S8035 for RC aerobatic 14% thick (s8035-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: S8035 for RC aerobatic 14% thick (s8035-il) Reynolds number: 500,000 Max Cl/Cd: 70.55 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s8035-il-500000.txt Download as CSV file: xf-s8035-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: S8035 for RC aerobatic 14% thick
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
------ -------- --------- --------- -------- -------- --------
-18.750 -1.0863 0.10248 0.09856 -0.0223 1.0000 0.0210
-18.500 -1.0943 0.09748 0.09347 -0.0248 1.0000 0.0213
-18.250 -1.1039 0.09232 0.08821 -0.0272 1.0000 0.0217
-18.000 -1.1123 0.08750 0.08329 -0.0294 1.0000 0.0219
-17.750 -1.1205 0.08268 0.07837 -0.0317 1.0000 0.0223
-17.500 -1.1285 0.07798 0.07355 -0.0338 1.0000 0.0227
-17.250 -1.1356 0.07355 0.06900 -0.0358 1.0000 0.0229
-17.000 -1.1398 0.06947 0.06480 -0.0376 1.0000 0.0232
-16.750 -1.1517 0.06486 0.06011 -0.0392 1.0000 0.0236
-16.500 -1.1626 0.06036 0.05556 -0.0408 1.0000 0.0242
-16.250 -1.1701 0.05632 0.05144 -0.0423 1.0000 0.0246
-16.000 -1.1767 0.05251 0.04755 -0.0435 1.0000 0.0251
-15.750 -1.1795 0.04925 0.04420 -0.0445 1.0000 0.0255
-15.500 -1.1826 0.04605 0.04091 -0.0453 1.0000 0.0260
-15.250 -1.1828 0.04328 0.03804 -0.0459 1.0000 0.0267
-15.000 -1.1823 0.04066 0.03533 -0.0462 1.0000 0.0273
-14.750 -1.1799 0.03834 0.03290 -0.0463 1.0000 0.0279
-14.500 -1.1778 0.03610 0.03056 -0.0462 1.0000 0.0286
-14.250 -1.1842 0.03322 0.02760 -0.0458 1.0000 0.0293
-14.000 -1.1843 0.03108 0.02541 -0.0451 1.0000 0.0302
-13.750 -1.1802 0.02940 0.02368 -0.0442 1.0000 0.0312
-13.500 -1.1742 0.02799 0.02220 -0.0431 1.0000 0.0323
-13.250 -1.1667 0.02675 0.02087 -0.0419 1.0000 0.0335
-13.000 -1.1578 0.02569 0.01972 -0.0405 1.0000 0.0346
-12.750 -1.1597 0.02406 0.01805 -0.0381 1.0000 0.0360
-12.500 -1.1544 0.02299 0.01695 -0.0358 1.0000 0.0377
-12.250 -1.1455 0.02219 0.01610 -0.0337 1.0000 0.0394
-12.000 -1.1343 0.02155 0.01539 -0.0316 1.0000 0.0412
-11.750 -1.1323 0.02057 0.01438 -0.0282 1.0000 0.0434
-11.500 -1.1264 0.01986 0.01367 -0.0250 1.0000 0.0459
-11.250 -1.1175 0.01935 0.01311 -0.0220 1.0000 0.0484
-11.000 -1.1104 0.01882 0.01252 -0.0185 1.0000 0.0509
-10.750 -1.1029 0.01813 0.01185 -0.0153 1.0000 0.0545
-10.500 -1.0888 0.01768 0.01137 -0.0130 1.0000 0.0579
-10.250 -1.0761 0.01715 0.01080 -0.0105 1.0000 0.0617
-10.000 -1.0628 0.01663 0.01030 -0.0081 1.0000 0.0659
-9.750 -1.0461 0.01627 0.00990 -0.0061 1.0000 0.0697
-9.500 -1.0325 0.01573 0.00937 -0.0037 1.0000 0.0746
-9.250 -1.0163 0.01533 0.00898 -0.0017 1.0000 0.0796
-9.000 -1.0002 0.01492 0.00856 0.0004 1.0000 0.0847
-8.750 -0.9842 0.01452 0.00819 0.0025 1.0000 0.0911
-8.500 -0.9677 0.01416 0.00782 0.0046 1.0000 0.0975
