EPPLER 582 AIRFOIL (e582-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: EPPLER 582 AIRFOIL (e582-il) Reynolds number: 200,000 Max Cl/Cd: 74.99 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e582-il-200000-n5.txt Download as CSV file: xf-e582-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 582 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.1816 0.11201 0.10836 -0.0808 0.9526 0.0202
-11.000 -0.1697 0.10757 0.10391 -0.0847 0.9468 0.0205
-10.500 -0.1548 0.09425 0.09054 -0.0950 0.9344 0.0116
-10.250 -0.1407 0.08984 0.08610 -0.0996 0.9281 0.0113
-10.000 -0.1263 0.08556 0.08179 -0.1044 0.9204 0.0110
-9.750 -0.1174 0.07946 0.07567 -0.1106 0.9122 0.0110
-9.500 -0.1067 0.07431 0.07048 -0.1163 0.9028 0.0105
-9.250 -0.1040 0.06782 0.06396 -0.1228 0.8911 0.0105
-9.000 -0.1085 0.06037 0.05646 -0.1307 0.8780 0.0100
-8.750 -0.1237 0.05405 0.04999 -0.1350 0.8645 0.0100
-8.500 -0.1453 0.04913 0.04487 -0.1349 0.8526 0.0096
-8.250 -0.1653 0.04443 0.03991 -0.1329 0.8424 0.0094
-8.000 -0.1763 0.04009 0.03525 -0.1306 0.8343 0.0094
-7.750 -0.1764 0.03707 0.03193 -0.1287 0.8274 0.0096
-7.500 -0.1704 0.03451 0.02907 -0.1271 0.8219 0.0099
-7.250 -0.1644 0.03171 0.02590 -0.1251 0.8158 0.0101
-7.000 -0.1530 0.02911 0.02285 -0.1234 0.8109 0.0108
-6.750 -0.1390 0.02649 0.01967 -0.1217 0.8064 0.0114
-6.500 -0.1217 0.02457 0.01736 -0.1203 0.8014 0.0115
-6.250 -0.1008 0.02288 0.01531 -0.1193 0.7973 0.0116
-6.000 -0.0770 0.02144 0.01353 -0.1187 0.7939 0.0117
-5.750 -0.0549 0.02024 0.01220 -0.1179 0.7897 0.0119
-5.500 -0.0323 0.01929 0.01116 -0.1172 0.7854 0.0123
-5.250 -0.0084 0.01850 0.01026 -0.1167 0.7817 0.0127
-5.000 0.0163 0.01776 0.00940 -0.1163 0.7786 0.0132
-4.750 0.0388 0.01712 0.00869 -0.1155 0.7745 0.0140
-4.500 0.0616 0.01655 0.00802 -0.1147 0.7703 0.0151
-4.250 0.0854 0.01603 0.00745 -0.1142 0.7668 0.0165
-4.000 0.1109 0.01561 0.00696 -0.1140 0.7637 0.0204
-3.750 0.1348 0.01519 0.00653 -0.1135 0.7601 0.0267
-3.500 0.1578 0.01473 0.00615 -0.1129 0.7559 0.0429
-3.250 0.1820 0.01428 0.00584 -0.1126 0.7523 0.0798
-3.000 0.2063 0.01372 0.00556 -0.1125 0.7492 0.1557
-2.750 0.2290 0.01297 0.00533 -0.1123 0.7460 0.2945
-2.500 0.2476 0.01199 0.00520 -0.1115 0.7418 0.5105
-2.250 0.2601 0.01208 0.00605 -0.1070 0.7380 0.7103
-2.000 0.2875 0.01232 0.00614 -0.1067 0.7348 0.7571
-1.500 0.3365 0.01282 0.00646 -0.1047 0.7278 0.7942
-1.250 0.3594 0.01303 0.00660 -0.1033 0.7239 0.8065
-1.000 0.3797 0.01334 0.00686 -0.1010 0.7203 0.8236
-0.750 0.3991 0.01362 0.00709 -0.0983 0.7174 0.8409
-0.500 0.4184 0.01376 0.00720 -0.0962 0.7133 0.8507
-0.250 0.4427 0.01379 0.00717 -0.0957 0.7091 0.8547
0.000 0.4704 0.01378 0.00708 -0.0959 0.7054 0.8579
0.250 0.5008 0.01377 0.00695 -0.0968 0.7023 0.8606
0.500 0.5246 0.01378 0.00694 -0.0961 0.6981 0.8625
0.750 0.5491 0.01380 0.00693 -0.0957 0.6935 0.8643
1.000 0.5763 0.01379 0.00688 -0.0958 0.6896 0.8660
1.250 0.6057 0.01378 0.00679 -0.0963 0.6864 0.8677
1.500 0.6295 0.01383 0.00685 -0.0959 0.6812 0.8695
1.750 0.6560 0.01385 0.00685 -0.0959 0.6765 0.8714
2.000 0.6853 0.01384 0.00679 -0.0965 0.6725 0.8729
2.250 0.7118 0.01388 0.00683 -0.0967 0.6674 0.8743
2.500 0.7377 0.01391 0.00687 -0.0967 0.6618 0.8758
2.750 0.7649 0.01390 0.00684 -0.0967 0.6574 0.8770
