EPPLER 1233 AIRFOIL (e1233-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: EPPLER 1233 AIRFOIL (e1233-il) Reynolds number: 500,000 Max Cl/Cd: 80.99 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e1233-il-500000.txt Download as CSV file: xf-e1233-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.6142 0.07672 0.07354 -0.0724 1.0000 0.0151
-14.250 -0.6415 0.06919 0.06587 -0.0766 1.0000 0.0150
-14.000 -0.6595 0.06389 0.06046 -0.0790 1.0000 0.0149
-13.750 -0.6859 0.05818 0.05457 -0.0811 1.0000 0.0149
-13.500 -0.7061 0.05390 0.05016 -0.0818 1.0000 0.0148
-13.250 -0.7264 0.05014 0.04626 -0.0815 1.0000 0.0148
-13.000 -0.7476 0.04698 0.04292 -0.0804 1.0000 0.0149
-12.750 -0.7626 0.04461 0.04045 -0.0784 1.0000 0.0149
-12.500 -0.7559 0.04129 0.03691 -0.0818 0.9968 0.0150
-12.250 -0.7445 0.03825 0.03359 -0.0855 0.9933 0.0151
-12.000 -0.7302 0.03628 0.03142 -0.0877 0.9880 0.0152
-11.750 -0.7156 0.03309 0.02802 -0.0900 0.9845 0.0155
-11.500 -0.6936 0.03120 0.02605 -0.0917 0.9811 0.0158
-11.250 -0.6729 0.02967 0.02443 -0.0928 0.9755 0.0159
-11.000 -0.6449 0.02821 0.02289 -0.0950 0.9725 0.0162
-10.750 -0.6291 0.02691 0.02151 -0.0945 0.9644 0.0164
-10.500 -0.6013 0.02554 0.02004 -0.0961 0.9607 0.0166
-10.250 -0.5850 0.02441 0.01883 -0.0951 0.9510 0.0171
-10.000 -0.5618 0.02329 0.01761 -0.0952 0.9436 0.0176
-9.750 -0.5364 0.02216 0.01639 -0.0955 0.9364 0.0178
-9.500 -0.5155 0.02125 0.01537 -0.0947 0.9261 0.0181
-9.250 -0.4868 0.01984 0.01393 -0.0957 0.9199 0.0185
-9.000 -0.4600 0.01880 0.01289 -0.0963 0.9082 0.0192
-8.750 -0.4215 0.01785 0.01189 -0.0990 0.8990 0.0199
-8.500 -0.3719 0.01692 0.01087 -0.1038 0.8890 0.0212
-8.250 -0.3187 0.01580 0.00970 -0.1099 0.8746 0.0225
-8.000 -0.2610 0.01506 0.00884 -0.1166 0.8553 0.0244
-7.750 -0.2255 0.01449 0.00815 -0.1187 0.8297 0.0265
-7.500 -0.2004 0.01418 0.00769 -0.1185 0.8043 0.0284
-7.250 -0.1813 0.01381 0.00721 -0.1172 0.7814 0.0308
-7.000 -0.1628 0.01351 0.00680 -0.1156 0.7602 0.0341
-6.750 -0.1442 0.01323 0.00643 -0.1139 0.7415 0.0383
-6.500 -0.1257 0.01290 0.00609 -0.1123 0.7244 0.0456
-6.250 -0.1060 0.01264 0.00581 -0.1109 0.7083 0.0563
-6.000 -0.0853 0.01243 0.00558 -0.1097 0.6932 0.0676
-5.750 -0.0638 0.01227 0.00537 -0.1085 0.6786 0.0776
-5.500 -0.0420 0.01212 0.00518 -0.1075 0.6646 0.0876
-5.250 -0.0196 0.01193 0.00498 -0.1065 0.6516 0.0979
-5.000 0.0031 0.01176 0.00479 -0.1056 0.6394 0.1091
-4.750 0.0257 0.01160 0.00460 -0.1047 0.6270 0.1220
