E231 (e231-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: E231 (e231-il) Reynolds number: 500,000 Max Cl/Cd: 93.44 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e231-il-500000.txt Download as CSV file: xf-e231-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: E231
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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.3610 0.11461 0.11235 -0.0441 1.0000 0.0134
-11.250 -0.3594 0.11094 0.10872 -0.0455 1.0000 0.0138
-11.000 -0.3599 0.10720 0.10501 -0.0468 1.0000 0.0141
-10.250 -0.2561 0.07794 0.07573 -0.0682 0.9272 0.0158
-10.000 -0.2648 0.07200 0.06980 -0.0703 0.9228 0.0160
-9.750 -0.2718 0.06647 0.06426 -0.0726 0.9184 0.0161
-9.500 -0.2811 0.06027 0.05804 -0.0759 0.9143 0.0162
-8.000 -0.4009 0.04670 0.04344 -0.0795 0.8895 0.0159
-7.750 -0.4056 0.04291 0.03952 -0.0773 0.8852 0.0164
-7.500 -0.3985 0.04073 0.03726 -0.0758 0.8808 0.0167
-7.250 -0.3904 0.03864 0.03502 -0.0741 0.8768 0.0171
-7.000 -0.3809 0.03656 0.03276 -0.0722 0.8735 0.0176
-6.750 -0.3694 0.03440 0.03042 -0.0704 0.8699 0.0184
-6.500 -0.3563 0.03217 0.02793 -0.0684 0.8661 0.0197
-5.500 -0.2902 0.01878 0.01276 -0.0583 0.8535 0.0101
-5.250 -0.2662 0.01693 0.01067 -0.0574 0.8506 0.0094
-5.000 -0.2419 0.01539 0.00892 -0.0564 0.8478 0.0089
-4.750 -0.2183 0.01440 0.00780 -0.0555 0.8454 0.0088
-4.500 -0.1952 0.01364 0.00695 -0.0545 0.8427 0.0090
-4.250 -0.1724 0.01300 0.00625 -0.0536 0.8393 0.0095
-4.000 -0.1488 0.01248 0.00568 -0.0527 0.8361 0.0105
-3.750 -0.1256 0.01191 0.00503 -0.0517 0.8332 0.0118
-3.500 -0.1011 0.01149 0.00455 -0.0510 0.8307 0.0164
-3.250 -0.0807 0.01070 0.00406 -0.0497 0.8276 0.0801
-3.000 -0.0607 0.00999 0.00384 -0.0486 0.8238 0.1952
-2.750 -0.0454 0.00899 0.00361 -0.0468 0.8204 0.3942
-2.500 -0.0331 0.00804 0.00341 -0.0439 0.8173 0.5942
-2.250 -0.0190 0.00743 0.00349 -0.0407 0.8143 0.7730
-2.000 0.0045 0.00753 0.00372 -0.0393 0.8104 0.8432
-1.750 0.0295 0.00766 0.00383 -0.0383 0.8069 0.8683
-1.500 0.0552 0.00778 0.00389 -0.0374 0.8039 0.8838
-1.250 0.0820 0.00797 0.00401 -0.0367 0.8011 0.8966
-1.000 0.1084 0.00814 0.00416 -0.0360 0.7966 0.9063
-0.750 0.1338 0.00823 0.00421 -0.0351 0.7925 0.9155
-0.500 0.1662 0.00838 0.00429 -0.0356 0.7892 0.9218
-0.250 0.1924 0.00847 0.00432 -0.0350 0.7854 0.9294
0.000 0.2296 0.00859 0.00443 -0.0367 0.7807 0.9333
0.250 0.2645 0.00866 0.00444 -0.0380 0.7764 0.9381
0.500 0.2949 0.00870 0.00440 -0.0384 0.7727 0.9435
0.750 0.3386 0.00876 0.00447 -0.0417 0.7673 0.9455
1.000 0.3813 0.00876 0.00443 -0.0449 0.7624 0.9473
1.250 0.4193 0.00875 0.00438 -0.0471 0.7575 0.9497
1.500 0.4474 0.00873 0.00437 -0.0472 0.7510 0.9539
1.750 0.4754 0.00868 0.00429 -0.0473 0.7456 0.9574
2.000 0.5120 0.00863 0.00426 -0.0493 0.7383 0.9588
2.250 0.5473 0.00857 0.00416 -0.0510 0.7315 0.9603
2.500 0.5800 0.00853 0.00414 -0.0522 0.7226 0.9624
2.750 0.6103 0.00849 0.00409 -0.0529 0.7139 0.9648
3.000 0.6355 0.00848 0.00408 -0.0525 0.7043 0.9682
3.250 0.6615 0.00845 0.00407 -0.0522 0.6930 0.9709
3.500 0.6947 0.00842 0.00403 -0.0536 0.6798 0.9722
3.750 0.7265 0.00842 0.00402 -0.0547 0.6647 0.9737
4.000 0.7563 0.00846 0.00401 -0.0553 0.6461 0.9755
