E230 (9.96%) (e230-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: E230 (9.96%) (e230-il) Reynolds number: 1,000,000 Max Cl/Cd: 58.05 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e230-il-1000000-n5.txt Download as CSV file: xf-e230-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E230 (9.96%)
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
------ -------- --------- --------- -------- -------- --------
-16.000 -0.9705 0.14245 0.14073 0.0566 1.0000 0.0035
-15.750 -1.0100 0.12641 0.12455 0.0476 1.0000 0.0034
-15.500 -1.0397 0.11375 0.11177 0.0403 1.0000 0.0034
-15.250 -1.0719 0.10131 0.09920 0.0329 1.0000 0.0034
-15.000 -1.1011 0.09000 0.08774 0.0260 1.0000 0.0033
-14.750 -1.1275 0.07973 0.07734 0.0196 1.0000 0.0033
-14.500 -1.1452 0.07154 0.06900 0.0142 1.0000 0.0033
-14.250 -1.1652 0.06341 0.06070 0.0089 1.0000 0.0033
-14.000 -1.1841 0.05627 0.05339 0.0045 1.0000 0.0033
-13.750 -1.1992 0.05050 0.04745 0.0015 1.0000 0.0033
-13.500 -1.2086 0.04621 0.04301 -0.0001 1.0000 0.0033
-13.250 -1.2192 0.04233 0.03898 -0.0007 1.0000 0.0034
-13.000 -1.2288 0.03905 0.03553 -0.0002 1.0000 0.0034
-12.750 -1.2358 0.03639 0.03272 0.0012 1.0000 0.0034
-12.500 -1.2388 0.03434 0.03052 0.0031 1.0000 0.0034
-12.250 -1.2395 0.03259 0.02862 0.0055 1.0000 0.0035
-12.000 -1.2400 0.03094 0.02683 0.0084 1.0000 0.0035
-11.750 -1.2344 0.02980 0.02558 0.0109 1.0000 0.0035
-11.500 -1.2310 0.02842 0.02407 0.0140 1.0000 0.0035
-11.250 -1.2213 0.02718 0.02270 0.0161 1.0000 0.0036
-11.000 -1.2092 0.02595 0.02134 0.0179 1.0000 0.0036
-10.750 -1.1933 0.02501 0.02029 0.0194 1.0000 0.0036
-10.500 -1.1781 0.02388 0.01904 0.0209 1.0000 0.0037
-10.250 -1.1637 0.02255 0.01758 0.0225 1.0000 0.0037
-10.000 -1.1503 0.02102 0.01589 0.0244 1.0000 0.0038
-9.750 -1.1336 0.01985 0.01460 0.0258 1.0000 0.0039
-9.500 -1.1145 0.01890 0.01357 0.0269 1.0000 0.0040
-9.250 -1.0944 0.01805 0.01264 0.0280 1.0000 0.0040
-9.000 -1.0729 0.01734 0.01185 0.0288 1.0000 0.0041
-8.750 -1.0510 0.01664 0.01109 0.0296 1.0000 0.0042
-8.500 -1.0284 0.01601 0.01039 0.0304 1.0000 0.0043
-8.250 -1.0055 0.01538 0.00971 0.0310 1.0000 0.0044
-8.000 -0.9819 0.01483 0.00911 0.0316 1.0000 0.0046
-7.750 -0.9576 0.01435 0.00859 0.0321 1.0000 0.0048
-7.500 -0.9334 0.01383 0.00802 0.0327 1.0000 0.0050
-7.250 -0.9089 0.01333 0.00746 0.0332 1.0000 0.0052
-7.000 -0.8813 0.01285 0.00693 0.0330 0.9752 0.0054
-6.750 -0.8554 0.01246 0.00647 0.0333 0.9518 0.0055
-6.500 -0.8330 0.01215 0.00609 0.0345 0.9346 0.0056
-6.250 -0.8098 0.01186 0.00573 0.0355 0.9203 0.0058
-6.000 -0.7869 0.01142 0.00519 0.0365 0.9070 0.0061
-5.750 -0.7629 0.01108 0.00479 0.0373 0.8943 0.0065
-5.500 -0.7382 0.01080 0.00444 0.0380 0.8819 0.0068
-5.250 -0.7131 0.01054 0.00413 0.0386 0.8696 0.0074
-5.000 -0.6875 0.01032 0.00383 0.0391 0.8572 0.0078
-4.750 -0.6616 0.01012 0.00357 0.0395 0.8444 0.0084
-4.500 -0.6357 0.00988 0.00329 0.0400 0.8314 0.0107
-4.250 -0.6110 0.00946 0.00295 0.0406 0.8182 0.0312
-4.000 -0.5859 0.00909 0.00266 0.0411 0.8048 0.0577
-3.750 -0.5605 0.00877 0.00242 0.0415 0.7912 0.0832
-3.500 -0.5348 0.00848 0.00221 0.0419 0.7774 0.1114
-3.250 -0.5093 0.00816 0.00201 0.0423 0.7635 0.1482
-3.000 -0.4839 0.00783 0.00181 0.0427 0.7497 0.1905
-2.750 -0.4585 0.00751 0.00164 0.0431 0.7352 0.2366
-2.500 -0.4327 0.00725 0.00150 0.0434 0.7202 0.2780
-2.250 -0.4065 0.00703 0.00137 0.0437 0.7046 0.3148
-2.000 -0.3799 0.00687 0.00127 0.0440 0.6882 0.3446
-1.750 -0.3531 0.00673 0.00118 0.0442 0.6717 0.3720
-1.500 -0.3264 0.00659 0.00109 0.0444 0.6546 0.4025