-4.500 0.0490 0.01140 0.00442 -0.1040 0.6153 0.1387
-4.250 0.0720 0.01121 0.00424 -0.1032 0.6042 0.1619
-4.000 0.0949 0.01087 0.00405 -0.1025 0.5936 0.2025
-3.750 0.1174 0.01045 0.00384 -0.1019 0.5837 0.2699
-3.500 0.1397 0.00988 0.00360 -0.1014 0.5734 0.3682
-3.250 0.1626 0.00931 0.00343 -0.1010 0.5640 0.4890
-3.000 0.1874 0.00914 0.00344 -0.1004 0.5542 0.5630
-2.750 0.2134 0.00916 0.00349 -0.1000 0.5456 0.5998
-2.500 0.2398 0.00923 0.00352 -0.0996 0.5367 0.6233
-2.250 0.2662 0.00934 0.00357 -0.0991 0.5285 0.6404
-2.000 0.2925 0.00944 0.00365 -0.0986 0.5199 0.6535
-1.750 0.3185 0.00960 0.00371 -0.0981 0.5118 0.6643
-1.500 0.3454 0.00970 0.00378 -0.0978 0.5042 0.6743
-1.250 0.3715 0.00985 0.00385 -0.0973 0.4968 0.6826
-1.000 0.3979 0.00999 0.00395 -0.0969 0.4902 0.6904
-0.750 0.4247 0.01012 0.00400 -0.0966 0.4830 0.6982
-0.500 0.4494 0.01030 0.00414 -0.0958 0.4762 0.7048
-0.250 0.4757 0.01046 0.00428 -0.0953 0.4699 0.7142
0.000 0.5005 0.01063 0.00444 -0.0945 0.4635 0.7225
0.250 0.5250 0.01087 0.00461 -0.0937 0.4575 0.7299
0.500 0.5521 0.01099 0.00469 -0.0935 0.4522 0.7360
0.750 0.5772 0.01105 0.00475 -0.0929 0.4466 0.7400
1.000 0.6018 0.01120 0.00483 -0.0922 0.4410 0.7434
1.250 0.6275 0.01130 0.00491 -0.0918 0.4360 0.7470
1.500 0.6531 0.01137 0.00496 -0.0914 0.4307 0.7506
1.750 0.6785 0.01149 0.00500 -0.0910 0.4256 0.7540
2.000 0.7036 0.01164 0.00508 -0.0906 0.4207 0.7570
2.250 0.7283 0.01167 0.00515 -0.0900 0.4167 0.7598
2.500 0.7529 0.01176 0.00523 -0.0894 0.4122 0.7627
2.750 0.7770 0.01189 0.00532 -0.0887 0.4077 0.7659
3.000 0.8017 0.01209 0.00545 -0.0883 0.4028 0.7694
3.250 0.8269 0.01216 0.00553 -0.0879 0.3992 0.7726
3.500 0.8516 0.01225 0.00561 -0.0874 0.3952 0.7753
3.750 0.8751 0.01237 0.00572 -0.0866 0.3913 0.7781
4.000 0.8985 0.01257 0.00588 -0.0859 0.3872 0.7811
4.250 0.9229 0.01272 0.00604 -0.0854 0.3837 0.7843
4.500 0.9471 0.01283 0.00617 -0.0848 0.3799 0.7875
4.750 0.9713 0.01298 0.00631 -0.0843 0.3762 0.7905
5.000 0.9951 0.01316 0.00646 -0.0838 0.3726 0.7933
5.250 1.0183 0.01340 0.00666 -0.0831 0.3688 0.7963
5.500 1.0414 0.01354 0.00685 -0.0824 0.3660 0.7993
5.750 1.0644 0.01368 0.00703 -0.0816 0.3628 0.8025
6.000 1.0873 0.01384 0.00720 -0.0809 0.3594 0.8057
6.250 1.1099 0.01405 0.00739 -0.0802 0.3560 0.8088
6.500 1.1328 0.01432 0.00762 -0.0796 0.3525 0.8119
6.750 1.1554 0.01452 0.00786 -0.0789 0.3497 0.8151
7.000 1.1772 0.01468 0.00808 -0.0780 0.3471 0.8184
7.250 1.1988 0.01487 0.00831 -0.0771 0.3442 0.8218
