S8035 for RC aerobatic 14% thick (s8035-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: S8035 for RC aerobatic 14% thick (s8035-il) Reynolds number: 200,000 Max Cl/Cd: 52.04 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s8035-il-200000.txt Download as CSV file: xf-s8035-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.250 -0.9350 0.10677 0.10237 -0.0262 1.0000 0.0413
-17.000 -0.9706 0.09640 0.09180 -0.0325 1.0000 0.0410
-16.750 -1.0022 0.08741 0.08259 -0.0379 1.0000 0.0409
-16.500 -1.0269 0.08016 0.07511 -0.0421 1.0000 0.0410
-16.250 -1.0482 0.07393 0.06866 -0.0454 1.0000 0.0411
-16.000 -1.0682 0.06842 0.06292 -0.0483 1.0000 0.0415
-15.750 -1.0826 0.06366 0.05796 -0.0499 1.0000 0.0417
-15.500 -1.0868 0.05994 0.05419 -0.0503 1.0000 0.0428
-15.250 -1.0857 0.05733 0.05155 -0.0506 1.0000 0.0438
-15.000 -1.0876 0.05452 0.04866 -0.0511 1.0000 0.0448
-14.750 -1.0908 0.05166 0.04568 -0.0514 1.0000 0.0457
-14.500 -1.0949 0.04883 0.04270 -0.0515 1.0000 0.0468
-14.250 -1.0981 0.04620 0.03989 -0.0512 1.0000 0.0480
-14.000 -1.1009 0.04380 0.03729 -0.0507 1.0000 0.0490
-13.750 -1.1040 0.04166 0.03492 -0.0498 1.0000 0.0500
-13.500 -1.0946 0.03935 0.03264 -0.0488 1.0000 0.0521
-13.250 -1.0893 0.03775 0.03102 -0.0478 1.0000 0.0539
-13.000 -1.0844 0.03617 0.02935 -0.0465 1.0000 0.0557
-12.750 -1.0803 0.03464 0.02767 -0.0450 1.0000 0.0577
-12.500 -1.0767 0.03317 0.02601 -0.0432 1.0000 0.0598
-12.250 -1.0669 0.03153 0.02445 -0.0418 1.0000 0.0627
-12.000 -1.0603 0.03041 0.02329 -0.0398 1.0000 0.0655
-11.750 -1.0534 0.02934 0.02207 -0.0377 1.0000 0.0686
-11.500 -1.0453 0.02798 0.02068 -0.0355 1.0000 0.0721
-11.250 -1.0384 0.02703 0.01974 -0.0331 1.0000 0.0756
-11.000 -1.0312 0.02627 0.01889 -0.0303 1.0000 0.0799
-10.750 -1.0233 0.02524 0.01783 -0.0275 1.0000 0.0841
-10.500 -1.0165 0.02450 0.01711 -0.0245 1.0000 0.0883
-10.250 -1.0060 0.02388 0.01636 -0.0218 1.0000 0.0934
-10.000 -0.9957 0.02292 0.01545 -0.0193 1.0000 0.0986
-9.750 -0.9836 0.02233 0.01481 -0.0168 1.0000 0.1046
-9.500 -0.9713 0.02153 0.01401 -0.0144 1.0000 0.1108
-9.250 -0.9581 0.02096 0.01343 -0.0121 1.0000 0.1178
-9.000 -0.9449 0.02025 0.01273 -0.0098 1.0000 0.1252
-8.750 -0.9302 0.01976 0.01219 -0.0076 1.0000 0.1336
-8.500 -0.9167 0.01910 0.01160 -0.0053 1.0000 0.1422
-8.250 -0.9016 0.01858 0.01105 -0.0031 1.0000 0.1521
-8.000 -0.8866 0.01810 0.01058 -0.0009 1.0000 0.1625
-7.750 -0.8724 0.01754 0.01009 0.0014 1.0000 0.1729
-7.500 -0.8574 0.01704 0.00961 0.0036 1.0000 0.1841
-7.250 -0.8422 0.01662 0.00919 0.0058 1.0000 0.1962
-7.000 -0.8272 0.01623 0.00882 0.0080 1.0000 0.2091
