S8037 (16%) (s8037-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: S8037 (16%) (s8037-il) Reynolds number: 500,000 Max Cl/Cd: 99.89 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s8037-il-500000.txt Download as CSV file: xf-s8037-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.4003 0.13760 0.13513 -0.0369 1.0000 0.0231
-14.000 -0.3962 0.13445 0.13200 -0.0377 1.0000 0.0232
-13.750 -0.5573 0.08513 0.08252 -0.0588 1.0000 0.0154
-13.500 -0.5732 0.07831 0.07568 -0.0626 1.0000 0.0149
-13.250 -0.6090 0.06782 0.06502 -0.0700 1.0000 0.0148
-13.000 -0.6626 0.05696 0.05387 -0.0763 1.0000 0.0142
-12.750 -0.6707 0.05375 0.05057 -0.0776 1.0000 0.0146
-12.500 -0.7070 0.04770 0.04427 -0.0785 1.0000 0.0142
-12.250 -0.7205 0.04488 0.04131 -0.0777 1.0000 0.0143
-12.000 -0.7508 0.04093 0.03710 -0.0751 1.0000 0.0144
-11.750 -0.7662 0.03880 0.03481 -0.0717 1.0000 0.0145
-11.500 -0.7856 0.03659 0.03242 -0.0670 1.0000 0.0143
-11.000 -0.7789 0.03200 0.02732 -0.0644 0.9908 0.0148
-10.750 -0.7645 0.02950 0.02451 -0.0642 0.9731 0.0151
-10.500 -0.7433 0.02750 0.02219 -0.0646 0.9548 0.0154
-10.000 -0.6669 0.02290 0.01714 -0.0719 0.9354 0.0162
-9.750 -0.6187 0.02143 0.01558 -0.0772 0.9229 0.0168
-9.500 -0.5757 0.02028 0.01427 -0.0812 0.9036 0.0177
-9.250 -0.5469 0.01947 0.01324 -0.0820 0.8811 0.0184
-9.000 -0.5268 0.01884 0.01241 -0.0808 0.8621 0.0188
-8.750 -0.5106 0.01797 0.01143 -0.0790 0.8465 0.0196
-8.500 -0.4946 0.01741 0.01082 -0.0771 0.8334 0.0204
-8.250 -0.4770 0.01694 0.01026 -0.0753 0.8227 0.0211
-8.000 -0.4591 0.01646 0.00968 -0.0736 0.8131 0.0217
-7.750 -0.4403 0.01607 0.00918 -0.0719 0.8041 0.0226
-7.500 -0.4263 0.01533 0.00837 -0.0695 0.7961 0.0234
-7.250 -0.4090 0.01486 0.00788 -0.0677 0.7885 0.0244
-7.000 -0.3890 0.01455 0.00750 -0.0662 0.7813 0.0258
-6.750 -0.3688 0.01423 0.00710 -0.0648 0.7749 0.0272
-6.500 -0.3521 0.01369 0.00655 -0.0627 0.7680 0.0289
-6.250 -0.3315 0.01338 0.00617 -0.0614 0.7622 0.0309
-6.000 -0.3120 0.01298 0.00574 -0.0597 0.7562 0.0332
-5.750 -0.2909 0.01267 0.00541 -0.0584 0.7503 0.0370
-5.500 -0.2703 0.01232 0.00503 -0.0570 0.7449 0.0438
-5.250 -0.2512 0.01187 0.00467 -0.0553 0.7396 0.0611
-5.000 -0.2311 0.01148 0.00439 -0.0539 0.7341 0.0862
-4.750 -0.2105 0.01113 0.00414 -0.0526 0.7292 0.1171
-4.500 -0.1899 0.01077 0.00393 -0.0512 0.7243 0.1561
-4.250 -0.1707 0.01034 0.00371 -0.0497 0.7188 0.2075
-4.000 -0.1525 0.00985 0.00348 -0.0479 0.7140 0.2777