-1.250 -0.2995 0.00648 0.00101 0.0446 0.6372 0.4308
-1.000 -0.2725 0.00638 0.00095 0.0448 0.6199 0.4576
-0.750 -0.2456 0.00629 0.00090 0.0450 0.6023 0.4859
-0.500 -0.2187 0.00620 0.00085 0.0452 0.5843 0.5145
-0.250 -0.1920 0.00610 0.00081 0.0454 0.5659 0.5460
0.000 -0.1654 0.00602 0.00078 0.0457 0.5465 0.5777
0.250 -0.1387 0.00595 0.00076 0.0459 0.5272 0.6086
0.500 -0.1122 0.00589 0.00075 0.0462 0.5064 0.6399
0.750 -0.0859 0.00585 0.00075 0.0466 0.4850 0.6710
1.000 -0.0595 0.00580 0.00076 0.0469 0.4646 0.7006
1.250 -0.0333 0.00578 0.00077 0.0473 0.4426 0.7309
1.500 -0.0071 0.00576 0.00080 0.0477 0.4213 0.7601
1.750 0.0190 0.00576 0.00084 0.0481 0.3988 0.7883
2.000 0.0451 0.00578 0.00089 0.0485 0.3745 0.8165
2.250 0.0713 0.00582 0.00095 0.0489 0.3494 0.8443
2.500 0.0983 0.00585 0.00102 0.0492 0.3290 0.8710
2.750 0.1265 0.00595 0.00112 0.0491 0.3020 0.8959
3.000 0.1569 0.00622 0.00126 0.0485 0.2520 0.9173
3.250 0.1915 0.00655 0.00144 0.0469 0.2043 0.9330
3.500 0.2272 0.00685 0.00163 0.0450 0.1672 0.9437
3.750 0.2625 0.00719 0.00183 0.0433 0.1316 0.9506
4.000 0.2933 0.00752 0.00203 0.0425 0.0992 0.9580
4.500 0.3559 0.00824 0.00251 0.0406 0.0453 0.9670
4.750 0.3816 0.00863 0.00278 0.0410 0.0226 0.9729
5.000 0.4150 0.00901 0.00310 0.0396 0.0120 0.9749
5.250 0.4477 0.00925 0.00336 0.0385 0.0107 0.9774
5.500 0.4787 0.00951 0.00363 0.0377 0.0100 0.9804
5.750 0.5054 0.00978 0.00394 0.0379 0.0095 0.9842
6.000 0.5382 0.01009 0.00427 0.0367 0.0089 0.9854
6.250 0.5711 0.01044 0.00465 0.0354 0.0085 0.9866
6.500 0.6034 0.01090 0.00516 0.0342 0.0080 0.9881
6.750 0.6350 0.01132 0.00562 0.0331 0.0078 0.9897
7.000 0.6659 0.01170 0.00606 0.0323 0.0076 0.9914
7.250 0.6958 0.01213 0.00653 0.0316 0.0074 0.9931
7.500 0.7247 0.01260 0.00705 0.0310 0.0072 0.9946
7.750 0.7562 0.01305 0.00755 0.0299 0.0069 0.9955
8.000 0.7871 0.01356 0.00812 0.0288 0.0067 0.9966
8.250 0.8175 0.01410 0.00872 0.0279 0.0064 0.9978
8.500 0.8471 0.01471 0.00940 0.0270 0.0063 0.9989
8.750 0.8764 0.01533 0.01008 0.0261 0.0061 0.9998
9.000 0.8991 0.01597 0.01079 0.0266 0.0060 1.0000
9.250 0.9191 0.01664 0.01152 0.0277 0.0059 1.0000
9.500 0.9383 0.01735 0.01231 0.0288 0.0058 1.0000
9.750 0.9570 0.01810 0.01313 0.0300 0.0057 1.0000
10.000 0.9741 0.01900 0.01411 0.0313 0.0056 1.0000
10.250 0.9891 0.02009 0.01530 0.0328 0.0055 1.0000
10.500 1.0003 0.02156 0.01691 0.0347 0.0054 1.0000
10.750 1.0100 0.02308 0.01858 0.0368 0.0053 1.0000
11.000 1.0228 0.02411 0.01972 0.0385 0.0053 1.0000
11.250 1.0356 0.02503 0.02074 0.0401 0.0052 1.0000
11.500 1.0457 0.02610 0.02192 0.0420 0.0052 1.0000
11.750 1.0536 0.02722 0.02315 0.0440 0.0052 1.0000
12.000 1.0547 0.02860 0.02465 0.0468 0.0051 1.0000
12.250 1.0466 0.03009 0.02626 0.0503 0.0051 1.0000
12.500 1.0439 0.03184 0.02813 0.0520 0.0051 1.0000
12.750 1.0414 0.03401 0.03043 0.0526 0.0051 1.0000
13.000 1.0373 0.03678 0.03333 0.0523 0.0050 1.0000
13.250 1.0314 0.04020 0.03690 0.0511 0.0050 1.0000
13.500 1.0263 0.04395 0.04078 0.0491 0.0050 1.0000
13.750 1.0163 0.04884 0.04581 0.0462 0.0049 1.0000
14.000 0.9993 0.05517 0.05231 0.0421 0.0050 1.0000
14.250 0.9863 0.06133 0.05861 0.0380 0.0049 1.0000
14.500 0.9707 0.06811 0.06551 0.0337 0.0049 1.0000
14.750 0.9486 0.07628 0.07381 0.0287 0.0049 1.0000
15.000 0.9166 0.08643 0.08410 0.0229 0.0050 1.0000
15.250 0.8960 0.09487 0.09264 0.0182 0.0050 1.0000
15.500 0.8598 0.10688 0.10478 0.0119 0.0051 1.0000
15.750 0.8233 0.11960 0.11761 0.0056 0.0051 1.0000
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Polar data table (+)
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