-8.250 -0.9517 0.01380 0.00748 0.0067 1.0000 0.1046
-8.000 -0.9359 0.01345 0.00715 0.0089 1.0000 0.1120
-7.750 -0.9202 0.01316 0.00688 0.0110 1.0000 0.1199
-7.500 -0.9059 0.01284 0.00660 0.0134 1.0000 0.1284
-7.250 -0.8800 0.01254 0.00633 0.0135 0.9986 0.1395
-7.000 -0.8427 0.01220 0.00605 0.0112 0.9954 0.1540
-6.750 -0.8055 0.01186 0.00577 0.0090 0.9923 0.1695
-6.500 -0.7701 0.01150 0.00547 0.0071 0.9878 0.1847
-6.250 -0.7329 0.01117 0.00521 0.0050 0.9841 0.2009
-6.000 -0.6972 0.01084 0.00494 0.0032 0.9795 0.2187
-5.750 -0.6624 0.01051 0.00468 0.0016 0.9735 0.2366
-5.500 -0.6245 0.01021 0.00443 -0.0006 0.9698 0.2546
-5.250 -0.5935 0.00989 0.00418 -0.0013 0.9616 0.2726
-5.000 -0.5569 0.00956 0.00393 -0.0032 0.9570 0.2927
-4.750 -0.5235 0.00927 0.00371 -0.0044 0.9493 0.3130
-4.500 -0.4862 0.00898 0.00349 -0.0063 0.9429 0.3352
-4.250 -0.4519 0.00870 0.00329 -0.0077 0.9329 0.3557
-4.000 -0.4163 0.00846 0.00309 -0.0092 0.9220 0.3764
-3.750 -0.3834 0.00827 0.00291 -0.0101 0.9084 0.3955
-3.500 -0.3546 0.00811 0.00277 -0.0102 0.8930 0.4148
-3.000 -0.3021 0.00788 0.00256 -0.0092 0.8625 0.4510
-2.750 -0.2768 0.00778 0.00248 -0.0084 0.8473 0.4701
-2.500 -0.2516 0.00770 0.00240 -0.0077 0.8322 0.4891
-2.250 -0.2266 0.00762 0.00233 -0.0069 0.8165 0.5087
-2.000 -0.2018 0.00754 0.00227 -0.0061 0.8003 0.5282
-1.750 -0.1768 0.00748 0.00221 -0.0053 0.7841 0.5470
-1.500 -0.1516 0.00742 0.00216 -0.0045 0.7685 0.5649
-1.250 -0.1263 0.00738 0.00212 -0.0038 0.7529 0.5820
-1.000 -0.1009 0.00734 0.00208 -0.0030 0.7373 0.5998
-0.750 -0.0756 0.00732 0.00206 -0.0023 0.7214 0.6181
-0.500 -0.0503 0.00730 0.00204 -0.0016 0.7056 0.6363
-0.250 -0.0251 0.00728 0.00203 -0.0008 0.6891 0.6542
0.000 0.0000 0.00727 0.00203 0.0000 0.6718 0.6718
0.250 0.0251 0.00728 0.00203 0.0008 0.6542 0.6891
0.500 0.0503 0.00730 0.00204 0.0016 0.6363 0.7055
0.750 0.0756 0.00732 0.00206 0.0023 0.6182 0.7214
1.000 0.1009 0.00734 0.00208 0.0030 0.5998 0.7373
1.250 0.1263 0.00738 0.00212 0.0038 0.5820 0.7528
1.500 0.1516 0.00742 0.00216 0.0045 0.5649 0.7685
1.750 0.1768 0.00748 0.00221 0.0052 0.5471 0.7841
2.000 0.2018 0.00754 0.00227 0.0061 0.5282 0.8003
2.250 0.2266 0.00762 0.00233 0.0069 0.5088 0.8166
2.500 0.2516 0.00770 0.00240 0.0077 0.4891 0.8322
2.750 0.2768 0.00779 0.00248 0.0084 0.4698 0.8474
3.000 0.3021 0.00788 0.00256 0.0092 0.4512 0.8625
3.500 0.3546 0.00811 0.00277 0.0102 0.4148 0.8930
3.750 0.3834 0.00827 0.00291 0.0101 0.3957 0.9084
4.000 0.4163 0.00846 0.00309 0.0092 0.3764 0.9219
4.250 0.4519 0.00870 0.00329 0.0077 0.3559 0.9329
4.500 0.4862 0.00898 0.00349 0.0063 0.3352 0.9429
4.750 0.5235 0.00927 0.00371 0.0043 0.3128 0.9493
5.000 0.5569 0.00956 0.00393 0.0032 0.2926 0.9570
5.250 0.5935 0.00989 0.00418 0.0013 0.2722 0.9616
5.500 0.6245 0.01021 0.00443 0.0006 0.2546 0.9698
