EPPLER 582 AIRFOIL (e582-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 582 AIRFOIL (e582-il) Reynolds number: 1,000,000 Max Cl/Cd: 140.43 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e582-il-1000000.txt Download as CSV file: xf-e582-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.0490 0.08278 0.08075 -0.1257 0.9083 0.0082
-10.250 -0.0416 0.07793 0.07574 -0.1300 0.8817 0.0085
-10.000 -0.0414 0.07417 0.07188 -0.1316 0.8607 0.0085
-9.750 -0.0503 0.06765 0.06530 -0.1343 0.8444 0.0088
-9.500 -0.0539 0.06355 0.06115 -0.1362 0.8320 0.0088
-9.250 -0.0681 0.05563 0.05318 -0.1422 0.8199 0.0089
-9.000 -0.0627 0.03455 0.03202 -0.1357 0.7940 0.0089
-8.750 -0.1028 0.04571 0.04303 -0.1443 0.8007 0.0088
-8.250 -0.1406 0.03911 0.03610 -0.1382 0.7858 0.0089
-8.000 -0.1519 0.03576 0.03248 -0.1351 0.7798 0.0089
-7.750 -0.1729 0.03050 0.02691 -0.1314 0.7745 0.0092
-7.500 -0.1624 0.02883 0.02513 -0.1301 0.7701 0.0093
-7.250 -0.1505 0.02717 0.02330 -0.1287 0.7659 0.0094
-7.000 -0.1636 0.01808 0.01316 -0.1225 0.7616 0.0055
-6.750 -0.1462 0.01556 0.01023 -0.1209 0.7581 0.0054
-6.500 -0.1233 0.01453 0.00902 -0.1202 0.7547 0.0056
-6.250 -0.0991 0.01381 0.00815 -0.1197 0.7513 0.0060
-6.000 -0.0740 0.01330 0.00750 -0.1194 0.7478 0.0063
-5.750 -0.0494 0.01264 0.00673 -0.1189 0.7449 0.0066
-5.500 -0.0264 0.01178 0.00581 -0.1183 0.7417 0.0069
-5.250 -0.0016 0.01129 0.00527 -0.1180 0.7385 0.0071
-5.000 0.0239 0.01093 0.00486 -0.1178 0.7353 0.0074
-4.750 0.0498 0.01061 0.00448 -0.1176 0.7319 0.0076
-4.500 0.0757 0.01025 0.00409 -0.1174 0.7293 0.0079
-4.250 0.1021 0.00996 0.00378 -0.1173 0.7263 0.0083
-4.000 0.1292 0.00978 0.00356 -0.1173 0.7232 0.0089
-3.750 0.1551 0.00940 0.00313 -0.1172 0.7201 0.0099
-3.500 0.1825 0.00922 0.00289 -0.1172 0.7167 0.0110
-3.250 0.2091 0.00886 0.00256 -0.1171 0.7141 0.0205
-3.000 0.2354 0.00847 0.00238 -0.1172 0.7110 0.0651
-2.750 0.2625 0.00821 0.00226 -0.1174 0.7080 0.1066
-2.500 0.2893 0.00788 0.00215 -0.1176 0.7048 0.1804
-2.250 0.3154 0.00720 0.00202 -0.1181 0.7013 0.3626
-2.000 0.3411 0.00600 0.00194 -0.1188 0.6986 0.7007
-1.750 0.3694 0.00606 0.00204 -0.1189 0.6953 0.7435
-1.500 0.3980 0.00613 0.00207 -0.1191 0.6921 0.7577
-1.250 0.4268 0.00625 0.00213 -0.1193 0.6888 0.7699
-1.000 0.4548 0.00639 0.00224 -0.1193 0.6854 0.7782
-0.750 0.4833 0.00646 0.00228 -0.1195 0.6822 0.7850
-0.500 0.5109 0.00651 0.00234 -0.1194 0.6786 0.7897
-0.250 0.5386 0.00660 0.00240 -0.1194 0.6748 0.7951
0.000 0.5666 0.00674 0.00248 -0.1195 0.6708 0.8016
0.250 0.5923 0.00686 0.00266 -0.1189 0.6670 0.8094
0.500 0.6194 0.00698 0.00277 -0.1187 0.6628 0.8169
0.750 0.6456 0.00705 0.00283 -0.1183 0.6588 0.8206
1.000 0.6734 0.00710 0.00286 -0.1185 0.6548 0.8224
1.250 0.7015 0.00711 0.00287 -0.1187 0.6505 0.8239
1.500 0.7295 0.00713 0.00286 -0.1189 0.6458 0.8251
1.750 0.7573 0.00718 0.00287 -0.1191 0.6408 0.8262
2.000 0.7855 0.00718 0.00288 -0.1194 0.6358 0.8272
2.250 0.8132 0.00722 0.00289 -0.1196 0.6302 0.8282
2.500 0.8407 0.00727 0.00291 -0.1198 0.6250 0.8289
2.750 0.8687 0.00729 0.00294 -0.1201 0.6191 0.8297
3.000 0.8958 0.00736 0.00297 -0.1202 0.6132 0.8304
3.250 0.9232 0.00738 0.00301 -0.1203 0.6071 0.8312
3.500 0.9499 0.00742 0.00303 -0.1203 0.6002 0.8319
3.750 0.9763 0.00748 0.00308 -0.1203 0.5935 0.8327
