S8035 for RC aerobatic 14% thick (s8035-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: S8035 for RC aerobatic 14% thick (s8035-il) Reynolds number: 100,000 Max Cl/Cd: 39.33 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s8035-il-100000-n5.txt Download as CSV file: xf-s8035-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.250 -0.8211 0.11730 0.11149 -0.0154 1.0000 0.0477
-16.000 -0.8922 0.09840 0.09230 -0.0267 1.0000 0.0473
-15.750 -0.9226 0.08904 0.08272 -0.0321 1.0000 0.0474
-15.500 -0.9456 0.08158 0.07503 -0.0362 1.0000 0.0479
-15.250 -0.9634 0.07537 0.06861 -0.0394 1.0000 0.0486
-15.000 -0.9779 0.06998 0.06298 -0.0419 1.0000 0.0493
-14.750 -0.9875 0.06554 0.05838 -0.0435 1.0000 0.0502
-14.500 -0.9903 0.06233 0.05515 -0.0444 1.0000 0.0515
-14.250 -0.9942 0.05904 0.05179 -0.0454 1.0000 0.0527
-14.000 -0.9985 0.05580 0.04845 -0.0462 1.0000 0.0542
-13.750 -1.0022 0.05271 0.04522 -0.0466 1.0000 0.0559
-13.500 -1.0054 0.04976 0.04208 -0.0469 1.0000 0.0578
-13.250 -1.0068 0.04709 0.03921 -0.0467 1.0000 0.0598
-13.000 -1.0062 0.04486 0.03698 -0.0463 1.0000 0.0615
-12.750 -1.0056 0.04276 0.03482 -0.0457 1.0000 0.0636
-12.500 -1.0041 0.04080 0.03275 -0.0448 1.0000 0.0663
-12.250 -1.0010 0.03897 0.03072 -0.0437 1.0000 0.0693
-12.000 -0.9982 0.03726 0.02898 -0.0423 1.0000 0.0719
-11.750 -0.9952 0.03578 0.02745 -0.0408 1.0000 0.0748
-11.500 -0.9904 0.03442 0.02599 -0.0390 1.0000 0.0786
-11.250 -0.9842 0.03315 0.02458 -0.0371 1.0000 0.0825
-11.000 -0.9804 0.03196 0.02341 -0.0348 1.0000 0.0860
-10.750 -0.9742 0.03095 0.02231 -0.0323 1.0000 0.0906
-10.500 -0.9670 0.02997 0.02122 -0.0298 1.0000 0.0954
-10.250 -0.9621 0.02905 0.02032 -0.0269 1.0000 0.0998
-10.000 -0.9526 0.02821 0.01938 -0.0244 1.0000 0.1058
-9.750 -0.9435 0.02733 0.01851 -0.0219 1.0000 0.1115
-9.500 -0.9323 0.02656 0.01768 -0.0196 1.0000 0.1182
-9.250 -0.9211 0.02577 0.01689 -0.0173 1.0000 0.1250
-9.000 -0.9084 0.02507 0.01612 -0.0150 1.0000 0.1328
-8.750 -0.8959 0.02435 0.01541 -0.0128 1.0000 0.1402
-8.500 -0.8815 0.02373 0.01470 -0.0107 1.0000 0.1494
-8.250 -0.8686 0.02305 0.01409 -0.0084 1.0000 0.1578
-8.000 -0.8538 0.02245 0.01346 -0.0063 1.0000 0.1673
-7.750 -0.8389 0.02189 0.01286 -0.0043 1.0000 0.1777
-7.500 -0.8245 0.02132 0.01234 -0.0021 1.0000 0.1882
-7.250 -0.8093 0.02080 0.01183 -0.0001 1.0000 0.1994
-7.000 -0.7938 0.02032 0.01135 0.0020 1.0000 0.2118