-6.750 -0.8132 0.01581 0.00848 0.0104 1.0000 0.2221
-6.500 -0.7993 0.01544 0.00817 0.0128 1.0000 0.2355
-6.250 -0.7854 0.01511 0.00788 0.0151 1.0000 0.2496
-6.000 -0.7714 0.01482 0.00764 0.0175 1.0000 0.2647
-5.750 -0.7572 0.01457 0.00744 0.0197 1.0000 0.2802
-5.500 -0.7428 0.01435 0.00727 0.0219 1.0000 0.2965
-5.250 -0.7268 0.01416 0.00711 0.0237 0.9997 0.3140
-5.000 -0.6844 0.01396 0.00701 0.0203 0.9936 0.3398
-4.750 -0.6439 0.01374 0.00685 0.0174 0.9864 0.3659
-4.500 -0.6034 0.01349 0.00671 0.0146 0.9795 0.3909
-4.250 -0.5638 0.01324 0.00653 0.0120 0.9719 0.4157
-4.000 -0.5265 0.01299 0.00636 0.0100 0.9637 0.4398
-3.750 -0.4853 0.01274 0.00619 0.0073 0.9573 0.4647
-3.500 -0.4493 0.01250 0.00603 0.0057 0.9484 0.4886
-3.250 -0.4065 0.01222 0.00585 0.0028 0.9427 0.5137
-3.000 -0.3696 0.01199 0.00568 0.0012 0.9340 0.5386
-2.750 -0.3270 0.01170 0.00550 -0.0015 0.9277 0.5628
-2.500 -0.2917 0.01149 0.00534 -0.0027 0.9175 0.5858
-2.250 -0.2510 0.01123 0.00516 -0.0049 0.9101 0.6075
-2.000 -0.2197 0.01107 0.00506 -0.0051 0.8973 0.6277
-1.750 -0.1886 0.01093 0.00496 -0.0053 0.8843 0.6484
-1.500 -0.1588 0.01083 0.00488 -0.0052 0.8709 0.6686
-1.250 -0.1302 0.01074 0.00484 -0.0047 0.8563 0.6874
-1.000 -0.1032 0.01067 0.00480 -0.0040 0.8407 0.7058
-0.750 -0.0771 0.01063 0.00478 -0.0030 0.8246 0.7240
-0.500 -0.0513 0.01060 0.00476 -0.0020 0.8083 0.7415
-0.250 -0.0256 0.01058 0.00474 -0.0010 0.7920 0.7587
0.000 0.0000 0.01058 0.00474 0.0000 0.7754 0.7754
0.250 0.0256 0.01058 0.00474 0.0010 0.7587 0.7919
0.500 0.0513 0.01060 0.00476 0.0020 0.7416 0.8083
0.750 0.0770 0.01063 0.00478 0.0030 0.7240 0.8246
1.000 0.1032 0.01067 0.00480 0.0040 0.7059 0.8408
1.250 0.1302 0.01074 0.00484 0.0047 0.6873 0.8564
1.500 0.1588 0.01083 0.00488 0.0052 0.6687 0.8709
1.750 0.1886 0.01093 0.00496 0.0053 0.6484 0.8843
2.000 0.2197 0.01107 0.00506 0.0051 0.6277 0.8973
2.250 0.2510 0.01123 0.00516 0.0049 0.6076 0.9101
2.500 0.2917 0.01149 0.00534 0.0027 0.5858 0.9175
2.750 0.3271 0.01170 0.00550 0.0015 0.5629 0.9277
3.000 0.3696 0.01199 0.00568 -0.0012 0.5385 0.9340
3.250 0.4065 0.01222 0.00585 -0.0028 0.5138 0.9427
3.500 0.4492 0.01249 0.00602 -0.0057 0.4887 0.9483
3.750 0.4852 0.01274 0.00619 -0.0072 0.4647 0.9573
4.000 0.5266 0.01299 0.00636 -0.0100 0.4401 0.9637
4.250 0.5638 0.01324 0.00653 -0.0120 0.4158 0.9719
4.500 0.6034 0.01349 0.00671 -0.0146 0.3910 0.9795
4.750 0.6440 0.01374 0.00685 -0.0174 0.3659 0.9864
5.000 0.6844 0.01396 0.00701 -0.0203 0.3396 0.9936
5.250 0.7268 0.01416 0.00711 -0.0237 0.3142 0.9997