4.000 1.0026 0.00753 0.00314 -0.1202 0.5858 0.8334
4.250 1.0284 0.00761 0.00321 -0.1201 0.5778 0.8341
4.500 1.0536 0.00771 0.00329 -0.1198 0.5687 0.8350
4.750 1.0792 0.00780 0.00339 -0.1196 0.5596 0.8360
5.000 1.1035 0.00793 0.00350 -0.1191 0.5495 0.8368
5.250 1.1275 0.00806 0.00361 -0.1187 0.5381 0.8376
5.500 1.1515 0.00820 0.00374 -0.1182 0.5259 0.8384
5.750 1.1742 0.00837 0.00389 -0.1175 0.5123 0.8393
6.000 1.1959 0.00857 0.00405 -0.1165 0.4972 0.8402
6.250 1.2165 0.00880 0.00424 -0.1154 0.4811 0.8412
6.500 1.2344 0.00909 0.00446 -0.1138 0.4625 0.8422
6.750 1.2506 0.00937 0.00468 -0.1118 0.4432 0.8433
7.000 1.2653 0.00971 0.00495 -0.1095 0.4228 0.8444
7.250 1.2798 0.01010 0.00527 -0.1072 0.4034 0.8455
7.500 1.2931 0.01051 0.00561 -0.1048 0.3818 0.8468
7.750 1.3057 0.01097 0.00599 -0.1023 0.3603 0.8481
8.000 1.3172 0.01147 0.00642 -0.0997 0.3401 0.8494
8.250 1.3287 0.01200 0.00688 -0.0972 0.3185 0.8508
8.500 1.3377 0.01264 0.00743 -0.0943 0.2968 0.8522
8.750 1.3481 0.01326 0.00798 -0.0917 0.2764 0.8537
9.000 1.3557 0.01402 0.00865 -0.0888 0.2544 0.8553
9.250 1.3617 0.01490 0.00942 -0.0858 0.2299 0.8570
9.500 1.3664 0.01590 0.01029 -0.0828 0.2058 0.8587
9.750 1.3738 0.01683 0.01115 -0.0803 0.1865 0.8601
10.000 1.3848 0.01761 0.01192 -0.0784 0.1756 0.8618
10.250 1.3873 0.01886 0.01305 -0.0754 0.1527 0.8641
10.500 1.3933 0.01999 0.01412 -0.0731 0.1354 0.8663
10.750 1.3961 0.02138 0.01541 -0.0705 0.1149 0.8685
11.000 1.4038 0.02253 0.01653 -0.0686 0.1030 0.8706
11.250 1.4098 0.02385 0.01781 -0.0667 0.0898 0.8728
11.500 1.4160 0.02521 0.01912 -0.0649 0.0779 0.8749
11.750 1.4205 0.02670 0.02056 -0.0630 0.0655 0.8774
12.000 1.4276 0.02805 0.02192 -0.0614 0.0569 0.8801
12.250 1.4324 0.02962 0.02347 -0.0597 0.0472 0.8831
12.500 1.4373 0.03124 0.02507 -0.0582 0.0389 0.8863
12.750 1.4434 0.03284 0.02666 -0.0569 0.0328 0.8895
13.000 1.4487 0.03451 0.02835 -0.0556 0.0273 0.8934
13.250 1.4542 0.03619 0.03006 -0.0543 0.0232 0.8982
13.500 1.4613 0.03780 0.03173 -0.0533 0.0201 0.9037
13.750 1.4663 0.03957 0.03354 -0.0521 0.0172 0.9114
14.000 1.4708 0.04134 0.03539 -0.0509 0.0146 0.9244
14.250 1.4765 0.04309 0.03726 -0.0501 0.0124 1.0000
14.500 1.4828 0.04507 0.03928 -0.0496 0.0109 1.0000
14.750 1.4887 0.04713 0.04138 -0.0491 0.0092 1.0000
15.000 1.4933 0.04937 0.04366 -0.0486 0.0078 1.0000
15.250 1.4958 0.05188 0.04619 -0.0482 0.0053 1.0000
15.500 1.4961 0.05467 0.04903 -0.0477 0.0034 1.0000
15.750 1.4964 0.05757 0.05199 -0.0474 0.0023 1.0000
16.000 1.4942 0.06083 0.05533 -0.0472 0.0014 1.0000
16.250 1.4902 0.06443 0.05903 -0.0471 0.0009 1.0000
16.500 1.4911 0.06748 0.06217 -0.0472 0.0008 1.0000
16.750 1.4922 0.07059 0.06536 -0.0475 0.0007 1.0000
17.000 1.4911 0.07405 0.06893 -0.0479 0.0007 1.0000
17.250 1.4915 0.07740 0.07237 -0.0484 0.0006 1.0000
17.500 1.4892 0.08116 0.07623 -0.0491 0.0006 1.0000
17.750 1.4875 0.08492 0.08009 -0.0498 0.0006 1.0000
18.000 1.4814 0.08943 0.08472 -0.0509 0.0005 1.0000
18.250 1.4761 0.09390 0.08931 -0.0521 0.0005 1.0000
18.500 1.4680 0.09893 0.09446 -0.0536 0.0005 1.0000
18.750 1.4598 0.10405 0.09971 -0.0553 0.0005 1.0000
19.000 1.4508 0.10942 0.10520 -0.0573 0.0004 1.0000
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Polar data table (+)
Polar graphs
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