S4233-136-84 (s4233-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: S4233-136-84 (s4233-il) Reynolds number: 1,000,000 Max Cl/Cd: 121.18 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s4233-il-1000000-n5.txt Download as CSV file: xf-s4233-il-1000000-n5.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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.6545 0.06258 0.06054 -0.0627 1.0000 0.0059
-12.750 -0.6910 0.04699 0.04456 -0.0796 0.9593 0.0058
-12.500 -0.7056 0.03981 0.03703 -0.0874 0.9199 0.0058
-12.250 -0.7150 0.03661 0.03362 -0.0884 0.8960 0.0058
-12.000 -0.7288 0.03350 0.03029 -0.0885 0.8769 0.0058
-11.750 -0.7369 0.03137 0.02798 -0.0875 0.8618 0.0059
-11.500 -0.7468 0.02955 0.02597 -0.0848 0.8484 0.0059
-11.000 -0.7417 0.02638 0.02241 -0.0810 0.8287 0.0060
-10.750 -0.7292 0.02521 0.02108 -0.0799 0.8205 0.0060
-10.500 -0.7153 0.02394 0.01964 -0.0789 0.8128 0.0061
-10.250 -0.6980 0.02300 0.01855 -0.0781 0.8057 0.0062
-10.000 -0.6810 0.02178 0.01717 -0.0774 0.7987 0.0063
-9.750 -0.6624 0.02072 0.01595 -0.0766 0.7915 0.0064
-9.500 -0.6429 0.01961 0.01468 -0.0760 0.7850 0.0065
-9.250 -0.6218 0.01870 0.01363 -0.0754 0.7784 0.0066
-9.000 -0.6002 0.01780 0.01259 -0.0749 0.7721 0.0067
-8.750 -0.5774 0.01703 0.01169 -0.0745 0.7654 0.0068
-8.500 -0.5544 0.01629 0.01083 -0.0741 0.7593 0.0069
-8.250 -0.5302 0.01565 0.01009 -0.0738 0.7533 0.0071
-8.000 -0.5058 0.01506 0.00940 -0.0735 0.7468 0.0072
-7.750 -0.4807 0.01455 0.00879 -0.0733 0.7409 0.0073
-7.500 -0.4553 0.01406 0.00822 -0.0731 0.7347 0.0074
-7.250 -0.4296 0.01365 0.00772 -0.0729 0.7287 0.0074
-7.000 -0.4051 0.01294 0.00694 -0.0727 0.7228 0.0076
-6.750 -0.3800 0.01236 0.00628 -0.0724 0.7167 0.0079
-6.500 -0.3539 0.01194 0.00579 -0.0723 0.7112 0.0080
-6.250 -0.3273 0.01159 0.00539 -0.0723 0.7052 0.0082
-6.000 -0.3006 0.01126 0.00500 -0.0722 0.6992 0.0084
-5.750 -0.2735 0.01095 0.00464 -0.0722 0.6938 0.0086
-5.500 -0.2463 0.01067 0.00431 -0.0722 0.6878 0.0088
-5.250 -0.2190 0.01041 0.00399 -0.0722 0.6822 0.0091
-5.000 -0.1914 0.01015 0.00369 -0.0722 0.6767 0.0094
-4.750 -0.1638 0.00995 0.00344 -0.0723 0.6708 0.0099
-4.500 -0.1359 0.00977 0.00322 -0.0724 0.6656 0.0102
-4.250 -0.1082 0.00952 0.00293 -0.0724 0.6598 0.0106
-4.000 -0.0804 0.00931 0.00267 -0.0725 0.6540 0.0112
-3.750 -0.0524 0.00914 0.00247 -0.0726 0.6489 0.0118
-3.500 -0.0242 0.00900 0.00230 -0.0727 0.6430 0.0125
-3.000 0.0324 0.00876 0.00199 -0.0729 0.6323 0.0151
-2.750 0.0601 0.00850 0.00181 -0.0730 0.6266 0.0374
-2.500 0.0873 0.00817 0.00165 -0.0731 0.6212 0.0889
-2.250 0.1150 0.00789 0.00152 -0.0733 0.6158 0.1370
-2.000 0.1426 0.00764 0.00142 -0.0734 0.6100 0.1888
-1.750 0.1701 0.00737 0.00133 -0.0736 0.6048 0.2517
-1.500 0.1977 0.00709 0.00126 -0.0738 0.5993 0.3191
-1.250 0.2251 0.00684 0.00121 -0.0739 0.5935 0.3920
-1.000 0.2530 0.00666 0.00119 -0.0741 0.5882 0.4479
-0.750 0.2812 0.00656 0.00117 -0.0743 0.5822 0.4869
-0.250 0.3379 0.00647 0.00118 -0.0746 0.5709 0.5404
0.000 0.3663 0.00645 0.00119 -0.0747 0.5647 0.5626
0.250 0.3946 0.00645 0.00121 -0.0749 0.5589 0.5825
0.500 0.4231 0.00645 0.00123 -0.0751 0.5525 0.5995
1.000 0.4799 0.00650 0.00129 -0.0754 0.5397 0.6283
1.250 0.5081 0.00653 0.00134 -0.0755 0.5326 0.6419
1.500 0.5364 0.00656 0.00138 -0.0757 0.5261 0.6553
1.750 0.5645 0.00660 0.00143 -0.0758 0.5184 0.6690
2.000 0.5926 0.00664 0.00149 -0.0759 0.5114 0.6821
2.250 0.6206 0.00670 0.00155 -0.0760 0.5032 0.6947
2.500 0.6486 0.00676 0.00162 -0.0761 0.4958 0.7075