7.500 1.2201 0.01508 0.00853 -0.0762 0.3410 0.8254
8.250 1.2837 0.01588 0.00938 -0.0736 0.3323 0.8362
8.500 1.3039 0.01610 0.00967 -0.0726 0.3298 0.8402
8.750 1.3241 0.01635 0.00996 -0.0717 0.3271 0.8442
9.000 1.3434 0.01660 0.01024 -0.0705 0.3242 0.8483
9.250 1.3620 0.01689 0.01057 -0.0693 0.3214 0.8529
9.500 1.3828 0.01731 0.01096 -0.0686 0.3181 0.8579
9.750 1.4015 0.01761 0.01133 -0.0675 0.3160 0.8631
10.000 1.4188 0.01787 0.01170 -0.0661 0.3137 0.8684
10.250 1.4357 0.01818 0.01209 -0.0647 0.3111 0.8749
10.500 1.4524 0.01851 0.01248 -0.0633 0.3083 0.8822
10.750 1.4678 0.01887 0.01289 -0.0617 0.3057 0.8912
11.000 1.4844 0.01930 0.01334 -0.0604 0.3028 0.9016
11.250 1.4991 0.01967 0.01381 -0.0587 0.3003 0.9184
11.500 1.5169 0.01997 0.01428 -0.0580 0.2977 1.0000
11.750 1.5341 0.02049 0.01486 -0.0572 0.2947 1.0000
12.000 1.5499 0.02105 0.01545 -0.0563 0.2917 1.0000
12.250 1.5651 0.02168 0.01607 -0.0553 0.2885 1.0000
12.500 1.5820 0.02236 0.01672 -0.0545 0.2850 1.0000
12.750 1.5939 0.02306 0.01753 -0.0532 0.2825 1.0000
13.000 1.6065 0.02379 0.01834 -0.0520 0.2795 1.0000
13.250 1.6186 0.02457 0.01918 -0.0508 0.2765 1.0000
13.500 1.6300 0.02544 0.02007 -0.0496 0.2734 1.0000
13.750 1.6433 0.02633 0.02091 -0.0487 0.2697 1.0000
14.000 1.6523 0.02735 0.02206 -0.0474 0.2673 1.0000
14.250 1.6604 0.02847 0.02328 -0.0462 0.2637 1.0000
14.500 1.6670 0.02973 0.02458 -0.0450 0.2595 1.0000
14.750 1.6727 0.03113 0.02596 -0.0438 0.2552 1.0000
15.000 1.6787 0.03259 0.02754 -0.0428 0.2513 1.0000
15.250 1.6834 0.03421 0.02924 -0.0419 0.2464 1.0000
15.500 1.6862 0.03604 0.03108 -0.0410 0.2421 1.0000
15.750 1.6892 0.03792 0.03301 -0.0402 0.2380 1.0000
16.000 1.6941 0.03976 0.03496 -0.0397 0.2338 1.0000
16.250 1.6958 0.04190 0.03716 -0.0392 0.2294 1.0000
16.500 1.6942 0.04439 0.03966 -0.0386 0.2253 1.0000
16.750 1.6971 0.04660 0.04198 -0.0383 0.2212 1.0000
17.000 1.6961 0.04922 0.04467 -0.0381 0.2163 1.0000
17.250 1.6907 0.05233 0.04780 -0.0380 0.2117 1.0000
17.500 1.6891 0.05518 0.05075 -0.0380 0.2071 1.0000
17.750 1.6843 0.05845 0.05409 -0.0382 0.2019 1.0000
18.000 1.6731 0.06247 0.05812 -0.0384 0.1966 1.0000
18.250 1.6680 0.06597 0.06173 -0.0389 0.1912 1.0000
18.500 1.6563 0.07029 0.06610 -0.0395 0.1855 1.0000
18.750 1.6461 0.07452 0.07039 -0.0403 0.1803 1.0000
19.000 1.6332 0.07922 0.07516 -0.0413 0.1738 1.0000
19.250 1.6174 0.08434 0.08031 -0.0425 0.1680 1.0000
|
Polar data table (+)
Polar graphs
<< Back to EPPLER 1233 AIRFOIL (e1233-il)