EPPLER 550 AIRFOIL (e550-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 550 AIRFOIL (e550-il) Reynolds number: 500,000 Max Cl/Cd: 95.45 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e550-il-500000-n5.txt Download as CSV file: xf-e550-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 550 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.250 -0.7145 0.11377 0.11070 -0.0347 1.0000 0.0042
-17.000 -0.7544 0.10090 0.09755 -0.0414 1.0000 0.0040
-16.750 -0.7754 0.09256 0.08905 -0.0459 1.0000 0.0040
-16.500 -0.7943 0.08504 0.08136 -0.0499 1.0000 0.0040
-16.250 -0.8096 0.07860 0.07476 -0.0531 1.0000 0.0040
-16.000 -0.8218 0.07303 0.06906 -0.0558 1.0000 0.0041
-15.750 -0.8270 0.06877 0.06471 -0.0577 1.0000 0.0041
-15.500 -0.8383 0.06392 0.05967 -0.0594 1.0000 0.0040
-15.250 -0.8424 0.06028 0.05593 -0.0606 1.0000 0.0041
-15.000 -0.8450 0.05695 0.05250 -0.0616 1.0000 0.0042
-14.750 -0.8473 0.05381 0.04927 -0.0622 1.0000 0.0042
-14.500 -0.8492 0.05087 0.04620 -0.0626 1.0000 0.0042
-14.250 -0.8483 0.04834 0.04358 -0.0628 1.0000 0.0043
-14.000 -0.8465 0.04603 0.04118 -0.0628 1.0000 0.0044
-13.750 -0.8442 0.04388 0.03894 -0.0626 1.0000 0.0045
-13.500 -0.8412 0.04185 0.03682 -0.0623 1.0000 0.0045
-13.250 -0.8379 0.03992 0.03479 -0.0617 1.0000 0.0046
-13.000 -0.8341 0.03807 0.03286 -0.0611 1.0000 0.0046
-12.750 -0.8290 0.03640 0.03111 -0.0603 1.0000 0.0047
-12.500 -0.8220 0.03495 0.02959 -0.0595 1.0000 0.0047
-12.250 -0.8170 0.03337 0.02794 -0.0585 1.0000 0.0048
-12.000 -0.8098 0.03204 0.02654 -0.0574 1.0000 0.0049
-11.750 -0.7928 0.03044 0.02487 -0.0584 0.9969 0.0050
-11.500 -0.7635 0.02890 0.02321 -0.0613 0.9442 0.0053
-11.250 -0.6622 0.02640 0.02045 -0.0798 0.9004 0.0055
-11.000 -0.6208 0.02518 0.01884 -0.0853 0.8261 0.0055
-10.750 -0.6119 0.02427 0.01774 -0.0839 0.7897 0.0058
-10.500 -0.6016 0.02347 0.01679 -0.0825 0.7637 0.0061
-10.250 -0.5911 0.02266 0.01586 -0.0810 0.7433 0.0063
-10.000 -0.5796 0.02189 0.01497 -0.0797 0.7258 0.0064
-9.750 -0.5678 0.02115 0.01412 -0.0783 0.7100 0.0065
-9.500 -0.5554 0.02044 0.01330 -0.0769 0.6951 0.0069
-9.250 -0.5428 0.01975 0.01252 -0.0756 0.6820 0.0072
-9.000 -0.5302 0.01908 0.01176 -0.0742 0.6707 0.0074
-8.750 -0.5198 0.01834 0.01095 -0.0724 0.6590 0.0080
-8.500 -0.5082 0.01771 0.01025 -0.0708 0.6489 0.0086
-8.250 -0.4987 0.01713 0.00960 -0.0686 0.6401 0.0092
-8.000 -0.4891 0.01667 0.00906 -0.0663 0.6314 0.0098
-7.750 -0.4749 0.01617 0.00851 -0.0646 0.6236 0.0109
-7.500 -0.4576 0.01576 0.00803 -0.0633 0.6156 0.0119
-7.250 -0.4398 0.01534 0.00756 -0.0621 0.6084 0.0135
-7.000 -0.4202 0.01495 0.00712 -0.0611 0.6009 0.0156