-6.750 -0.7783 0.01987 0.01091 0.0040 1.0000 0.2252
-6.500 -0.7632 0.01944 0.01049 0.0061 1.0000 0.2387
-6.250 -0.7484 0.01903 0.01012 0.0083 1.0000 0.2531
-6.000 -0.7335 0.01865 0.00979 0.0105 1.0000 0.2678
-5.750 -0.7188 0.01831 0.00949 0.0126 1.0000 0.2830
-5.500 -0.7041 0.01800 0.00920 0.0148 1.0000 0.2985
-5.250 -0.6893 0.01772 0.00896 0.0169 1.0000 0.3143
-5.000 -0.6538 0.01744 0.00872 0.0149 0.9932 0.3358
-4.750 -0.6181 0.01714 0.00847 0.0130 0.9847 0.3576
-4.500 -0.5832 0.01687 0.00823 0.0113 0.9754 0.3801
-4.250 -0.5484 0.01660 0.00803 0.0097 0.9662 0.4021
-4.000 -0.5127 0.01634 0.00782 0.0080 0.9570 0.4257
-3.750 -0.4793 0.01609 0.00763 0.0068 0.9466 0.4484
-3.500 -0.4431 0.01585 0.00746 0.0052 0.9379 0.4724
-3.250 -0.4074 0.01562 0.00728 0.0037 0.9285 0.4951
-3.000 -0.3733 0.01541 0.00713 0.0026 0.9182 0.5169
-2.500 -0.3038 0.01502 0.00685 0.0003 0.8974 0.5608
-2.250 -0.2709 0.01486 0.00674 -0.0004 0.8854 0.5823
-2.000 -0.2372 0.01472 0.00662 -0.0012 0.8736 0.6041
-1.750 -0.2032 0.01458 0.00653 -0.0019 0.8614 0.6246
-1.500 -0.1728 0.01448 0.00646 -0.0020 0.8468 0.6441
-1.250 -0.1432 0.01439 0.00640 -0.0018 0.8319 0.6631
-1.000 -0.1142 0.01433 0.00635 -0.0016 0.8168 0.6816
-0.750 -0.0856 0.01428 0.00631 -0.0012 0.8013 0.6999
-0.500 -0.0570 0.01424 0.00629 -0.0009 0.7857 0.7175
-0.250 -0.0285 0.01422 0.00628 -0.0004 0.7693 0.7350
0.000 0.0000 0.01421 0.00628 0.0000 0.7524 0.7523
0.250 0.0285 0.01422 0.00628 0.0004 0.7350 0.7693
0.500 0.0570 0.01424 0.00629 0.0009 0.7176 0.7857
0.750 0.0857 0.01428 0.00631 0.0012 0.7000 0.8014
1.000 0.1142 0.01433 0.00635 0.0016 0.6816 0.8167
1.250 0.1432 0.01439 0.00640 0.0018 0.6631 0.8319
1.500 0.1728 0.01447 0.00646 0.0020 0.6441 0.8468
1.750 0.2031 0.01458 0.00653 0.0019 0.6246 0.8614
2.000 0.2372 0.01472 0.00662 0.0011 0.6042 0.8736
2.250 0.2709 0.01487 0.00674 0.0003 0.5823 0.8855
2.500 0.3038 0.01502 0.00685 -0.0003 0.5607 0.8974
3.000 0.3733 0.01541 0.00713 -0.0026 0.5169 0.9182
3.250 0.4074 0.01562 0.00728 -0.0037 0.4951 0.9285
3.500 0.4431 0.01585 0.00745 -0.0052 0.4724 0.9378
3.750 0.4793 0.01609 0.00763 -0.0068 0.4485 0.9466
4.000 0.5126 0.01634 0.00782 -0.0080 0.4258 0.9570
4.250 0.5484 0.01660 0.00803 -0.0097 0.4022 0.9662
4.500 0.5833 0.01687 0.00823 -0.0113 0.3800 0.9754
4.750 0.6181 0.01714 0.00847 -0.0130 0.3576 0.9847
5.000 0.6538 0.01744 0.00872 -0.0149 0.3358 0.9932
5.250 0.6893 0.01772 0.00896 -0.0169 0.3143 1.0000
