EPPLER 1233 AIRFOIL (e1233-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 1233 AIRFOIL (e1233-il) Reynolds number: 1,000,000 Max Cl/Cd: 103.31 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e1233-il-1000000-n5.txt Download as CSV file: xf-e1233-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 1233 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-17.750 -0.7487 0.10312 0.10029 -0.0580 1.0000 0.0069
-17.500 -0.8061 0.08959 0.08657 -0.0652 1.0000 0.0068
-17.250 -0.8565 0.07742 0.07418 -0.0718 1.0000 0.0067
-17.000 -0.8943 0.06759 0.06416 -0.0773 1.0000 0.0067
-16.750 -0.9206 0.06023 0.05663 -0.0812 1.0000 0.0067
-16.500 -0.9381 0.05476 0.05103 -0.0837 1.0000 0.0067
-16.250 -0.9430 0.05014 0.04629 -0.0871 0.9994 0.0068
-16.000 -0.9390 0.04563 0.04164 -0.0920 0.9977 0.0069
-15.750 -0.9296 0.04225 0.03815 -0.0958 0.9960 0.0068
-15.500 -0.9204 0.03919 0.03498 -0.0991 0.9945 0.0069
-15.250 -0.9056 0.03680 0.03250 -0.1020 0.9935 0.0069
-15.000 -0.8965 0.03464 0.03026 -0.1032 0.9915 0.0070
-14.750 -0.8831 0.03276 0.02831 -0.1046 0.9892 0.0071
-14.500 -0.8682 0.03097 0.02644 -0.1061 0.9873 0.0072
-14.250 -0.8508 0.02932 0.02471 -0.1078 0.9856 0.0073
-14.000 -0.8294 0.02788 0.02321 -0.1097 0.9843 0.0073
-13.750 -0.8054 0.02665 0.02192 -0.1117 0.9832 0.0074
-13.500 -0.7985 0.02547 0.02069 -0.1102 0.9799 0.0075
-13.250 -0.7853 0.02430 0.01946 -0.1099 0.9763 0.0075
-13.000 -0.7605 0.02347 0.01858 -0.1110 0.9739 0.0077
-12.500 -0.7401 0.02151 0.01652 -0.1083 0.9630 0.0078
-12.250 -0.7416 0.02053 0.01549 -0.1047 0.9513 0.0080
-11.750 -0.7089 0.01883 0.01369 -0.1033 0.9272 0.0083
-11.500 -0.6638 0.01784 0.01265 -0.1078 0.9175 0.0086
-11.250 -0.5895 0.01676 0.01149 -0.1179 0.9054 0.0087
-11.000 -0.4911 0.01582 0.01040 -0.1329 0.8811 0.0092
-10.750 -0.4560 0.01545 0.00977 -0.1352 0.8296 0.0095
-10.500 -0.4483 0.01518 0.00930 -0.1321 0.7922 0.0096
-10.250 -0.4417 0.01495 0.00892 -0.1287 0.7626 0.0098
-9.750 -0.4220 0.01450 0.00824 -0.1227 0.7201 0.0101
-9.500 -0.4076 0.01420 0.00785 -0.1205 0.7028 0.0105
-9.250 -0.3907 0.01394 0.00752 -0.1187 0.6865 0.0107
-9.000 -0.3731 0.01371 0.00720 -0.1170 0.6698 0.0111
-8.750 -0.3542 0.01348 0.00690 -0.1155 0.6560 0.0114
-8.500 -0.3345 0.01328 0.00663 -0.1142 0.6426 0.0120
-8.250 -0.3137 0.01308 0.00636 -0.1130 0.6293 0.0123
-8.000 -0.2928 0.01286 0.00608 -0.1118 0.6167 0.0128
-7.750 -0.2718 0.01264 0.00581 -0.1106 0.6051 0.0135
-7.500 -0.2493 0.01243 0.00556 -0.1097 0.5948 0.0141
-7.250 -0.2268 0.01226 0.00532 -0.1088 0.5846 0.0149
-7.000 -0.2038 0.01206 0.00509 -0.1080 0.5742 0.0160
-6.750 -0.1807 0.01189 0.00487 -0.1072 0.5636 0.0171