-6.500 -0.3792 0.01420 0.00633 -0.0594 0.5873 0.0251
-6.250 -0.3579 0.01383 0.00596 -0.0587 0.5806 0.0334
-6.000 -0.3357 0.01347 0.00561 -0.0581 0.5752 0.0442
-5.750 -0.3131 0.01308 0.00527 -0.0576 0.5696 0.0592
-5.500 -0.2908 0.01267 0.00493 -0.0571 0.5642 0.0833
-5.250 -0.2686 0.01219 0.00457 -0.0566 0.5596 0.1184
-5.000 -0.2469 0.01154 0.00415 -0.0562 0.5549 0.1764
-4.750 -0.2272 0.01058 0.00360 -0.0558 0.5501 0.2780
-4.500 -0.2087 0.00935 0.00298 -0.0553 0.5456 0.4333
-4.250 -0.1821 0.00917 0.00297 -0.0553 0.5412 0.4973
-4.000 -0.1537 0.00917 0.00294 -0.0555 0.5367 0.5181
-3.750 -0.1252 0.00922 0.00294 -0.0556 0.5327 0.5333
-3.500 -0.0968 0.00930 0.00296 -0.0557 0.5290 0.5459
-3.250 -0.0681 0.00940 0.00302 -0.0558 0.5256 0.5582
-3.000 -0.0392 0.00954 0.00310 -0.0560 0.5221 0.5699
-2.750 -0.0106 0.00959 0.00313 -0.0561 0.5186 0.5746
-2.500 0.0180 0.00961 0.00307 -0.0563 0.5151 0.5763
-2.250 0.0465 0.00963 0.00301 -0.0565 0.5117 0.5778
-2.000 0.0756 0.00962 0.00296 -0.0568 0.5088 0.5793
-1.750 0.1045 0.00962 0.00291 -0.0571 0.5058 0.5810
-1.500 0.1334 0.00964 0.00287 -0.0574 0.5028 0.5825
-1.250 0.1622 0.00966 0.00283 -0.0576 0.5001 0.5838
-1.000 0.1909 0.00969 0.00279 -0.0579 0.4975 0.5850
-0.750 0.2194 0.00971 0.00277 -0.0581 0.4950 0.5862
-0.500 0.2483 0.00970 0.00277 -0.0584 0.4924 0.5875
-0.250 0.2770 0.00972 0.00278 -0.0586 0.4896 0.5890
0.000 0.3057 0.00974 0.00279 -0.0589 0.4869 0.5904
0.250 0.3343 0.00978 0.00281 -0.0591 0.4845 0.5918
0.500 0.3628 0.00983 0.00282 -0.0594 0.4823 0.5932
0.750 0.3912 0.00989 0.00285 -0.0596 0.4799 0.5946
1.000 0.4200 0.00993 0.00288 -0.0598 0.4777 0.5961
1.250 0.4487 0.00996 0.00292 -0.0601 0.4752 0.5976
1.500 0.4774 0.01000 0.00296 -0.0604 0.4730 0.5990
1.750 0.5060 0.01006 0.00300 -0.0607 0.4707 0.6005
2.000 0.5344 0.01011 0.00305 -0.0609 0.4682 0.6021
2.250 0.5624 0.01017 0.00311 -0.0611 0.4659 0.6036
2.500 0.5905 0.01025 0.00319 -0.0612 0.4637 0.6051
2.750 0.6189 0.01029 0.00328 -0.0615 0.4615 0.6066
3.000 0.6473 0.01034 0.00336 -0.0617 0.4591 0.6082
3.250 0.6756 0.01040 0.00345 -0.0619 0.4565 0.6098
3.500 0.7036 0.01047 0.00354 -0.0621 0.4538 0.6115
3.750 0.7315 0.01055 0.00362 -0.0623 0.4509 0.6133
4.000 0.7590 0.01065 0.00372 -0.0624 0.4481 0.6150
4.250 0.7871 0.01072 0.00382 -0.0626 0.4452 0.6167
4.500 0.8150 0.01078 0.00393 -0.0627 0.4417 0.6185
4.750 0.8425 0.01084 0.00405 -0.0628 0.4382 0.6205
5.000 0.8697 0.01093 0.00416 -0.0629 0.4347 0.6224
5.250 0.8966 0.01104 0.00429 -0.0629 0.4313 0.6245
5.500 0.9242 0.01110 0.00443 -0.0630 0.4275 0.6265
5.750 0.9513 0.01118 0.00456 -0.0630 0.4229 0.6287
6.000 0.9778 0.01129 0.00469 -0.0629 0.4184 0.6308