5.500 0.7041 0.01800 0.00920 -0.0148 0.2986 1.0000
5.750 0.7188 0.01831 0.00949 -0.0126 0.2832 1.0000
6.000 0.7335 0.01865 0.00979 -0.0105 0.2679 1.0000
6.250 0.7483 0.01903 0.01012 -0.0083 0.2531 1.0000
6.500 0.7632 0.01944 0.01049 -0.0061 0.2388 1.0000
6.750 0.7783 0.01987 0.01090 -0.0040 0.2251 1.0000
7.000 0.7938 0.02032 0.01135 -0.0020 0.2118 1.0000
7.250 0.8093 0.02079 0.01182 0.0001 0.1994 1.0000
7.500 0.8245 0.02131 0.01233 0.0021 0.1881 1.0000
7.750 0.8389 0.02188 0.01286 0.0043 0.1778 1.0000
8.000 0.8538 0.02245 0.01346 0.0063 0.1673 1.0000
8.250 0.8686 0.02305 0.01408 0.0084 0.1578 1.0000
8.500 0.8815 0.02372 0.01470 0.0107 0.1494 1.0000
8.750 0.8960 0.02435 0.01541 0.0128 0.1402 1.0000
9.000 0.9084 0.02507 0.01612 0.0150 0.1328 1.0000
9.250 0.9211 0.02577 0.01689 0.0173 0.1249 1.0000
9.500 0.9324 0.02656 0.01768 0.0196 0.1182 1.0000
9.750 0.9437 0.02733 0.01851 0.0219 0.1115 1.0000
10.000 0.9528 0.02821 0.01938 0.0244 0.1058 1.0000
10.250 0.9623 0.02905 0.02032 0.0268 0.0999 1.0000
10.500 0.9672 0.02997 0.02122 0.0298 0.0954 1.0000
10.750 0.9745 0.03095 0.02231 0.0323 0.0906 1.0000
11.000 0.9807 0.03196 0.02341 0.0347 0.0860 1.0000
11.250 0.9846 0.03314 0.02457 0.0370 0.0825 1.0000
11.500 0.9908 0.03442 0.02598 0.0390 0.0786 1.0000
11.750 0.9958 0.03577 0.02744 0.0407 0.0749 1.0000
12.000 0.9989 0.03725 0.02896 0.0423 0.0720 1.0000
12.250 1.0015 0.03896 0.03070 0.0436 0.0692 1.0000
12.500 1.0048 0.04078 0.03273 0.0447 0.0663 1.0000
12.750 1.0064 0.04273 0.03479 0.0456 0.0636 1.0000
13.000 1.0070 0.04483 0.03695 0.0462 0.0615 1.0000
13.250 1.0074 0.04706 0.03918 0.0466 0.0597 1.0000
13.500 1.0064 0.04973 0.04204 0.0468 0.0578 1.0000
13.750 1.0034 0.05265 0.04516 0.0466 0.0559 1.0000
14.000 0.9995 0.05576 0.04841 0.0461 0.0542 1.0000
14.250 0.9953 0.05899 0.05174 0.0453 0.0527 1.0000
14.500 0.9915 0.06227 0.05508 0.0443 0.0514 1.0000
14.750 0.9889 0.06548 0.05831 0.0434 0.0502 1.0000
15.000 0.9789 0.06996 0.06297 0.0417 0.0493 1.0000
15.250 0.9644 0.07537 0.06860 0.0392 0.0485 1.0000
15.500 0.9468 0.08156 0.07501 0.0361 0.0479 1.0000
15.750 0.9241 0.08897 0.08264 0.0320 0.0474 1.0000
16.000 0.8920 0.09867 0.09258 0.0264 0.0472 1.0000
16.250 0.8235 0.11705 0.11124 0.0154 0.0478 1.0000
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Polar data table (+)
Polar graphs
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