EPPLER 552 AIRFOIL (e552-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 552 AIRFOIL (e552-il) Reynolds number: 1,000,000 Max Cl/Cd: 131.04 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e552-il-1000000.txt Download as CSV file: xf-e552-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 552 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.000 -0.6491 0.15613 0.15407 -0.0169 1.0000 0.0052
-18.750 -0.6715 0.14565 0.14348 -0.0221 1.0000 0.0052
-18.500 -0.6892 0.13687 0.13459 -0.0265 1.0000 0.0051
-18.250 -0.7164 0.12640 0.12397 -0.0319 1.0000 0.0051
-18.000 -0.7341 0.11859 0.11606 -0.0358 1.0000 0.0050
-17.750 -0.7614 0.10936 0.10669 -0.0404 1.0000 0.0049
-17.250 -0.7915 0.09570 0.09278 -0.0475 1.0000 0.0050
-17.000 -0.8026 0.08988 0.08684 -0.0505 1.0000 0.0050
-16.750 -0.8147 0.08429 0.08113 -0.0531 1.0000 0.0050
-16.500 -0.8203 0.07968 0.07641 -0.0554 1.0000 0.0051
-16.250 -0.8263 0.07527 0.07190 -0.0574 1.0000 0.0051
-16.000 -0.8310 0.07117 0.06771 -0.0592 1.0000 0.0051
-15.500 -0.8434 0.06322 0.05956 -0.0620 1.0000 0.0051
-15.250 -0.8597 0.05833 0.05449 -0.0633 1.0000 0.0052
-15.000 -0.8610 0.05530 0.05138 -0.0641 1.0000 0.0052
-14.750 -0.8664 0.05197 0.04794 -0.0647 1.0000 0.0053
-14.500 -0.8691 0.04906 0.04496 -0.0651 1.0000 0.0054
-14.250 -0.8668 0.04672 0.04255 -0.0653 1.0000 0.0053
-14.000 -0.8691 0.04409 0.03986 -0.0655 1.0000 0.0055
-13.750 -0.8693 0.04176 0.03746 -0.0654 1.0000 0.0055
-13.500 -0.8664 0.03975 0.03541 -0.0653 1.0000 0.0056
-13.250 -0.8651 0.03767 0.03326 -0.0649 1.0000 0.0056
-13.000 -0.8597 0.03597 0.03153 -0.0647 1.0000 0.0057
-12.750 -0.8561 0.03419 0.02970 -0.0642 1.0000 0.0058
-12.500 -0.8534 0.03243 0.02788 -0.0635 1.0000 0.0058
-12.250 -0.8493 0.03083 0.02625 -0.0627 1.0000 0.0059
-12.000 -0.8455 0.02931 0.02470 -0.0617 1.0000 0.0060
-11.750 -0.8225 0.02733 0.02265 -0.0650 0.9977 0.0061
-11.500 -0.8044 0.02564 0.02091 -0.0666 0.9842 0.0062
-11.250 -0.7602 0.02380 0.01899 -0.0733 0.9471 0.0064
-11.000 -0.6650 0.02164 0.01666 -0.0906 0.9208 0.0067
-10.750 -0.6143 0.02047 0.01513 -0.0980 0.8466 0.0069
-10.500 -0.6097 0.01947 0.01390 -0.0963 0.8035 0.0070
-10.250 -0.6039 0.01850 0.01277 -0.0946 0.7748 0.0070
-10.000 -0.6052 0.01731 0.01142 -0.0921 0.7517 0.0072
-9.750 -0.6085 0.01634 0.01032 -0.0888 0.7330 0.0074
-9.500 -0.5966 0.01569 0.00957 -0.0871 0.7172 0.0077
-9.250 -0.5806 0.01517 0.00896 -0.0859 0.7030 0.0081
-9.000 -0.5619 0.01471 0.00843 -0.0849 0.6902 0.0084
-8.750 -0.5418 0.01431 0.00795 -0.0841 0.6785 0.0090
-8.500 -0.5214 0.01388 0.00743 -0.0833 0.6674 0.0097
-8.250 -0.5005 0.01341 0.00691 -0.0826 0.6567 0.0112
-8.000 -0.4780 0.01300 0.00645 -0.0821 0.6470 0.0128
-7.500 -0.4320 0.01218 0.00558 -0.0812 0.6283 0.0226
-7.250 -0.4080 0.01183 0.00522 -0.0809 0.6195 0.0301