6.250 1.0044 0.01139 0.00484 -0.0629 0.4138 0.6330
6.750 1.0569 0.01160 0.00514 -0.0627 0.4025 0.6372
7.000 1.0829 0.01170 0.00532 -0.0626 0.3965 0.6395
7.250 1.1084 0.01183 0.00550 -0.0623 0.3891 0.6420
7.500 1.1333 0.01198 0.00569 -0.0620 0.3812 0.6448
7.750 1.1570 0.01217 0.00589 -0.0615 0.3708 0.6478
8.000 1.1807 0.01237 0.00612 -0.0610 0.3584 0.6508
8.250 1.2019 0.01265 0.00638 -0.0601 0.3424 0.6536
8.500 1.2209 0.01302 0.00673 -0.0589 0.3232 0.6566
8.750 1.2377 0.01349 0.00715 -0.0573 0.3014 0.6598
9.000 1.2508 0.01409 0.00766 -0.0552 0.2783 0.6631
9.250 1.2615 0.01472 0.00822 -0.0526 0.2560 0.6665
9.500 1.2681 0.01537 0.00881 -0.0494 0.2368 0.6698
9.750 1.2744 0.01608 0.00949 -0.0462 0.2195 0.6736
10.000 1.2798 0.01687 0.01024 -0.0431 0.2023 0.6777
10.250 1.2838 0.01774 0.01108 -0.0400 0.1864 0.6821
10.500 1.2856 0.01876 0.01208 -0.0368 0.1709 0.6864
10.750 1.2868 0.01989 0.01320 -0.0339 0.1581 0.6914
11.000 1.2865 0.02123 0.01455 -0.0313 0.1457 0.6972
11.250 1.2867 0.02271 0.01605 -0.0290 0.1350 0.7030
11.500 1.2876 0.02429 0.01767 -0.0272 0.1253 0.7093
11.750 1.2871 0.02612 0.01952 -0.0255 0.1165 0.7161
12.000 1.2851 0.02819 0.02163 -0.0241 0.1075 0.7229
12.250 1.2856 0.03019 0.02369 -0.0230 0.0998 0.7308
12.500 1.2832 0.03251 0.02604 -0.0219 0.0923 0.7389
12.750 1.2810 0.03491 0.02849 -0.0210 0.0845 0.7483
13.000 1.2796 0.03729 0.03094 -0.0203 0.0782 0.7587
13.250 1.2772 0.03983 0.03353 -0.0197 0.0722 0.7707
13.500 1.2756 0.04232 0.03611 -0.0192 0.0663 0.7854
14.000 1.2720 0.04740 0.04141 -0.0182 0.0566 0.8330
14.250 1.2739 0.05014 0.04440 -0.0189 0.0516 0.9319
14.500 1.2742 0.05274 0.04705 -0.0190 0.0478 1.0000
14.750 1.2732 0.05569 0.05002 -0.0192 0.0440 1.0000
15.000 1.2748 0.05841 0.05278 -0.0195 0.0405 1.0000
15.250 1.2745 0.06141 0.05581 -0.0199 0.0374 1.0000
15.500 1.2757 0.06429 0.05874 -0.0204 0.0346 1.0000
15.750 1.2760 0.06735 0.06182 -0.0209 0.0317 1.0000
16.000 1.2766 0.07041 0.06493 -0.0216 0.0293 1.0000
16.250 1.2776 0.07348 0.06804 -0.0223 0.0269 1.0000
16.500 1.2774 0.07679 0.07139 -0.0231 0.0249 1.0000
16.750 1.2793 0.07984 0.07450 -0.0239 0.0230 1.0000
17.000 1.2780 0.08338 0.07808 -0.0250 0.0211 1.0000
17.250 1.2792 0.08663 0.08139 -0.0260 0.0195 1.0000
17.500 1.2784 0.09023 0.08504 -0.0271 0.0178 1.0000
17.750 1.2787 0.09369 0.08856 -0.0283 0.0166 1.0000
18.000 1.2784 0.09731 0.09225 -0.0296 0.0154 1.0000
18.250 1.2767 0.10117 0.09616 -0.0311 0.0141 1.0000
18.500 1.2766 0.10485 0.09991 -0.0325 0.0132 1.0000
18.750 1.2757 0.10867 0.10381 -0.0341 0.0123 1.0000
19.000 1.2747 0.11258 0.10779 -0.0358 0.0116 1.0000
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