S4233-136-84 (s4233-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: S4233-136-84 (s4233-il) Reynolds number: 500,000 Max Cl/Cd: 111.52 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s4233-il-500000.txt Download as CSV file: xf-s4233-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.2747 0.07703 0.07499 -0.0636 0.9481 0.0284
-10.500 -0.2698 0.07447 0.07240 -0.0636 0.9345 0.0288
-10.250 -0.2674 0.07168 0.06957 -0.0638 0.9225 0.0292
-10.000 -0.2662 0.06857 0.06643 -0.0643 0.9119 0.0297
-9.750 -0.2733 0.06327 0.06110 -0.0663 0.9026 0.0301
-9.500 -0.2891 0.05563 0.05345 -0.0702 0.8944 0.0303
-9.250 -0.4422 0.05220 0.04924 -0.0886 0.8980 0.0279
-9.000 -0.4717 0.04502 0.04176 -0.0879 0.8845 0.0285
-8.750 -0.4588 0.04239 0.03915 -0.0877 0.8758 0.0290
-8.500 -0.4485 0.04046 0.03712 -0.0870 0.8676 0.0296
-8.250 -0.4370 0.03863 0.03519 -0.0864 0.8588 0.0303
-8.000 -0.4257 0.03666 0.03302 -0.0856 0.8512 0.0315
-7.750 -0.4089 0.03759 0.03346 -0.0839 0.8424 0.0347
-7.500 -0.4195 0.02497 0.01982 -0.0813 0.8355 0.0236
-7.250 -0.4012 0.02047 0.01459 -0.0793 0.8285 0.0182
-7.000 -0.3769 0.01961 0.01350 -0.0787 0.8225 0.0179
-6.750 -0.3523 0.01839 0.01214 -0.0783 0.8158 0.0179
-6.500 -0.3284 0.01704 0.01066 -0.0777 0.8095 0.0180
-6.250 -0.3043 0.01590 0.00942 -0.0772 0.8034 0.0181
-6.000 -0.2803 0.01487 0.00833 -0.0767 0.7968 0.0184
-5.500 -0.2306 0.01351 0.00686 -0.0760 0.7845 0.0194
-5.250 -0.2052 0.01297 0.00624 -0.0756 0.7785 0.0200
-5.000 -0.1791 0.01251 0.00572 -0.0754 0.7726 0.0208
-4.750 -0.1526 0.01213 0.00528 -0.0753 0.7661 0.0219
-4.500 -0.1265 0.01166 0.00470 -0.0750 0.7607 0.0229
-4.250 -0.0998 0.01121 0.00422 -0.0749 0.7543 0.0246
-4.000 -0.0726 0.01091 0.00385 -0.0747 0.7484 0.0270
-3.750 -0.0455 0.01058 0.00349 -0.0746 0.7428 0.0340
-3.500 -0.0209 0.00968 0.00306 -0.0745 0.7365 0.1359
-3.250 0.0045 0.00908 0.00282 -0.0745 0.7310 0.2383
-3.000 0.0307 0.00860 0.00266 -0.0745 0.7251 0.3308
-2.750 0.0575 0.00828 0.00254 -0.0745 0.7191 0.3995
-2.500 0.0845 0.00807 0.00246 -0.0745 0.7139 0.4612
-2.250 0.1118 0.00787 0.00243 -0.0744 0.7077 0.5192
-2.000 0.1389 0.00774 0.00242 -0.0743 0.7020 0.5716
-1.750 0.1666 0.00769 0.00241 -0.0742 0.6966 0.6055
-1.500 0.1948 0.00766 0.00239 -0.0742 0.6905 0.6274
-1.250 0.2228 0.00767 0.00235 -0.0742 0.6851 0.6474
-1.000 0.2509 0.00764 0.00235 -0.0742 0.6792 0.6660
-0.750 0.2789 0.00763 0.00234 -0.0742 0.6733 0.6833
-0.500 0.3069 0.00765 0.00234 -0.0742 0.6680 0.6996
-0.250 0.3349 0.00763 0.00235 -0.0742 0.6619 0.7154
0.000 0.3628 0.00763 0.00235 -0.0741 0.6562 0.7304
0.250 0.3907 0.00765 0.00236 -0.0741 0.6505 0.7450
0.500 0.4186 0.00764 0.00238 -0.0741 0.6444 0.7597
0.750 0.4462 0.00767 0.00239 -0.0740 0.6389 0.7748
1.000 0.4737 0.00766 0.00244 -0.0739 0.6326 0.7905
1.250 0.5010 0.00766 0.00246 -0.0738 0.6265 0.8069
1.500 0.5280 0.00768 0.00251 -0.0735 0.6207 0.8239
1.750 0.5547 0.00767 0.00256 -0.0732 0.6141 0.8421
2.250 0.6065 0.00769 0.00267 -0.0723 0.6016 0.8841
2.500 0.6313 0.00769 0.00270 -0.0715 0.5951 0.9100
2.750 0.6580 0.00770 0.00276 -0.0711 0.5886 0.9396
3.000 0.6936 0.00773 0.00280 -0.0727 0.5813 0.9670
3.250 0.7346 0.00779 0.00285 -0.0757 0.5739 0.9898
3.500 0.7671 0.00787 0.00292 -0.0769 0.5662 1.0000
3.750 0.7932 0.00798 0.00300 -0.0768 0.5589 1.0000
4.000 0.8196 0.00809 0.00309 -0.0767 0.5511 1.0000