4.250 0.7839 0.00853 0.00405 -0.0555 0.6236 0.9776
4.500 0.8082 0.00867 0.00411 -0.0550 0.5966 0.9802
4.750 0.8276 0.00890 0.00424 -0.0535 0.5646 0.9831
5.000 0.8550 0.00915 0.00435 -0.0539 0.5257 0.9845
5.250 0.8814 0.00950 0.00454 -0.0542 0.4842 0.9863
5.500 0.9050 0.00995 0.00480 -0.0539 0.4385 0.9886
5.750 0.9266 0.01041 0.00510 -0.0533 0.3973 0.9910
6.000 0.9477 0.01088 0.00541 -0.0526 0.3617 0.9935
6.250 0.9728 0.01132 0.00572 -0.0528 0.3257 0.9953
6.500 0.9967 0.01182 0.00607 -0.0528 0.2898 0.9973
6.750 1.0206 0.01232 0.00645 -0.0528 0.2567 0.9992
7.000 1.0361 0.01278 0.00681 -0.0510 0.2313 1.0000
7.250 1.0434 0.01317 0.00714 -0.0475 0.2119 1.0000
7.500 1.0474 0.01357 0.00747 -0.0433 0.1942 1.0000
7.750 1.0474 0.01393 0.00778 -0.0383 0.1790 1.0000
8.000 1.0369 0.01412 0.00796 -0.0311 0.1685 1.0000
8.250 1.0266 0.01433 0.00816 -0.0241 0.1588 1.0000
8.500 1.0256 0.01470 0.00849 -0.0191 0.1463 1.0000
8.750 1.0319 0.01519 0.00893 -0.0157 0.1317 1.0000
9.000 1.0417 0.01575 0.00946 -0.0131 0.1179 1.0000
9.250 1.0528 0.01636 0.01003 -0.0109 0.1043 1.0000
9.500 1.0643 0.01703 0.01065 -0.0088 0.0910 1.0000
9.750 1.0763 0.01772 0.01130 -0.0068 0.0791 1.0000
10.000 1.0886 0.01843 0.01200 -0.0050 0.0695 1.0000
10.250 1.0999 0.01924 0.01278 -0.0032 0.0606 1.0000
10.500 1.1119 0.02004 0.01354 -0.0015 0.0508 1.0000
10.750 1.1250 0.02078 0.01435 0.0000 0.0453 1.0000
11.000 1.1357 0.02171 0.01526 0.0017 0.0378 1.0000
11.250 1.1467 0.02263 0.01616 0.0033 0.0313 1.0000
11.500 1.1584 0.02352 0.01707 0.0047 0.0256 1.0000
11.750 1.1666 0.02469 0.01825 0.0065 0.0210 1.0000
12.000 1.1737 0.02597 0.01953 0.0083 0.0156 1.0000
12.250 1.1819 0.02720 0.02082 0.0099 0.0125 1.0000
12.500 1.1833 0.02900 0.02267 0.0120 0.0102 1.0000
12.750 1.1888 0.03052 0.02426 0.0136 0.0079 1.0000
13.000 1.1868 0.03271 0.02657 0.0156 0.0061 1.0000
13.250 1.1903 0.03446 0.02843 0.0170 0.0065 1.0000
13.500 1.1925 0.03641 0.03048 0.0183 0.0054 1.0000
13.750 1.1906 0.03879 0.03298 0.0196 0.0051 1.0000
14.000 1.1832 0.04181 0.03612 0.0209 0.0049 1.0000
14.250 1.1745 0.04517 0.03964 0.0219 0.0045 1.0000
14.500 1.1776 0.04740 0.04197 0.0222 0.0045 1.0000
14.750 1.1710 0.05084 0.04556 0.0226 0.0043 1.0000
15.000 1.1728 0.05347 0.04831 0.0226 0.0041 1.0000
15.250 1.1733 0.05634 0.05129 0.0223 0.0039 1.0000
15.500 1.1759 0.05907 0.05411 0.0218 0.0036 1.0000
15.750 1.1520 0.06536 0.06063 0.0211 0.0040 1.0000
16.000 1.1543 0.06847 0.06382 0.0199 0.0036 1.0000
16.250 1.1563 0.07169 0.06711 0.0185 0.0034 1.0000
16.500 1.1434 0.07718 0.07276 0.0168 0.0034 1.0000
16.750 1.1340 0.08239 0.07810 0.0147 0.0033 1.0000
17.000 1.1239 0.08788 0.08371 0.0124 0.0032 1.0000
17.250 1.1144 0.09343 0.08939 0.0098 0.0032 1.0000
17.500 1.1041 0.09930 0.09538 0.0071 0.0032 1.0000
17.750 1.0901 0.10592 0.10215 0.0040 0.0032 1.0000
18.000 1.0825 0.11158 0.10793 0.0011 0.0032 1.0000
18.250 1.0700 0.11826 0.11473 -0.0023 0.0032 1.0000
18.500 1.0570 0.12514 0.12174 -0.0059 0.0031 1.0000
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Polar data table (+)
Polar graphs
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