2.750 0.6762 0.00682 0.00170 -0.0761 0.4873 0.7202
3.000 0.7040 0.00688 0.00178 -0.0762 0.4792 0.7332
3.250 0.7313 0.00697 0.00187 -0.0762 0.4703 0.7466
3.500 0.7588 0.00704 0.00197 -0.0762 0.4612 0.7609
3.750 0.7859 0.00712 0.00208 -0.0762 0.4523 0.7762
4.000 0.8126 0.00723 0.00220 -0.0761 0.4418 0.7930
4.250 0.8393 0.00731 0.00232 -0.0760 0.4312 0.8115
4.500 0.8653 0.00742 0.00246 -0.0757 0.4205 0.8324
4.750 0.8906 0.00753 0.00261 -0.0753 0.4089 0.8560
5.000 0.9150 0.00764 0.00277 -0.0747 0.3965 0.8844
5.250 0.9379 0.00774 0.00293 -0.0737 0.3833 0.9223
5.750 0.9980 0.00824 0.00333 -0.0753 0.3426 1.0000
6.000 1.0214 0.00861 0.00359 -0.0748 0.3177 1.0000
6.250 1.0439 0.00904 0.00387 -0.0741 0.2906 1.0000
6.500 1.0651 0.00953 0.00421 -0.0733 0.2590 1.0000
6.750 1.0846 0.01013 0.00462 -0.0722 0.2228 1.0000
7.000 1.1033 0.01074 0.00505 -0.0710 0.1897 1.0000
7.250 1.1210 0.01138 0.00552 -0.0696 0.1572 1.0000
7.500 1.1391 0.01196 0.00596 -0.0683 0.1330 1.0000
7.750 1.1553 0.01261 0.00647 -0.0667 0.1074 1.0000
8.000 1.1700 0.01328 0.00701 -0.0649 0.0842 1.0000
8.250 1.1840 0.01387 0.00752 -0.0628 0.0668 1.0000
8.500 1.1938 0.01452 0.00808 -0.0601 0.0515 1.0000
8.750 1.2047 0.01515 0.00865 -0.0576 0.0398 1.0000
9.000 1.2150 0.01586 0.00932 -0.0553 0.0294 1.0000
9.250 1.2245 0.01666 0.01007 -0.0529 0.0195 1.0000
9.500 1.2334 0.01755 0.01091 -0.0507 0.0113 1.0000
9.750 1.2455 0.01830 0.01168 -0.0489 0.0090 1.0000
10.000 1.2586 0.01904 0.01244 -0.0474 0.0079 1.0000
10.250 1.2718 0.01981 0.01324 -0.0459 0.0072 1.0000
10.500 1.2845 0.02063 0.01410 -0.0445 0.0068 1.0000
10.750 1.2967 0.02152 0.01503 -0.0431 0.0066 1.0000
11.000 1.3082 0.02248 0.01604 -0.0418 0.0062 1.0000
11.250 1.3182 0.02359 0.01719 -0.0404 0.0059 1.0000
11.500 1.3287 0.02469 0.01834 -0.0391 0.0057 1.0000
11.750 1.3395 0.02580 0.01951 -0.0380 0.0056 1.0000
12.000 1.3498 0.02698 0.02074 -0.0369 0.0055 1.0000
12.250 1.3593 0.02828 0.02209 -0.0358 0.0054 1.0000
12.500 1.3677 0.02968 0.02355 -0.0348 0.0052 1.0000
12.750 1.3759 0.03114 0.02508 -0.0338 0.0051 1.0000
13.000 1.3840 0.03265 0.02664 -0.0329 0.0050 1.0000
13.250 1.3904 0.03434 0.02839 -0.0321 0.0048 1.0000
13.500 1.3970 0.03606 0.03019 -0.0313 0.0047 1.0000
13.750 1.4034 0.03786 0.03205 -0.0307 0.0047 1.0000
14.000 1.4083 0.03986 0.03412 -0.0301 0.0046 1.0000
14.250 1.4112 0.04211 0.03644 -0.0295 0.0045 1.0000
14.500 1.4144 0.04442 0.03881 -0.0291 0.0044 1.0000
14.750 1.4169 0.04687 0.04134 -0.0288 0.0042 1.0000
15.000 1.4169 0.04968 0.04423 -0.0287 0.0041 1.0000
15.250 1.4175 0.05251 0.04714 -0.0286 0.0041 1.0000
15.500 1.4129 0.05604 0.05078 -0.0288 0.0040 1.0000
15.750 1.4123 0.05921 0.05403 -0.0290 0.0039 1.0000
16.000 1.4143 0.06211 0.05702 -0.0294 0.0039 1.0000
16.250 1.4149 0.06527 0.06026 -0.0299 0.0039 1.0000
16.500 1.4111 0.06911 0.06420 -0.0306 0.0039 1.0000
16.750 1.4122 0.07237 0.06754 -0.0314 0.0039 1.0000
17.000 1.4091 0.07626 0.07153 -0.0324 0.0038 1.0000
17.250 1.4057 0.08031 0.07567 -0.0335 0.0038 1.0000
17.500 1.4018 0.08453 0.08000 -0.0348 0.0037 1.0000
17.750 1.3993 0.08861 0.08418 -0.0361 0.0037 1.0000
18.000 1.3941 0.09318 0.08884 -0.0377 0.0037 1.0000
18.250 1.3894 0.09774 0.09351 -0.0394 0.0037 1.0000
18.500 1.3860 0.10219 0.09805 -0.0412 0.0036 1.0000
18.750 1.3778 0.10752 0.10349 -0.0434 0.0036 1.0000
19.000 1.3709 0.11269 0.10876 -0.0456 0.0036 1.0000
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Polar data table (+)
Polar graphs
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