5.500 0.7428 0.01434 0.00726 -0.0219 0.2965 1.0000
5.750 0.7571 0.01456 0.00743 -0.0197 0.2803 1.0000
6.000 0.7713 0.01482 0.00764 -0.0175 0.2647 1.0000
6.250 0.7854 0.01511 0.00787 -0.0151 0.2496 1.0000
6.500 0.7993 0.01544 0.00816 -0.0128 0.2356 1.0000
6.750 0.8132 0.01581 0.00848 -0.0104 0.2222 1.0000
7.000 0.8272 0.01623 0.00881 -0.0080 0.2090 1.0000
7.250 0.8422 0.01661 0.00919 -0.0058 0.1962 1.0000
7.500 0.8574 0.01704 0.00961 -0.0036 0.1841 1.0000
7.750 0.8724 0.01753 0.01009 -0.0014 0.1730 1.0000
8.000 0.8866 0.01809 0.01057 0.0009 0.1625 1.0000
8.250 0.9016 0.01858 0.01105 0.0031 0.1521 1.0000
8.500 0.9167 0.01910 0.01160 0.0053 0.1422 1.0000
8.750 0.9302 0.01975 0.01218 0.0076 0.1336 1.0000
9.000 0.9449 0.02025 0.01273 0.0098 0.1251 1.0000
9.250 0.9581 0.02096 0.01342 0.0121 0.1178 1.0000
9.500 0.9714 0.02154 0.01401 0.0144 0.1108 1.0000
9.750 0.9836 0.02232 0.01480 0.0168 0.1046 1.0000
10.000 0.9959 0.02292 0.01545 0.0192 0.0986 1.0000
10.250 1.0062 0.02389 0.01637 0.0217 0.0934 1.0000
10.500 1.0167 0.02451 0.01711 0.0244 0.0883 1.0000
10.750 1.0236 0.02524 0.01782 0.0275 0.0841 1.0000
11.000 1.0314 0.02628 0.01889 0.0302 0.0798 1.0000
11.250 1.0387 0.02703 0.01974 0.0330 0.0757 1.0000
11.500 1.0455 0.02798 0.02067 0.0355 0.0721 1.0000
11.750 1.0539 0.02932 0.02205 0.0376 0.0687 1.0000
12.000 1.0609 0.03040 0.02328 0.0398 0.0656 1.0000
12.250 1.0675 0.03153 0.02445 0.0417 0.0627 1.0000
12.500 1.0774 0.03319 0.02602 0.0431 0.0598 1.0000
12.750 1.0814 0.03463 0.02766 0.0449 0.0578 1.0000
13.000 1.0851 0.03616 0.02934 0.0465 0.0557 1.0000
13.250 1.0895 0.03772 0.03098 0.0477 0.0537 1.0000
13.500 1.0954 0.03933 0.03263 0.0488 0.0521 1.0000
13.750 1.1047 0.04157 0.03483 0.0497 0.0500 1.0000
14.000 1.1021 0.04380 0.03729 0.0506 0.0491 1.0000
14.250 1.0991 0.04622 0.03992 0.0512 0.0480 1.0000
14.500 1.0955 0.04878 0.04264 0.0514 0.0467 1.0000
14.750 1.0921 0.05155 0.04556 0.0513 0.0456 1.0000
15.000 1.0890 0.05440 0.04854 0.0510 0.0447 1.0000
15.250 1.0872 0.05724 0.05145 0.0506 0.0437 1.0000
15.500 1.0884 0.05986 0.05410 0.0502 0.0428 1.0000
15.750 1.0844 0.06353 0.05783 0.0498 0.0417 1.0000
16.000 1.0678 0.06854 0.06305 0.0479 0.0414 1.0000
16.250 1.0487 0.07395 0.06869 0.0451 0.0411 1.0000
16.500 1.0279 0.08019 0.07515 0.0419 0.0410 1.0000
16.750 1.0037 0.08736 0.08253 0.0378 0.0409 1.0000
17.000 0.9731 0.09616 0.09156 0.0323 0.0409 1.0000
17.250 0.9330 0.10744 0.10305 0.0254 0.0412 1.0000
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Polar data table (+)
Polar graphs
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