-7.000 -0.3833 0.01146 0.00487 -0.0807 0.6114 0.0399
-6.750 -0.3583 0.01113 0.00455 -0.0806 0.6039 0.0527
-6.500 -0.3331 0.01073 0.00422 -0.0805 0.5969 0.0727
-6.250 -0.3081 0.01034 0.00390 -0.0804 0.5899 0.0990
-6.000 -0.2830 0.00980 0.00354 -0.0804 0.5840 0.1417
-5.750 -0.2592 0.00904 0.00306 -0.0804 0.5779 0.2169
-5.500 -0.2370 0.00792 0.00249 -0.0805 0.5721 0.3547
-5.250 -0.2089 0.00773 0.00241 -0.0807 0.5668 0.3982
-5.000 -0.1802 0.00772 0.00237 -0.0809 0.5612 0.4162
-4.750 -0.1515 0.00772 0.00234 -0.0811 0.5560 0.4263
-4.500 -0.1221 0.00773 0.00229 -0.0813 0.5517 0.4332
-4.250 -0.0933 0.00773 0.00226 -0.0815 0.5472 0.4404
-4.000 -0.0642 0.00782 0.00226 -0.0817 0.5428 0.4475
-3.750 -0.0353 0.00780 0.00223 -0.0819 0.5391 0.4530
-3.500 -0.0060 0.00782 0.00223 -0.0822 0.5355 0.4583
-3.250 0.0232 0.00789 0.00226 -0.0824 0.5317 0.4665
-3.000 0.0519 0.00796 0.00230 -0.0825 0.5278 0.4728
-2.750 0.0808 0.00799 0.00228 -0.0828 0.5243 0.4750
-2.500 0.1102 0.00798 0.00224 -0.0831 0.5214 0.4770
-2.250 0.1395 0.00800 0.00221 -0.0833 0.5184 0.4786
-2.000 0.1686 0.00801 0.00218 -0.0836 0.5155 0.4800
-1.750 0.1972 0.00799 0.00214 -0.0838 0.5125 0.4825
-1.500 0.2258 0.00802 0.00214 -0.0839 0.5092 0.4847
-1.250 0.2551 0.00801 0.00214 -0.0842 0.5071 0.4868
-1.000 0.2843 0.00801 0.00213 -0.0845 0.5045 0.4887
-0.750 0.3134 0.00803 0.00213 -0.0848 0.5019 0.4907
-0.500 0.3424 0.00806 0.00214 -0.0850 0.4995 0.4926
-0.250 0.3712 0.00811 0.00215 -0.0852 0.4969 0.4944
0.000 0.3997 0.00820 0.00219 -0.0854 0.4939 0.4960
0.250 0.4288 0.00816 0.00219 -0.0857 0.4921 0.4990
0.500 0.4579 0.00816 0.00221 -0.0860 0.4900 0.5015
0.750 0.4869 0.00818 0.00224 -0.0862 0.4879 0.5038
1.000 0.5158 0.00821 0.00228 -0.0865 0.4857 0.5060
1.250 0.5446 0.00826 0.00231 -0.0867 0.4834 0.5083
1.500 0.5731 0.00834 0.00236 -0.0869 0.4809 0.5104
1.750 0.6015 0.00844 0.00244 -0.0871 0.4780 0.5125
2.000 0.6305 0.00843 0.00247 -0.0873 0.4764 0.5157
2.250 0.6593 0.00844 0.00253 -0.0876 0.4745 0.5185
2.500 0.6881 0.00847 0.00258 -0.0878 0.4723 0.5215
2.750 0.7168 0.00851 0.00264 -0.0881 0.4700 0.5244
3.000 0.7453 0.00858 0.00270 -0.0882 0.4675 0.5270
3.250 0.7733 0.00865 0.00277 -0.0884 0.4644 0.5301
3.500 0.8016 0.00872 0.00287 -0.0886 0.4616 0.5335
3.750 0.8302 0.00873 0.00293 -0.0888 0.4593 0.5369
4.000 0.8587 0.00877 0.00300 -0.0890 0.4567 0.5403
4.250 0.8871 0.00882 0.00307 -0.0892 0.4541 0.5435
4.500 0.9151 0.00887 0.00315 -0.0893 0.4511 0.5476
4.750 0.9424 0.00899 0.00327 -0.0893 0.4472 0.5519
5.000 0.9708 0.00901 0.00336 -0.0895 0.4445 0.5563
5.250 0.9990 0.00905 0.00344 -0.0897 0.4414 0.5603
5.500 1.0270 0.00908 0.00352 -0.0898 0.4381 0.5652
5.750 1.0543 0.00916 0.00363 -0.0898 0.4345 0.5702
6.000 1.0814 0.00927 0.00376 -0.0898 0.4306 0.5753
