E224 (10.17%) (e224-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: E224 (10.17%) (e224-il) Reynolds number: 500,000 Max Cl/Cd: 79.13 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e224-il-500000-n5.txt Download as CSV file: xf-e224-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E224 (10.17%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.7133 0.05439 0.05182 -0.0496 1.0000 0.0044
-11.000 -0.7484 0.04396 0.04113 -0.0591 1.0000 0.0042
-10.750 -0.7632 0.04013 0.03715 -0.0608 1.0000 0.0043
-10.500 -0.7855 0.03718 0.03402 -0.0583 1.0000 0.0043
-10.250 -0.7945 0.03439 0.03100 -0.0562 1.0000 0.0043
-10.000 -0.7981 0.03178 0.02814 -0.0539 1.0000 0.0043
-9.750 -0.7979 0.02930 0.02538 -0.0515 1.0000 0.0043
-9.500 -0.7924 0.02730 0.02314 -0.0493 1.0000 0.0045
-9.250 -0.7819 0.02589 0.02155 -0.0474 1.0000 0.0046
-9.000 -0.7730 0.02408 0.01949 -0.0452 1.0000 0.0047
-8.750 -0.7456 0.02280 0.01801 -0.0463 0.9980 0.0050
-8.500 -0.7167 0.02139 0.01637 -0.0476 0.9954 0.0052
-8.250 -0.6885 0.01993 0.01467 -0.0486 0.9928 0.0054
-8.000 -0.6603 0.01870 0.01325 -0.0495 0.9895 0.0055
-7.750 -0.6308 0.01750 0.01187 -0.0505 0.9864 0.0056
-7.500 -0.6015 0.01588 0.01006 -0.0517 0.9837 0.0059
-7.250 -0.5735 0.01491 0.00899 -0.0523 0.9798 0.0063
-7.000 -0.5442 0.01419 0.00817 -0.0530 0.9757 0.0067
-6.750 -0.5126 0.01356 0.00745 -0.0541 0.9727 0.0071
-6.500 -0.4798 0.01295 0.00675 -0.0554 0.9703 0.0077
-6.250 -0.4518 0.01244 0.00616 -0.0556 0.9646 0.0083
-6.000 -0.4212 0.01197 0.00562 -0.0563 0.9598 0.0089
-5.750 -0.3887 0.01143 0.00505 -0.0575 0.9560 0.0113
-5.500 -0.3604 0.01104 0.00459 -0.0577 0.9486 0.0138
-5.250 -0.3286 0.01061 0.00414 -0.0586 0.9432 0.0191
-5.000 -0.2994 0.01024 0.00377 -0.0590 0.9356 0.0268
-4.750 -0.2688 0.00986 0.00343 -0.0597 0.9287 0.0397
-4.500 -0.2408 0.00948 0.00313 -0.0598 0.9195 0.0623
-4.250 -0.2125 0.00908 0.00284 -0.0601 0.9106 0.0950
-4.000 -0.1846 0.00877 0.00260 -0.0602 0.9005 0.1231
-3.750 -0.1573 0.00850 0.00239 -0.0601 0.8894 0.1529
-3.500 -0.1304 0.00822 0.00220 -0.0600 0.8777 0.1903
-3.250 -0.1036 0.00794 0.00203 -0.0598 0.8657 0.2339
-3.000 -0.0767 0.00775 0.00188 -0.0596 0.8534 0.2676
-2.750 -0.0497 0.00758 0.00175 -0.0594 0.8408 0.2977
-2.500 -0.0229 0.00742 0.00164 -0.0592 0.8281 0.3326
-2.000 0.0307 0.00715 0.00146 -0.0587 0.8014 0.4015
-1.750 0.0575 0.00704 0.00139 -0.0585 0.7874 0.4356
-1.500 0.0844 0.00695 0.00133 -0.0582 0.7730 0.4678
-1.250 0.1111 0.00687 0.00128 -0.0579 0.7583 0.4994
-1.000 0.1379 0.00681 0.00125 -0.0576 0.7433 0.5301
-0.750 0.1646 0.00676 0.00123 -0.0574 0.7279 0.5601
-0.500 0.1913 0.00672 0.00122 -0.0570 0.7122 0.5902
-0.250 0.2180 0.00670 0.00122 -0.0567 0.6959 0.6194
0.000 0.2445 0.00668 0.00123 -0.0564 0.6789 0.6493
0.250 0.2708 0.00668 0.00125 -0.0560 0.6614 0.6786
0.500 0.2970 0.00670 0.00128 -0.0555 0.6436 0.7060
0.750 0.3233 0.00672 0.00132 -0.0551 0.6257 0.7321
1.000 0.3494 0.00676 0.00138 -0.0546 0.6070 0.7576
1.250 0.3752 0.00681 0.00144 -0.0541 0.5881 0.7827
1.500 0.4008 0.00687 0.00151 -0.0535 0.5688 0.8074
1.750 0.4260 0.00694 0.00158 -0.0528 0.5480 0.8314