4.250 0.8462 0.00820 0.00320 -0.0766 0.5432 1.0000
4.500 0.8727 0.00833 0.00331 -0.0765 0.5349 1.0000
4.750 0.8993 0.00845 0.00344 -0.0764 0.5261 1.0000
5.000 0.9253 0.00862 0.00356 -0.0762 0.5174 1.0000
5.250 0.9518 0.00874 0.00371 -0.0761 0.5073 1.0000
5.500 0.9778 0.00889 0.00387 -0.0759 0.4974 1.0000
5.750 1.0032 0.00908 0.00402 -0.0756 0.4866 1.0000
6.000 1.0286 0.00926 0.00421 -0.0753 0.4743 1.0000
6.250 1.0537 0.00945 0.00440 -0.0750 0.4610 1.0000
6.500 1.0784 0.00967 0.00460 -0.0746 0.4478 1.0000
6.750 1.1028 0.00991 0.00484 -0.0742 0.4342 1.0000
7.000 1.1256 0.01021 0.00509 -0.0735 0.4158 1.0000
7.250 1.1474 0.01056 0.00537 -0.0727 0.3934 1.0000
7.500 1.1687 0.01094 0.00569 -0.0718 0.3717 1.0000
7.750 1.1889 0.01137 0.00605 -0.0707 0.3487 1.0000
8.000 1.2077 0.01186 0.00645 -0.0695 0.3249 1.0000
8.250 1.2252 0.01240 0.00690 -0.0681 0.2981 1.0000
8.500 1.2392 0.01310 0.00744 -0.0661 0.2667 1.0000
8.750 1.2507 0.01387 0.00804 -0.0638 0.2353 1.0000
9.000 1.2580 0.01465 0.00869 -0.0608 0.2060 1.0000
9.250 1.2634 0.01555 0.00945 -0.0576 0.1774 1.0000
9.500 1.2682 0.01656 0.01032 -0.0546 0.1506 1.0000
9.750 1.2719 0.01771 0.01133 -0.0517 0.1241 1.0000
10.000 1.2762 0.01892 0.01241 -0.0491 0.1010 1.0000
10.250 1.2793 0.02027 0.01365 -0.0466 0.0795 1.0000
10.500 1.2804 0.02184 0.01510 -0.0441 0.0582 1.0000
10.750 1.2800 0.02361 0.01675 -0.0417 0.0392 1.0000
11.000 1.2780 0.02561 0.01866 -0.0393 0.0249 1.0000
11.250 1.2813 0.02733 0.02038 -0.0376 0.0199 1.0000
11.500 1.2831 0.02923 0.02231 -0.0360 0.0172 1.0000
11.750 1.2896 0.03083 0.02399 -0.0347 0.0160 1.0000
12.000 1.2953 0.03255 0.02578 -0.0336 0.0151 1.0000
12.250 1.3002 0.03440 0.02770 -0.0326 0.0145 1.0000
12.500 1.3009 0.03668 0.03006 -0.0316 0.0139 1.0000
12.750 1.2979 0.03939 0.03286 -0.0305 0.0134 1.0000
13.000 1.3013 0.04159 0.03516 -0.0299 0.0131 1.0000
13.250 1.3034 0.04400 0.03766 -0.0293 0.0128 1.0000
13.500 1.3046 0.04658 0.04035 -0.0289 0.0125 1.0000
13.750 1.3056 0.04928 0.04314 -0.0286 0.0122 1.0000
14.000 1.3054 0.05218 0.04613 -0.0285 0.0119 1.0000
14.250 1.3056 0.05512 0.04916 -0.0284 0.0118 1.0000
14.500 1.3048 0.05827 0.05239 -0.0285 0.0115 1.0000
14.750 1.3050 0.06136 0.05557 -0.0288 0.0114 1.0000
15.000 1.3046 0.06458 0.05886 -0.0291 0.0111 1.0000
15.250 1.3026 0.06810 0.06247 -0.0296 0.0109 1.0000
15.500 1.2991 0.07184 0.06628 -0.0301 0.0107 1.0000
15.750 1.2927 0.07589 0.07041 -0.0305 0.0104 1.0000
16.000 1.2945 0.07904 0.07365 -0.0310 0.0104 1.0000
16.250 1.2950 0.08250 0.07722 -0.0318 0.0101 1.0000
16.500 1.2962 0.08582 0.08063 -0.0325 0.0101 1.0000
16.750 1.2975 0.08918 0.08410 -0.0332 0.0100 1.0000
17.000 1.2983 0.09271 0.08774 -0.0342 0.0099 1.0000
17.250 1.2990 0.09624 0.09138 -0.0351 0.0098 1.0000
17.500 1.2992 0.09994 0.09520 -0.0362 0.0097 1.0000
17.750 1.2988 0.10376 0.09913 -0.0375 0.0096 1.0000
18.000 1.2982 0.10763 0.10313 -0.0387 0.0096 1.0000
18.250 1.2968 0.11175 0.10738 -0.0403 0.0095 1.0000
18.500 1.2943 0.11612 0.11188 -0.0421 0.0094 1.0000
18.750 1.2913 0.12064 0.11654 -0.0441 0.0094 1.0000
19.000 1.2871 0.12541 0.12145 -0.0463 0.0093 1.0000
19.250 1.2817 0.13054 0.12673 -0.0488 0.0093 1.0000
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Polar data table (+)
Polar graphs
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