-3.750 -0.1346 0.00939 0.00329 -0.0461 0.7095 0.3594
-3.500 -0.1173 0.00897 0.00317 -0.0441 0.7044 0.4372
-3.250 -0.0993 0.00865 0.00308 -0.0421 0.6993 0.5071
-3.000 -0.0789 0.00848 0.00304 -0.0404 0.6948 0.5613
-2.750 -0.0564 0.00839 0.00303 -0.0392 0.6900 0.5952
-2.500 -0.0326 0.00833 0.00299 -0.0382 0.6849 0.6188
-2.250 -0.0080 0.00829 0.00294 -0.0374 0.6801 0.6387
-2.000 0.0172 0.00829 0.00292 -0.0367 0.6755 0.6566
-1.750 0.0412 0.00823 0.00290 -0.0357 0.6704 0.6747
-1.500 0.0659 0.00820 0.00288 -0.0349 0.6654 0.6920
-1.250 0.0916 0.00821 0.00284 -0.0343 0.6608 0.7069
-1.000 0.1162 0.00817 0.00285 -0.0335 0.6559 0.7228
-0.750 0.1406 0.00814 0.00285 -0.0326 0.6507 0.7401
-0.500 0.1661 0.00811 0.00283 -0.0320 0.6460 0.7549
-0.250 0.1922 0.00811 0.00283 -0.0315 0.6413 0.7677
0.000 0.2174 0.00807 0.00283 -0.0309 0.6359 0.7809
0.250 0.2429 0.00805 0.00281 -0.0303 0.6307 0.7945
0.500 0.2694 0.00806 0.00280 -0.0299 0.6257 0.8077
0.750 0.2951 0.00801 0.00282 -0.0294 0.6197 0.8210
1.000 0.3218 0.00799 0.00281 -0.0290 0.6140 0.8351
1.250 0.3492 0.00799 0.00283 -0.0289 0.6085 0.8503
1.500 0.3774 0.00797 0.00287 -0.0289 0.6022 0.8667
1.750 0.4090 0.00799 0.00289 -0.0296 0.5963 0.8832
2.000 0.4440 0.00803 0.00297 -0.0311 0.5896 0.8986
2.250 0.4832 0.00810 0.00304 -0.0336 0.5824 0.9116
2.500 0.5271 0.00823 0.00315 -0.0371 0.5754 0.9198
2.750 0.5659 0.00833 0.00325 -0.0395 0.5677 0.9298
3.000 0.6096 0.00849 0.00337 -0.0430 0.5605 0.9342
3.250 0.6446 0.00862 0.00351 -0.0445 0.5523 0.9423
3.500 0.6801 0.00881 0.00366 -0.0462 0.5446 0.9478
3.750 0.7153 0.00897 0.00382 -0.0478 0.5352 0.9535
4.000 0.7476 0.00914 0.00397 -0.0488 0.5264 0.9606
4.250 0.7843 0.00931 0.00412 -0.0508 0.5165 0.9653
4.500 0.8160 0.00949 0.00429 -0.0517 0.5068 0.9725
4.750 0.8537 0.00966 0.00443 -0.0540 0.4963 0.9762
5.000 0.8865 0.00986 0.00461 -0.0552 0.4847 0.9825
5.250 0.9246 0.01000 0.00475 -0.0577 0.4722 0.9857
5.500 0.9618 0.01016 0.00488 -0.0600 0.4598 0.9895
5.750 0.9968 0.01037 0.00505 -0.0618 0.4454 0.9938
6.000 1.0344 0.01052 0.00516 -0.0643 0.4285 0.9968
6.250 1.0708 0.01072 0.00530 -0.0666 0.4098 1.0000
6.500 1.0830 0.01093 0.00545 -0.0638 0.3947 1.0000
6.750 1.0952 0.01116 0.00565 -0.0609 0.3802 1.0000
7.000 1.1069 0.01144 0.00586 -0.0580 0.3649 1.0000
7.250 1.1185 0.01173 0.00611 -0.0550 0.3503 1.0000
7.500 1.1295 0.01205 0.00638 -0.0520 0.3359 1.0000
7.750 1.1395 0.01239 0.00667 -0.0487 0.3214 1.0000
