S4233-136-84 (s4233-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: S4233-136-84 (s4233-il) Reynolds number: 100,000 Max Cl/Cd: 52.23 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s4233-il-100000.txt Download as CSV file: xf-s4233-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: S4233-136-84
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3179 0.09953 0.09503 -0.0457 1.0000 0.1286
-9.250 -0.3454 0.09813 0.09381 -0.0458 1.0000 0.1328
-9.000 -0.3872 0.09824 0.09410 -0.0429 1.0000 0.1336
-8.750 -0.4285 0.09824 0.09426 -0.0398 1.0000 0.1339
-8.500 -0.4065 0.09480 0.09083 -0.0354 1.0000 0.1369
-8.250 -0.4099 0.09377 0.08985 -0.0316 1.0000 0.1398
-8.000 -0.4153 0.09129 0.08742 -0.0325 0.9973 0.1439
-7.750 -0.4306 0.08488 0.08108 -0.0447 0.9857 0.1510
-7.500 -0.4239 0.07973 0.07586 -0.0545 0.9748 0.1631
-7.250 -0.3879 0.07716 0.07331 -0.0512 0.9730 0.1698
-7.000 -0.4565 0.05139 0.04597 -0.0738 0.9507 0.0793
-6.750 -0.4284 0.04665 0.04100 -0.0764 0.9456 0.0731
-6.500 -0.4177 0.04228 0.03547 -0.0755 0.9360 0.0648
-6.250 -0.3873 0.03809 0.03098 -0.0777 0.9313 0.0630
-6.000 -0.3661 0.03543 0.02795 -0.0774 0.9239 0.0616
-5.750 -0.3346 0.03286 0.02492 -0.0785 0.9181 0.0606
-5.500 -0.2927 0.03052 0.02213 -0.0810 0.9148 0.0609
-5.250 -0.2744 0.02933 0.02073 -0.0793 0.9058 0.0620
-5.000 -0.2335 0.02800 0.01912 -0.0814 0.9015 0.0653
-4.750 -0.2079 0.02665 0.01791 -0.0814 0.8950 0.0708
-4.500 -0.1777 0.02572 0.01689 -0.0817 0.8886 0.0771
-4.250 -0.1400 0.02428 0.01557 -0.0834 0.8849 0.0926
-4.000 -0.1301 0.02307 0.01483 -0.0809 0.8754 0.1499
-3.750 -0.1055 0.02123 0.01436 -0.0811 0.8705 0.4114
-3.500 -0.0912 0.02127 0.01478 -0.0786 0.8620 0.5179
-3.250 -0.0652 0.02147 0.01518 -0.0772 0.8561 0.6031
-3.000 -0.0432 0.02176 0.01547 -0.0754 0.8494 0.6496
-2.750 -0.0217 0.02199 0.01568 -0.0735 0.8421 0.6866
-2.500 0.0112 0.02202 0.01562 -0.0732 0.8383 0.7241
-2.250 0.0205 0.02241 0.01603 -0.0696 0.8284 0.7502
-2.000 0.0495 0.02239 0.01594 -0.0684 0.8239 0.7807
-1.750 0.0606 0.02272 0.01626 -0.0651 0.8151 0.8071
-1.500 0.0856 0.02270 0.01617 -0.0635 0.8096 0.8355
-1.250 0.1054 0.02284 0.01627 -0.0612 0.8032 0.8613
-1.000 0.1275 0.02297 0.01635 -0.0596 0.7959 0.8878
-0.750 0.1698 0.02277 0.01603 -0.0611 0.7925 0.9136
-0.500 0.2095 0.02311 0.01628 -0.0636 0.7848 0.9371
-0.250 0.2711 0.02298 0.01601 -0.0696 0.7804 0.9556
0.000 0.3446 0.02258 0.01545 -0.0776 0.7777 0.9677
0.250 0.4050 0.02256 0.01533 -0.0844 0.7715 0.9825
0.500 0.4674 0.02228 0.01497 -0.0915 0.7656 0.9961
0.750 0.5004 0.02191 0.01450 -0.0927 0.7612 1.0000
1.000 0.4884 0.02263 0.01521 -0.0877 0.7494 1.0000
1.250 0.5094 0.02236 0.01485 -0.0864 0.7453 1.0000
1.500 0.5015 0.02319 0.01564 -0.0818 0.7334 1.0000
1.750 0.5294 0.02307 0.01543 -0.0816 0.7287 1.0000
2.000 0.5408 0.02374 0.01605 -0.0797 0.7185 1.0000
2.250 0.5770 0.02335 0.01559 -0.0803 0.7150 1.0000
2.500 0.5877 0.02423 0.01646 -0.0785 0.7037 1.0000
2.750 0.6245 0.02380 0.01597 -0.0791 0.7001 1.0000
3.000 0.6369 0.02469 0.01687 -0.0775 0.6891 1.0000
3.250 0.6741 0.02421 0.01636 -0.0781 0.6852 1.0000
3.500 0.6877 0.02508 0.01725 -0.0766 0.6743 1.0000