-6.500 -0.1571 0.01173 0.00466 -0.1064 0.5533 0.0186
-6.250 -0.1332 0.01155 0.00446 -0.1058 0.5448 0.0212
-6.000 -0.1093 0.01137 0.00426 -0.1051 0.5353 0.0247
-5.750 -0.0851 0.01120 0.00407 -0.1045 0.5268 0.0294
-5.500 -0.0607 0.01102 0.00390 -0.1039 0.5174 0.0358
-5.250 -0.0359 0.01088 0.00374 -0.1034 0.5093 0.0426
-5.000 -0.0106 0.01072 0.00359 -0.1030 0.5017 0.0502
-4.750 0.0144 0.01060 0.00346 -0.1025 0.4936 0.0588
-4.500 0.0403 0.01047 0.00334 -0.1022 0.4858 0.0665
-4.250 0.0658 0.01037 0.00323 -0.1018 0.4777 0.0751
-4.000 0.0919 0.01026 0.00313 -0.1015 0.4712 0.0842
-3.750 0.1182 0.01016 0.00303 -0.1012 0.4647 0.0934
-3.250 0.1703 0.00991 0.00285 -0.1007 0.4520 0.1268
-3.000 0.1964 0.00976 0.00276 -0.1005 0.4453 0.1516
-2.750 0.2224 0.00964 0.00269 -0.1002 0.4385 0.1780
-2.500 0.2491 0.00947 0.00261 -0.1001 0.4334 0.2109
-2.250 0.2756 0.00929 0.00254 -0.1001 0.4279 0.2512
-2.000 0.3018 0.00911 0.00247 -0.1000 0.4223 0.2998
-1.750 0.3286 0.00888 0.00241 -0.1000 0.4176 0.3575
-1.500 0.3555 0.00865 0.00234 -0.1000 0.4122 0.4212
-1.250 0.3821 0.00844 0.00231 -0.1000 0.4062 0.4928
-1.000 0.4092 0.00834 0.00233 -0.1000 0.4015 0.5409
-0.750 0.4366 0.00832 0.00235 -0.0999 0.3974 0.5688
-0.500 0.4636 0.00833 0.00239 -0.0998 0.3928 0.5909
-0.250 0.4902 0.00838 0.00243 -0.0995 0.3882 0.6072
0.000 0.5169 0.00843 0.00249 -0.0993 0.3842 0.6233
0.250 0.5436 0.00848 0.00255 -0.0990 0.3802 0.6402
0.500 0.5699 0.00855 0.00263 -0.0987 0.3755 0.6554
0.750 0.5957 0.00864 0.00271 -0.0982 0.3709 0.6662
1.000 0.6217 0.00874 0.00278 -0.0979 0.3673 0.6747
1.250 0.6483 0.00881 0.00284 -0.0976 0.3644 0.6795
1.500 0.6744 0.00889 0.00290 -0.0973 0.3607 0.6829
1.750 0.7001 0.00898 0.00297 -0.0969 0.3566 0.6859
2.000 0.7254 0.00910 0.00306 -0.0964 0.3525 0.6890
2.250 0.7512 0.00919 0.00313 -0.0960 0.3492 0.6921
2.500 0.7772 0.00929 0.00321 -0.0957 0.3465 0.6949
2.750 0.8029 0.00939 0.00329 -0.0953 0.3433 0.6972
3.000 0.8280 0.00951 0.00339 -0.0948 0.3400 0.6999
3.250 0.8526 0.00964 0.00351 -0.0943 0.3361 0.7026
3.500 0.8778 0.00976 0.00362 -0.0938 0.3331 0.7053
3.750 0.9033 0.00986 0.00373 -0.0934 0.3303 0.7078
4.000 0.9285 0.00998 0.00384 -0.0930 0.3274 0.7105
4.250 0.9533 0.01011 0.00396 -0.0925 0.3244 0.7131
4.500 0.9777 0.01027 0.00409 -0.0920 0.3213 0.7154
4.750 1.0014 0.01043 0.00423 -0.0913 0.3180 0.7173
5.000 1.0260 0.01054 0.00436 -0.0908 0.3157 0.7197
5.250 1.0503 0.01066 0.00450 -0.0903 0.3131 0.7221
5.500 1.0742 0.01080 0.00465 -0.0897 0.3100 0.7247
5.750 1.0978 0.01096 0.00481 -0.0890 0.3073 0.7273
6.000 1.1208 0.01114 0.00498 -0.0883 0.3044 0.7298