8.000 1.1482 0.01277 0.00699 -0.0452 0.3070 1.0000
8.500 1.1593 0.01348 0.00762 -0.0370 0.2804 1.0000
8.750 1.1633 0.01384 0.00795 -0.0327 0.2691 1.0000
9.000 1.1672 0.01428 0.00835 -0.0284 0.2571 1.0000
9.250 1.1714 0.01479 0.00881 -0.0245 0.2458 1.0000
9.500 1.1791 0.01527 0.00928 -0.0212 0.2342 1.0000
9.750 1.1863 0.01582 0.00981 -0.0181 0.2235 1.0000
10.000 1.1922 0.01649 0.01045 -0.0149 0.2135 1.0000
10.250 1.1999 0.01716 0.01110 -0.0122 0.2035 1.0000
10.500 1.2082 0.01787 0.01181 -0.0097 0.1945 1.0000
10.750 1.2136 0.01879 0.01269 -0.0070 0.1853 1.0000
11.000 1.2240 0.01953 0.01347 -0.0051 0.1771 1.0000
11.250 1.2305 0.02053 0.01445 -0.0029 0.1691 1.0000
11.500 1.2394 0.02147 0.01540 -0.0011 0.1612 1.0000
11.750 1.2466 0.02256 0.01649 0.0007 0.1540 1.0000
12.000 1.2545 0.02365 0.01759 0.0023 0.1468 1.0000
12.250 1.2611 0.02488 0.01883 0.0040 0.1405 1.0000
12.500 1.2695 0.02604 0.02001 0.0053 0.1341 1.0000
12.750 1.2736 0.02753 0.02149 0.0069 0.1280 1.0000
13.000 1.2828 0.02870 0.02272 0.0081 0.1222 1.0000
13.250 1.2854 0.03039 0.02438 0.0095 0.1163 1.0000
13.500 1.2938 0.03168 0.02573 0.0105 0.1112 1.0000
13.750 1.2984 0.03330 0.02737 0.0116 0.1061 1.0000
14.000 1.3013 0.03509 0.02918 0.0128 0.1017 1.0000
14.250 1.3084 0.03659 0.03074 0.0136 0.0974 1.0000
14.500 1.3102 0.03858 0.03273 0.0145 0.0927 1.0000
14.750 1.3133 0.04051 0.03471 0.0153 0.0891 1.0000
15.000 1.3189 0.04227 0.03653 0.0160 0.0854 1.0000
15.250 1.3196 0.04453 0.03880 0.0166 0.0819 1.0000
15.500 1.3189 0.04697 0.04129 0.0172 0.0786 1.0000
15.750 1.3246 0.04886 0.04326 0.0175 0.0754 1.0000
16.000 1.3260 0.05123 0.04566 0.0179 0.0724 1.0000
16.250 1.3217 0.05421 0.04865 0.0181 0.0695 1.0000
16.500 1.3240 0.05658 0.05111 0.0183 0.0672 1.0000
16.750 1.3274 0.05887 0.05348 0.0183 0.0647 1.0000
17.000 1.3275 0.06157 0.05622 0.0183 0.0623 1.0000
17.250 1.3217 0.06497 0.05965 0.0181 0.0601 1.0000
17.500 1.3207 0.06789 0.06265 0.0179 0.0580 1.0000
17.750 1.3233 0.07043 0.06529 0.0176 0.0560 1.0000
18.000 1.3226 0.07342 0.06834 0.0172 0.0544 1.0000
18.250 1.3180 0.07694 0.07190 0.0166 0.0524 1.0000
18.500 1.3086 0.08104 0.07603 0.0159 0.0504 1.0000
18.750 1.3099 0.08391 0.07901 0.0153 0.0492 1.0000
19.000 1.3089 0.08710 0.08229 0.0146 0.0479 1.0000
19.250 1.3061 0.09061 0.08587 0.0136 0.0462 1.0000
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Polar data table (+)
Polar graphs
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