EPPLER 583 AIRFOIL (e583-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 583 AIRFOIL (e583-il) Reynolds number: 1,000,000 Max Cl/Cd: 132.03 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e583-il-1000000-n5.txt Download as CSV file: xf-e583-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 583 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.3921 0.04281 0.03947 -0.1376 0.7233 0.0027
-12.250 -0.4489 0.03531 0.03161 -0.1377 0.7174 0.0027
-12.000 -0.4679 0.03217 0.02825 -0.1357 0.7124 0.0027
-11.750 -0.4751 0.03012 0.02604 -0.1336 0.7073 0.0027
-11.500 -0.4827 0.02814 0.02388 -0.1308 0.7022 0.0027
-11.250 -0.4991 0.02557 0.02100 -0.1265 0.6977 0.0028
-11.000 -0.4997 0.02421 0.01949 -0.1234 0.6935 0.0028
-10.750 -0.4981 0.02316 0.01829 -0.1200 0.6891 0.0028
-10.500 -0.4920 0.02199 0.01693 -0.1173 0.6848 0.0028
-10.250 -0.4815 0.02088 0.01565 -0.1153 0.6812 0.0028
-10.000 -0.4677 0.01988 0.01450 -0.1136 0.6781 0.0029
-9.750 -0.4521 0.01898 0.01346 -0.1121 0.6748 0.0029
-9.500 -0.4353 0.01813 0.01246 -0.1108 0.6716 0.0029
-9.250 -0.4162 0.01749 0.01170 -0.1097 0.6684 0.0029
-9.000 -0.3965 0.01685 0.01094 -0.1087 0.6656 0.0030
-8.750 -0.3755 0.01626 0.01027 -0.1079 0.6632 0.0030
-8.500 -0.3542 0.01567 0.00958 -0.1071 0.6604 0.0030
-8.250 -0.3338 0.01495 0.00875 -0.1061 0.6575 0.0032
-8.000 -0.3123 0.01438 0.00808 -0.1053 0.6545 0.0032
-7.750 -0.2904 0.01385 0.00747 -0.1046 0.6518 0.0034
-7.500 -0.2667 0.01349 0.00706 -0.1041 0.6494 0.0035
-7.250 -0.2425 0.01311 0.00664 -0.1036 0.6475 0.0037
-7.000 -0.2178 0.01280 0.00629 -0.1033 0.6454 0.0039
-6.750 -0.1933 0.01245 0.00590 -0.1029 0.6431 0.0039
-6.500 -0.1682 0.01219 0.00560 -0.1026 0.6406 0.0042
-6.250 -0.1433 0.01191 0.00527 -0.1023 0.6382 0.0044
-6.000 -0.1184 0.01164 0.00495 -0.1019 0.6358 0.0045
-5.500 -0.0672 0.01116 0.00441 -0.1014 0.6319 0.0048
-5.250 -0.0413 0.01091 0.00412 -0.1012 0.6299 0.0049
-5.000 -0.0155 0.01066 0.00385 -0.1010 0.6277 0.0053
-4.750 0.0107 0.01045 0.00363 -0.1009 0.6255 0.0057
-4.500 0.0370 0.01028 0.00343 -0.1008 0.6232 0.0061
-4.250 0.0634 0.01012 0.00324 -0.1007 0.6210 0.0067
-4.000 0.0897 0.00996 0.00307 -0.1005 0.6187 0.0081
-3.750 0.1164 0.00980 0.00291 -0.1005 0.6168 0.0104
-3.500 0.1433 0.00961 0.00275 -0.1005 0.6150 0.0158
-3.250 0.1702 0.00944 0.00261 -0.1005 0.6130 0.0248
-3.000 0.1972 0.00928 0.00249 -0.1006 0.6109 0.0364
-2.750 0.2240 0.00910 0.00238 -0.1006 0.6087 0.0537
-2.500 0.2503 0.00887 0.00228 -0.1006 0.6066 0.0889
-2.250 0.2767 0.00865 0.00218 -0.1006 0.6044 0.1311
-2.000 0.3024 0.00835 0.00209 -0.1006 0.6021 0.2008
-1.750 0.3290 0.00804 0.00201 -0.1008 0.6003 0.2747
-1.500 0.3558 0.00769 0.00192 -0.1010 0.5983 0.3607
-1.250 0.3821 0.00719 0.00182 -0.1013 0.5961 0.4919
-1.000 0.4081 0.00659 0.00175 -0.1016 0.5937 0.6624
-0.750 0.4360 0.00654 0.00181 -0.1017 0.5913 0.7140
-0.500 0.4643 0.00658 0.00184 -0.1019 0.5887 0.7303
-0.250 0.4926 0.00664 0.00186 -0.1021 0.5863 0.7413
0.000 0.5212 0.00668 0.00192 -0.1024 0.5842 0.7562
0.250 0.5496 0.00676 0.00202 -0.1025 0.5818 0.7725
0.500 0.5775 0.00683 0.00211 -0.1026 0.5791 0.7821
0.750 0.6060 0.00688 0.00214 -0.1029 0.5764 0.7850
1.000 0.6343 0.00692 0.00215 -0.1032 0.5735 0.7866
1.250 0.6623 0.00698 0.00217 -0.1034 0.5707 0.7881
1.500 0.6911 0.00702 0.00219 -0.1038 0.5681 0.7892
1.750 0.7197 0.00705 0.00222 -0.1042 0.5648 0.7903
2.000 0.7477 0.00708 0.00225 -0.1044 0.5613 0.7918
