3439 0.9914
6.750 0.9538 0.01560 0.00806 -0.0368 0.3145 0.9990
7.250 0.9657 0.01644 0.00872 -0.0292 0.2781 1.0000
7.500 0.9687 0.01687 0.00908 -0.0248 0.2621 1.0000
7.750 0.9687 0.01730 0.00943 -0.0198 0.2472 1.0000
8.000 0.9711 0.01775 0.00983 -0.0154 0.2331 1.0000
8.250 0.9747 0.01826 0.01029 -0.0114 0.2195 1.0000
8.500 0.9797 0.01882 0.01080 -0.0077 0.2071 1.0000
8.750 0.9852 0.01943 0.01138 -0.0043 0.1962 1.0000
9.000 0.9906 0.02011 0.01202 -0.0011 0.1858 1.0000
9.250 0.9984 0.02078 0.01268 0.0016 0.1758 1.0000
9.500 1.0050 0.02156 0.01344 0.0044 0.1670 1.0000
9.750 1.0126 0.02236 0.01424 0.0068 0.1588 1.0000
10.000 1.0204 0.02322 0.01510 0.0090 0.1519 1.0000
10.250 1.0287 0.02411 0.01600 0.0111 0.1450 1.0000
10.500 1.0359 0.02512 0.01701 0.0131 0.1390 1.0000
10.750 1.0452 0.02606 0.01799 0.0148 0.1329 1.0000
11.000 1.0516 0.02723 0.01914 0.0165 0.1277 1.0000
11.250 1.0614 0.02825 0.02021 0.0180 0.1228 1.0000
11.500 1.0697 0.02939 0.02138 0.0194 0.1179 1.0000
11.750 1.0756 0.03074 0.02273 0.0208 0.1138 1.0000
12.000 1.0856 0.03185 0.02392 0.0220 0.1100 1.0000
12.250 1.0942 0.03309 0.02521 0.0231 0.1059 1.0000
12.500 1.1004 0.03454 0.02666 0.0242 0.1024 1.0000
12.750 1.1076 0.03595 0.02812 0.0252 0.0991 1.0000
13.000 1.1165 0.03726 0.02952 0.0261 0.0960 1.0000
13.250 1.1236 0.03874 0.03105 0.0270 0.0928 1.0000
13.500 1.1288 0.04040 0.03273 0.0278 0.0903 1.0000
13.750 1.1346 0.04206 0.03443 0.0286 0.0879 1.0000
14.000 1.1428 0.04355 0.03603 0.0292 0.0853 1.0000
14.250 1.1495 0.04521 0.03777 0.0298 0.0829 1.0000
14.500 1.1543 0.04707 0.03968 0.0303 0.0805 1.0000
14.750 1.1579 0.04908 0.04171 0.0307 0.0786 1.0000
15.000 1.1632 0.05097 0.04368 0.0311 0.0766 1.0000
15.250 1.1694 0.05283 0.04566 0.0314 0.0745 1.0000
15.500 1.1744 0.05485 0.04777 0.0316 0.0725 1.0000
15.750 1.1778 0.05708 0.05008 0.0317 0.0706 1.0000
16.000 1.1794 0.05951 0.05254 0.0317 0.0689 1.0000
16.250 1.1818 0.06190 0.05498 0.0317 0.0672 1.0000
16.500 1.1857 0.06422 0.05743 0.0316 0.0656 1.0000
16.750 1.1887 0.06666 0.05999 0.0314 0.0640 1.0000
17.000 1.1904 0.06931 0.06274 0.0310 0.0624 1.0000
17.250 1.1908 0.07215 0.06566 0.0305 0.0610 1.0000
17.500 1.1903 0.07513 0.06868 0.0299 0.0596 1.0000
17.750 1.1903 0.07805 0.07166 0.0294 0.0584 1.0000
18.000 1.1901 0.08114 0.07492 0.0287 0.0571 1.0000
18.250 1.1888 0.08443 0.07835 0.0278 0.0557 1.0000
18.500 1.1871 0.08781 0.08184 0.0268 0.0545 1.0000
18.750 1.1846 0.09134 0.08547 0.0257 0.0534 1.0000
19.000 1.1818 0.09495 0.08916 0.0245 0.0524 1.0000
19.250 1.1787 0.09861 0.09288 0.0231 0.0514 1.0000
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Polar data table (+)
Polar graphs
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