3.000 0.7892 0.01394 0.00690 -0.0963 0.6519 0.8782
3.250 0.8141 0.01398 0.00696 -0.0960 0.6462 0.8794
3.500 0.8426 0.01397 0.00693 -0.0964 0.6414 0.8804
3.750 0.8649 0.01405 0.00707 -0.0956 0.6345 0.8820
4.000 0.8911 0.01406 0.00709 -0.0956 0.6283 0.8836
4.250 0.9156 0.01413 0.00718 -0.0952 0.6214 0.8852
4.500 0.9410 0.01417 0.00726 -0.0951 0.6142 0.8865
4.750 0.9659 0.01425 0.00736 -0.0949 0.6069 0.8879
5.000 0.9912 0.01432 0.00745 -0.0947 0.5991 0.8892
5.250 1.0147 0.01441 0.00760 -0.0942 0.5906 0.8905
5.500 1.0382 0.01447 0.00767 -0.0936 0.5823 0.8918
5.750 1.0578 0.01458 0.00785 -0.0923 0.5726 0.8936
6.000 1.0789 0.01469 0.00799 -0.0913 0.5628 0.8955
6.250 1.0999 0.01481 0.00813 -0.0903 0.5522 0.8974
6.500 1.1182 0.01498 0.00834 -0.0888 0.5402 0.8994
6.750 1.1358 0.01515 0.00855 -0.0872 0.5276 0.9015
7.000 1.1534 0.01538 0.00880 -0.0856 0.5143 0.9036
7.250 1.1693 0.01565 0.00909 -0.0838 0.4998 0.9058
7.500 1.1835 0.01596 0.00940 -0.0816 0.4844 0.9082
7.750 1.1971 0.01633 0.00978 -0.0795 0.4680 0.9110
8.000 1.2097 0.01678 0.01022 -0.0772 0.4509 0.9142
8.250 1.2209 0.01732 0.01073 -0.0749 0.4327 0.9181
8.500 1.2299 0.01790 0.01130 -0.0722 0.4142 0.9221
8.750 1.2380 0.01857 0.01196 -0.0695 0.3949 0.9265
9.000 1.2454 0.01936 0.01272 -0.0670 0.3757 0.9317
9.250 1.2512 0.02024 0.01359 -0.0642 0.3570 0.9380
9.750 1.2664 0.02219 0.01554 -0.0601 0.3192 0.9618
10.000 1.2730 0.02331 0.01664 -0.0583 0.3009 1.0000
10.250 1.2793 0.02469 0.01797 -0.0566 0.2822 1.0000
10.500 1.2868 0.02606 0.01933 -0.0552 0.2640 1.0000
10.750 1.2929 0.02755 0.02080 -0.0538 0.2455 1.0000
11.000 1.2985 0.02914 0.02235 -0.0523 0.2279 1.0000
11.250 1.3031 0.03084 0.02401 -0.0509 0.2105 1.0000
11.500 1.3075 0.03259 0.02573 -0.0496 0.1943 1.0000
11.750 1.3126 0.03436 0.02749 -0.0485 0.1783 1.0000
12.000 1.3170 0.03624 0.02934 -0.0473 0.1624 1.0000
12.250 1.3213 0.03818 0.03128 -0.0463 0.1477 1.0000
12.500 1.3252 0.04020 0.03329 -0.0453 0.1336 1.0000
12.750 1.3292 0.04228 0.03536 -0.0445 0.1211 1.0000
13.000 1.3325 0.04447 0.03756 -0.0437 0.1088 1.0000
13.250 1.3355 0.04675 0.03984 -0.0429 0.0977 1.0000
13.750 1.3411 0.05154 0.04467 -0.0418 0.0771 1.0000
14.000 1.3435 0.05407 0.04723 -0.0414 0.0681 1.0000
14.250 1.3450 0.05677 0.04997 -0.0410 0.0603 1.0000
14.500 1.3450 0.05970 0.05292 -0.0408 0.0530 1.0000
14.750 1.3467 0.06251 0.05580 -0.0406 0.0464 1.0000
15.000 1.3469 0.06558 0.05892 -0.0406 0.0411 1.0000
15.250 1.3458 0.06886 0.06226 -0.0407 0.0364 1.0000
15.500 1.3462 0.07206 0.06556 -0.0410 0.0324 1.0000
15.750 1.3439 0.07568 0.06923 -0.0414 0.0290 1.0000
16.000 1.3430 0.07918 0.07285 -0.0419 0.0260 1.0000
16.250 1.3405 0.08299 0.07674 -0.0425 0.0235 1.0000
16.500 1.3372 0.08698 0.08086 -0.0434 0.0212 1.0000
16.750 1.3348 0.09096 0.08495 -0.0443 0.0191 1.0000
17.000 1.3293 0.09545 0.08951 -0.0456 0.0174 1.0000
17.250 1.3268 0.09957 0.09379 -0.0468 0.0158 1.0000
17.500 1.3221 0.10410 0.09843 -0.0484 0.0144 1.0000
17.750 1.3153 0.10907 0.10350 -0.0502 0.0134 1.0000
18.000 1.3109 0.11371 0.10831 -0.0520 0.0123 1.0000
18.250 1.3053 0.11863 0.11335 -0.0540 0.0114 1.0000
18.500 1.2979 0.12393 0.11877 -0.0564 0.0107 1.0000
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