5.750 0.6625 0.01051 0.00468 -0.0016 0.2366 0.9735
6.000 0.6972 0.01084 0.00494 -0.0032 0.2185 0.9795
6.250 0.7328 0.01117 0.00521 -0.0050 0.2010 0.9841
6.500 0.7702 0.01150 0.00547 -0.0072 0.1848 0.9878
6.750 0.8055 0.01186 0.00577 -0.0090 0.1693 0.9923
7.000 0.8428 0.01220 0.00605 -0.0112 0.1541 0.9954
7.250 0.8801 0.01254 0.00633 -0.0135 0.1394 0.9986
7.500 0.9059 0.01284 0.00660 -0.0134 0.1284 1.0000
7.750 0.9202 0.01316 0.00687 -0.0110 0.1199 1.0000
8.000 0.9359 0.01345 0.00715 -0.0089 0.1119 1.0000
8.250 0.9517 0.01379 0.00748 -0.0067 0.1046 1.0000
8.500 0.9677 0.01416 0.00782 -0.0046 0.0975 1.0000
8.750 0.9842 0.01452 0.00819 -0.0025 0.0912 1.0000
9.000 1.0002 0.01492 0.00856 -0.0004 0.0849 1.0000
9.250 1.0163 0.01533 0.00898 0.0016 0.0795 1.0000
9.500 1.0326 0.01573 0.00937 0.0037 0.0746 1.0000
9.750 1.0461 0.01627 0.00990 0.0061 0.0697 1.0000
10.000 1.0628 0.01662 0.01030 0.0081 0.0659 1.0000
10.250 1.0762 0.01715 0.01080 0.0105 0.0617 1.0000
10.500 1.0888 0.01769 0.01137 0.0130 0.0580 1.0000
10.750 1.1029 0.01813 0.01185 0.0152 0.0546 1.0000
11.000 1.1104 0.01883 0.01252 0.0185 0.0509 1.0000
11.250 1.1178 0.01935 0.01310 0.0219 0.0484 1.0000
11.500 1.1267 0.01986 0.01366 0.0249 0.0459 1.0000
11.750 1.1330 0.02055 0.01436 0.0281 0.0436 1.0000
12.000 1.1347 0.02155 0.01539 0.0316 0.0412 1.0000
12.250 1.1457 0.02219 0.01610 0.0337 0.0395 1.0000
12.500 1.1551 0.02297 0.01693 0.0358 0.0376 1.0000
12.750 1.1608 0.02401 0.01800 0.0379 0.0360 1.0000
13.000 1.1583 0.02568 0.01970 0.0404 0.0344 1.0000
13.250 1.1674 0.02673 0.02086 0.0418 0.0334 1.0000
13.500 1.1748 0.02796 0.02217 0.0431 0.0323 1.0000
13.750 1.1813 0.02936 0.02363 0.0441 0.0312 1.0000
14.000 1.1854 0.03103 0.02535 0.0450 0.0301 1.0000
14.250 1.1849 0.03322 0.02760 0.0457 0.0294 1.0000
14.500 1.1772 0.03621 0.03066 0.0461 0.0284 1.0000
14.750 1.1811 0.03830 0.03285 0.0462 0.0279 1.0000
15.000 1.1837 0.04060 0.03526 0.0461 0.0272 1.0000
15.250 1.1853 0.04310 0.03786 0.0457 0.0265 1.0000
15.500 1.1837 0.04603 0.04090 0.0452 0.0261 1.0000
15.750 1.1817 0.04912 0.04407 0.0444 0.0255 1.0000
16.000 1.1774 0.05255 0.04759 0.0433 0.0250 1.0000
16.250 1.1723 0.05621 0.05132 0.0420 0.0244 1.0000
16.500 1.1640 0.06033 0.05552 0.0406 0.0241 1.0000
16.750 1.1542 0.06471 0.05996 0.0390 0.0236 1.0000
17.000 1.1436 0.06922 0.06456 0.0374 0.0232 1.0000
17.250 1.1370 0.07351 0.06896 0.0356 0.0229 1.0000
17.500 1.1307 0.07793 0.07351 0.0335 0.0226 1.0000
17.750 1.1225 0.08254 0.07823 0.0316 0.0224 1.0000
18.000 1.1147 0.08734 0.08313 0.0293 0.0220 1.0000
18.250 1.1056 0.09233 0.08822 0.0269 0.0216 1.0000
18.500 1.0968 0.09735 0.09334 0.0245 0.0213 1.0000
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Polar data table (+)
Polar graphs
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