3.750 0.7250 0.02457 0.01672 -0.0772 0.6702 1.0000
4.000 0.7398 0.02538 0.01759 -0.0758 0.6594 1.0000
4.250 0.7773 0.02484 0.01703 -0.0763 0.6551 1.0000
4.500 0.7928 0.02562 0.01786 -0.0750 0.6443 1.0000
4.750 0.8308 0.02502 0.01726 -0.0756 0.6397 1.0000
5.000 0.8468 0.02576 0.01809 -0.0742 0.6288 1.0000
5.250 0.8858 0.02509 0.01742 -0.0749 0.6241 1.0000
5.500 0.9021 0.02578 0.01821 -0.0735 0.6129 1.0000
5.750 0.9429 0.02501 0.01745 -0.0744 0.6082 1.0000
6.000 0.9588 0.02568 0.01823 -0.0729 0.5965 1.0000
6.250 0.9825 0.02590 0.01853 -0.0721 0.5868 1.0000
6.500 1.0188 0.02532 0.01799 -0.0725 0.5794 1.0000
6.750 1.0384 0.02571 0.01850 -0.0713 0.5679 1.0000
7.000 1.0666 0.02559 0.01846 -0.0709 0.5580 1.0000
7.250 1.1021 0.02500 0.01790 -0.0711 0.5486 1.0000
7.500 1.1234 0.02515 0.01816 -0.0699 0.5357 1.0000
7.750 1.1475 0.02509 0.01820 -0.0689 0.5227 1.0000
8.000 1.1732 0.02490 0.01809 -0.0680 0.5089 1.0000
8.250 1.1982 0.02470 0.01796 -0.0671 0.4943 1.0000
8.500 1.2220 0.02456 0.01788 -0.0659 0.4786 1.0000
8.750 1.2447 0.02443 0.01780 -0.0647 0.4618 1.0000
9.000 1.2675 0.02427 0.01765 -0.0634 0.4435 1.0000
9.250 1.2806 0.02453 0.01801 -0.0610 0.4237 1.0000
9.500 1.2932 0.02480 0.01834 -0.0585 0.4029 1.0000
9.750 1.3041 0.02514 0.01868 -0.0558 0.3811 1.0000
10.000 1.3061 0.02572 0.01930 -0.0521 0.3571 1.0000
10.250 1.3021 0.02649 0.02004 -0.0477 0.3325 1.0000
10.500 1.2955 0.02760 0.02109 -0.0435 0.3061 1.0000
10.750 1.2875 0.02911 0.02249 -0.0399 0.2784 1.0000
11.000 1.2780 0.03103 0.02430 -0.0367 0.2494 1.0000
11.250 1.2677 0.03336 0.02650 -0.0340 0.2198 1.0000
11.500 1.2560 0.03609 0.02907 -0.0317 0.1908 1.0000
11.750 1.2427 0.03926 0.03205 -0.0297 0.1632 1.0000
12.000 1.2286 0.04277 0.03536 -0.0281 0.1389 1.0000
12.250 1.2155 0.04647 0.03891 -0.0269 0.1167 1.0000
12.500 1.2019 0.05036 0.04260 -0.0258 0.0997 1.0000
12.750 1.1919 0.05410 0.04621 -0.0249 0.0846 1.0000
13.000 1.1874 0.05738 0.04936 -0.0239 0.0733 1.0000
13.250 1.1887 0.06016 0.05213 -0.0230 0.0647 1.0000
13.500 1.1969 0.06235 0.05434 -0.0218 0.0581 1.0000
13.750 1.2132 0.06387 0.05564 -0.0204 0.0523 1.0000
14.000 1.2224 0.06623 0.05827 -0.0197 0.0493 1.0000
14.250 1.2382 0.06820 0.06038 -0.0187 0.0469 1.0000
14.500 1.2553 0.07025 0.06248 -0.0179 0.0448 1.0000
14.750 1.2922 0.07261 0.06485 -0.0166 0.0428 1.0000
15.000 1.2884 0.07632 0.06887 -0.0164 0.0423 1.0000
15.250 1.2809 0.08042 0.07329 -0.0166 0.0419 1.0000
15.500 1.2703 0.08490 0.07808 -0.0171 0.0415 1.0000
15.750 1.2566 0.08988 0.08335 -0.0182 0.0412 1.0000
16.000 1.2435 0.09518 0.08892 -0.0195 0.0413 1.0000
16.250 1.2244 0.10114 0.09516 -0.0217 0.0409 1.0000
16.500 1.2066 0.10754 0.10181 -0.0243 0.0412 1.0000
16.750 1.1865 0.11450 0.10901 -0.0277 0.0413 1.0000
17.000 1.1651 0.12213 0.11686 -0.0318 0.0416 1.0000
17.250 1.1435 0.13028 0.12520 -0.0364 0.0420 1.0000
17.500 1.1226 0.13889 0.13396 -0.0415 0.0424 1.0000
17.750 1.1037 0.14771 0.14290 -0.0468 0.0428 1.0000
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Polar data table (+)
Polar graphs
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