2.000 0.4509 0.00704 0.00167 -0.0521 0.5272 0.8553
2.250 0.4753 0.00713 0.00176 -0.0512 0.5061 0.8784
2.500 0.4995 0.00725 0.00186 -0.0503 0.4849 0.9013
2.750 0.5240 0.00738 0.00196 -0.0494 0.4621 0.9242
3.000 0.5512 0.00753 0.00206 -0.0492 0.4381 0.9466
3.250 0.5827 0.00774 0.00218 -0.0501 0.4107 0.9679
3.500 0.6172 0.00797 0.00231 -0.0517 0.3834 0.9882
3.750 0.6462 0.00822 0.00247 -0.0521 0.3575 1.0000
4.000 0.6710 0.00848 0.00264 -0.0516 0.3317 1.0000
4.250 0.6954 0.00879 0.00282 -0.0511 0.3027 1.0000
4.500 0.7197 0.00913 0.00304 -0.0505 0.2709 1.0000
4.750 0.7444 0.00947 0.00328 -0.0501 0.2444 1.0000
5.000 0.7692 0.00978 0.00351 -0.0496 0.2212 1.0000
5.250 0.7933 0.01018 0.00378 -0.0491 0.1924 1.0000
5.500 0.8168 0.01064 0.00409 -0.0485 0.1602 1.0000
5.750 0.8403 0.01111 0.00442 -0.0479 0.1315 1.0000
6.250 0.8881 0.01196 0.00513 -0.0468 0.0920 1.0000
6.500 0.9120 0.01238 0.00549 -0.0462 0.0770 1.0000
6.750 0.9355 0.01283 0.00589 -0.0456 0.0627 1.0000
7.000 0.9587 0.01331 0.00631 -0.0450 0.0496 1.0000
7.250 0.9819 0.01378 0.00675 -0.0444 0.0397 1.0000
7.500 1.0048 0.01427 0.00725 -0.0437 0.0311 1.0000
7.750 1.0273 0.01480 0.00777 -0.0429 0.0246 1.0000
8.000 1.0494 0.01534 0.00831 -0.0421 0.0206 1.0000
8.250 1.0715 0.01589 0.00890 -0.0412 0.0179 1.0000
8.500 1.0936 0.01639 0.00946 -0.0405 0.0163 1.0000
8.750 1.1147 0.01698 0.01009 -0.0395 0.0144 1.0000
9.000 1.1341 0.01772 0.01090 -0.0384 0.0130 1.0000
9.250 1.1553 0.01824 0.01150 -0.0375 0.0122 1.0000
9.500 1.1755 0.01882 0.01215 -0.0365 0.0113 1.0000
9.750 1.1950 0.01944 0.01282 -0.0354 0.0103 1.0000
10.000 1.2120 0.02024 0.01368 -0.0340 0.0093 1.0000
10.250 1.2279 0.02109 0.01462 -0.0324 0.0087 1.0000
10.500 1.2453 0.02175 0.01540 -0.0310 0.0081 1.0000
10.750 1.2604 0.02249 0.01623 -0.0293 0.0074 1.0000
11.000 1.2732 0.02326 0.01708 -0.0273 0.0069 1.0000
11.250 1.2845 0.02410 0.01799 -0.0251 0.0064 1.0000
11.500 1.2926 0.02517 0.01914 -0.0227 0.0060 1.0000
11.750 1.2988 0.02636 0.02044 -0.0202 0.0057 1.0000
12.000 1.3091 0.02732 0.02151 -0.0183 0.0053 1.0000
12.250 1.3170 0.02847 0.02277 -0.0164 0.0049 1.0000
12.500 1.3231 0.02980 0.02421 -0.0146 0.0047 1.0000
12.750 1.3311 0.03104 0.02554 -0.0131 0.0044 1.0000
13.000 1.3350 0.03268 0.02729 -0.0116 0.0042 1.0000
13.250 1.3394 0.03437 0.02910 -0.0104 0.0040 1.0000
13.500 1.3402 0.03648 0.03133 -0.0093 0.0039 1.0000
13.750 1.3371 0.03914 0.03412 -0.0084 0.0037 1.0000
14.000 1.3289 0.04254 0.03767 -0.0080 0.0036 1.0000
14.250 1.3260 0.04561 0.04089 -0.0081 0.0035 1.0000
14.500 1.3197 0.04931 0.04474 -0.0087 0.0035 1.0000
14.750 1.3164 0.05287 0.04845 -0.0096 0.0034 1.0000
15.000 1.3052 0.05773 0.05348 -0.0113 0.0034 1.0000
15.250 1.2964 0.06255 0.05845 -0.0132 0.0033 1.0000
15.500 1.2861 0.06790 0.06396 -0.0157 0.0033 1.0000
15.750 1.2698 0.07455 0.07078 -0.0190 0.0033 1.0000
16.000 1.2546 0.08140 0.07778 -0.0226 0.0032 1.0000
16.250 1.2381 0.08877 0.08531 -0.0266 0.0033 1.0000
16.500 1.2211 0.09657 0.09326 -0.0310 0.0033 1.0000
16.750 1.2014 0.10518 0.10202 -0.0358 0.0033 1.0000
17.000 1.1815 0.11411 0.11110 -0.0409 0.0033 1.0000
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