2.250 0.7750 0.00714 0.00229 -0.1045 0.5571 0.7932
2.500 0.8025 0.00720 0.00234 -0.1047 0.5533 0.7945
2.750 0.8306 0.00724 0.00239 -0.1049 0.5490 0.7957
3.000 0.8579 0.00730 0.00244 -0.1051 0.5439 0.7970
3.250 0.8845 0.00739 0.00250 -0.1051 0.5389 0.7983
3.500 0.9121 0.00745 0.00257 -0.1053 0.5337 0.7996
3.750 0.9387 0.00753 0.00264 -0.1053 0.5274 0.8010
4.000 0.9651 0.00763 0.00272 -0.1052 0.5215 0.8026
4.250 0.9915 0.00772 0.00281 -0.1052 0.5142 0.8041
4.500 1.0167 0.00784 0.00291 -0.1050 0.5064 0.8055
4.750 1.0421 0.00797 0.00301 -0.1048 0.4976 0.8066
5.000 1.0665 0.00810 0.00313 -0.1044 0.4888 0.8080
5.500 1.1130 0.00843 0.00343 -0.1032 0.4678 0.8109
5.750 1.1354 0.00862 0.00360 -0.1024 0.4574 0.8124
6.000 1.1564 0.00885 0.00380 -0.1014 0.4461 0.8141
6.250 1.1765 0.00908 0.00400 -0.1003 0.4337 0.8158
6.500 1.1942 0.00932 0.00420 -0.0986 0.4203 0.8179
6.750 1.2113 0.00957 0.00443 -0.0968 0.4079 0.8199
7.000 1.2275 0.00988 0.00470 -0.0949 0.3951 0.8217
7.500 1.2569 0.01059 0.00533 -0.0907 0.3677 0.8254
7.750 1.2702 0.01099 0.00571 -0.0884 0.3534 0.8274
8.000 1.2820 0.01145 0.00613 -0.0859 0.3379 0.8296
8.250 1.2916 0.01199 0.00662 -0.0831 0.3203 0.8320
8.500 1.3001 0.01260 0.00717 -0.0802 0.3033 0.8346
8.750 1.3086 0.01325 0.00777 -0.0775 0.2881 0.8371
9.250 1.3241 0.01470 0.00916 -0.0721 0.2610 0.8425
9.500 1.3296 0.01559 0.01002 -0.0693 0.2463 0.8454
9.750 1.3346 0.01658 0.01098 -0.0667 0.2318 0.8485
10.000 1.3410 0.01759 0.01196 -0.0643 0.2191 0.8516
10.250 1.3468 0.01869 0.01304 -0.0621 0.2061 0.8545
10.500 1.3509 0.01993 0.01425 -0.0598 0.1922 0.8575
10.750 1.3536 0.02130 0.01559 -0.0574 0.1778 0.8611
11.000 1.3565 0.02274 0.01700 -0.0553 0.1639 0.8649
11.250 1.3582 0.02432 0.01853 -0.0531 0.1496 0.8688
11.500 1.3592 0.02600 0.02016 -0.0511 0.1350 0.8728
11.750 1.3635 0.02749 0.02166 -0.0494 0.1247 0.8776
12.000 1.3647 0.02926 0.02339 -0.0475 0.1118 0.8828
12.500 1.3711 0.03264 0.02677 -0.0445 0.0918 0.8939
12.750 1.3687 0.03484 0.02891 -0.0428 0.0768 0.9011
13.000 1.3743 0.03642 0.03054 -0.0416 0.0722 0.9100
13.250 1.3761 0.03829 0.03243 -0.0401 0.0631 0.9239
13.500 1.3796 0.04051 0.03469 -0.0397 0.0529 0.9583
14.000 1.3832 0.04515 0.03926 -0.0384 0.0345 1.0000
14.250 1.3847 0.04754 0.04163 -0.0377 0.0278 1.0000
14.500 1.3916 0.04944 0.04355 -0.0373 0.0255 1.0000
14.750 1.3949 0.05173 0.04586 -0.0369 0.0217 1.0000
15.250 1.4031 0.05633 0.05050 -0.0363 0.0155 1.0000
15.500 1.4087 0.05852 0.05273 -0.0362 0.0139 1.0000
15.750 1.4119 0.06101 0.05525 -0.0361 0.0120 1.0000
16.000 1.4172 0.06332 0.05761 -0.0360 0.0107 1.0000
16.250 1.4207 0.06588 0.06021 -0.0361 0.0095 1.0000
16.500 1.4245 0.06844 0.06282 -0.0362 0.0082 1.0000
16.750 1.4274 0.07116 0.06559 -0.0364 0.0072 1.0000
17.000 1.4312 0.07380 0.06829 -0.0367 0.0065 1.0000
17.250 1.4333 0.07669 0.07123 -0.0371 0.0056 1.0000
17.500 1.4349 0.07972 0.07432 -0.0375 0.0047 1.0000
17.750 1.4372 0.08268 0.07734 -0.0380 0.0043 1.0000
18.000 1.4391 0.08577 0.08050 -0.0387 0.0039 1.0000
18.250 1.4392 0.08910 0.08389 -0.0394 0.0032 1.0000
18.500 1.4397 0.09244 0.08730 -0.0402 0.0028 1.0000
18.750 1.4398 0.09588 0.09081 -0.0411 0.0026 1.0000
19.000 1.4394 0.09943 0.09443 -0.0421 0.0022 1.0000
19.250 1.4385 0.10310 0.09818 -0.0433 0.0020 1.0000
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Polar data table (+)
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