6.250 1.1095 0.00929 0.00385 -0.0900 0.4269 0.5806
6.500 1.1370 0.00934 0.00396 -0.0900 0.4224 0.5867
6.750 1.1633 0.00946 0.00408 -0.0899 0.4173 0.5927
7.000 1.1909 0.00950 0.00421 -0.0899 0.4126 0.5997
7.250 1.2180 0.00958 0.00434 -0.0899 0.4068 0.6072
7.500 1.2437 0.00971 0.00449 -0.0897 0.4006 0.6149
7.750 1.2707 0.00978 0.00463 -0.0897 0.3931 0.6234
8.000 1.2959 0.00992 0.00480 -0.0894 0.3849 0.6320
8.250 1.3209 0.01008 0.00498 -0.0891 0.3735 0.6414
8.500 1.3447 0.01030 0.00521 -0.0885 0.3590 0.6516
8.750 1.3661 0.01063 0.00550 -0.0876 0.3396 0.6622
9.000 1.3846 0.01110 0.00589 -0.0862 0.3144 0.6740
9.250 1.4010 0.01164 0.00636 -0.0846 0.2890 0.6873
9.500 1.4156 0.01224 0.00689 -0.0826 0.2655 0.7017
9.750 1.4284 0.01286 0.00745 -0.0803 0.2424 0.7176
10.000 1.4367 0.01347 0.00801 -0.0772 0.2227 0.7353
10.250 1.4433 0.01410 0.00862 -0.0738 0.2035 0.7556
10.500 1.4484 0.01479 0.00931 -0.0703 0.1857 0.7808
10.750 1.4529 0.01549 0.01004 -0.0669 0.1708 0.8150
11.000 1.4533 0.01612 0.01082 -0.0628 0.1581 0.8853
11.250 1.4540 0.01699 0.01176 -0.0593 0.1439 1.0000
11.500 1.4547 0.01818 0.01290 -0.0562 0.1313 1.0000
11.750 1.4552 0.01952 0.01421 -0.0536 0.1205 1.0000
12.000 1.4539 0.02112 0.01579 -0.0511 0.1101 1.0000
12.250 1.4496 0.02311 0.01773 -0.0488 0.0983 1.0000
12.500 1.4526 0.02478 0.01942 -0.0474 0.0920 1.0000
12.750 1.4518 0.02686 0.02151 -0.0459 0.0851 1.0000
13.000 1.4500 0.02914 0.02378 -0.0447 0.0777 1.0000
13.250 1.4492 0.03143 0.02609 -0.0437 0.0715 1.0000
13.500 1.4459 0.03402 0.02868 -0.0427 0.0655 1.0000
13.750 1.4451 0.03647 0.03115 -0.0420 0.0603 1.0000
14.000 1.4414 0.03924 0.03394 -0.0414 0.0552 1.0000
14.250 1.4395 0.04192 0.03663 -0.0409 0.0504 1.0000
14.500 1.4388 0.04457 0.03932 -0.0405 0.0474 1.0000
14.750 1.4362 0.04748 0.04225 -0.0403 0.0430 1.0000
15.000 1.4355 0.05028 0.04508 -0.0402 0.0398 1.0000
15.250 1.4325 0.05341 0.04823 -0.0402 0.0362 1.0000
15.500 1.4333 0.05621 0.05107 -0.0403 0.0336 1.0000
15.750 1.4318 0.05931 0.05419 -0.0406 0.0310 1.0000
16.000 1.4323 0.06224 0.05716 -0.0408 0.0287 1.0000
16.250 1.4312 0.06545 0.06040 -0.0413 0.0260 1.0000
16.500 1.4310 0.06858 0.06356 -0.0417 0.0244 1.0000
16.750 1.4323 0.07159 0.06663 -0.0423 0.0227 1.0000
17.000 1.4323 0.07483 0.06991 -0.0429 0.0211 1.0000
17.250 1.4311 0.07826 0.07337 -0.0437 0.0193 1.0000
17.500 1.4320 0.08148 0.07665 -0.0445 0.0181 1.0000
17.750 1.4327 0.08474 0.07996 -0.0453 0.0169 1.0000
18.000 1.4302 0.08855 0.08381 -0.0464 0.0155 1.0000
18.250 1.4318 0.09180 0.08712 -0.0474 0.0145 1.0000
18.500 1.4306 0.09550 0.09088 -0.0485 0.0134 1.0000
18.750 1.4288 0.09931 0.09472 -0.0498 0.0123 1.0000
19.000 1.4278 0.10310 0.09858 -0.0512 0.0114 1.0000
19.250 1.4275 0.10678 0.10231 -0.0525 0.0105 1.0000
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