6.250 1.1435 0.01133 0.00516 -0.0875 0.3013 0.7320
6.500 1.1676 0.01147 0.00532 -0.0870 0.2994 0.7341
6.750 1.1910 0.01163 0.00549 -0.0864 0.2973 0.7360
7.000 1.2136 0.01180 0.00567 -0.0856 0.2942 0.7386
7.250 1.2356 0.01198 0.00588 -0.0847 0.2916 0.7412
7.500 1.2570 0.01220 0.00610 -0.0838 0.2888 0.7437
7.750 1.2782 0.01242 0.00633 -0.0828 0.2862 0.7461
8.000 1.3004 0.01261 0.00655 -0.0821 0.2843 0.7486
8.250 1.3224 0.01280 0.00677 -0.0813 0.2820 0.7513
8.500 1.3437 0.01302 0.00701 -0.0804 0.2794 0.7537
8.750 1.3644 0.01326 0.00726 -0.0794 0.2770 0.7560
9.000 1.3844 0.01351 0.00754 -0.0784 0.2744 0.7586
9.250 1.4034 0.01381 0.00786 -0.0772 0.2718 0.7613
9.500 1.4221 0.01410 0.00818 -0.0760 0.2693 0.7644
9.750 1.4427 0.01435 0.00847 -0.0751 0.2676 0.7676
10.000 1.4626 0.01462 0.00878 -0.0741 0.2652 0.7706
10.250 1.4814 0.01493 0.00912 -0.0729 0.2628 0.7732
10.500 1.4991 0.01528 0.00950 -0.0717 0.2599 0.7761
10.750 1.5147 0.01571 0.00996 -0.0702 0.2565 0.7797
11.000 1.5313 0.01612 0.01040 -0.0688 0.2535 0.7835
11.250 1.5494 0.01648 0.01081 -0.0677 0.2507 0.7875
11.500 1.5655 0.01693 0.01129 -0.0664 0.2470 0.7913
11.750 1.5797 0.01746 0.01185 -0.0649 0.2431 0.7951
12.000 1.5920 0.01809 0.01250 -0.0631 0.2393 0.7996
12.500 1.6224 0.01916 0.01367 -0.0606 0.2325 0.8102
12.750 1.6310 0.02002 0.01454 -0.0586 0.2264 0.8163
13.000 1.6432 0.02073 0.01531 -0.0572 0.2227 0.8230
13.500 1.6582 0.02276 0.01739 -0.0535 0.2104 0.8391
13.750 1.6672 0.02374 0.01843 -0.0520 0.2044 0.8497
14.000 1.6673 0.02525 0.01997 -0.0497 0.1964 0.8664
14.250 1.6748 0.02625 0.02110 -0.0481 0.1930 0.8947
14.750 1.6819 0.02968 0.02465 -0.0459 0.1773 1.0000
15.000 1.6791 0.03190 0.02687 -0.0444 0.1699 1.0000
15.250 1.6797 0.03397 0.02897 -0.0433 0.1633 1.0000
15.500 1.6741 0.03665 0.03165 -0.0421 0.1564 1.0000
15.750 1.6709 0.03924 0.03426 -0.0412 0.1494 1.0000
16.000 1.6610 0.04254 0.03758 -0.0403 0.1421 1.0000
16.250 1.6539 0.04572 0.04080 -0.0398 0.1357 1.0000
16.500 1.6389 0.04983 0.04493 -0.0393 0.1279 1.0000
16.750 1.6279 0.05367 0.04880 -0.0391 0.1222 1.0000
17.000 1.6147 0.05789 0.05307 -0.0392 0.1163 1.0000
17.250 1.5996 0.06248 0.05770 -0.0394 0.1104 1.0000
17.500 1.5839 0.06727 0.06255 -0.0399 0.1049 1.0000
17.750 1.5703 0.07197 0.06730 -0.0407 0.1004 1.0000
18.000 1.5511 0.07749 0.07287 -0.0416 0.0943 1.0000
18.250 1.5351 0.08275 0.07817 -0.0428 0.0896 1.0000
18.500 1.5233 0.08757 0.08305 -0.0440 0.0862 1.0000
18.750 1.5163 0.09180 0.08736 -0.0452 0.0835 1.0000
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Polar data table (+)
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