EPPLER 582 AIRFOIL (e582-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 582 AIRFOIL (e582-il) Reynolds number: 500,000 Max Cl/Cd: 112.01 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e582-il-500000.txt Download as CSV file: xf-e582-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.1790 0.11308 0.11077 -0.0800 0.9759 0.0131
-11.250 -0.1686 0.10890 0.10659 -0.0833 0.9685 0.0135
-11.000 -0.1581 0.10415 0.10183 -0.0874 0.9610 0.0143
-10.750 -0.1469 0.09865 0.09632 -0.0931 0.9534 0.0147
-10.500 -0.1331 0.09186 0.08952 -0.1012 0.9471 0.0150
-10.250 -0.1152 0.08540 0.08303 -0.1094 0.9410 0.0151
-10.000 -0.0986 0.07938 0.07698 -0.1167 0.9334 0.0153
-9.750 -0.0736 0.07650 0.07404 -0.1216 0.9239 0.0159
-9.500 -0.0549 0.07157 0.06903 -0.1288 0.9093 0.0161
-9.250 -0.0459 0.06720 0.06456 -0.1335 0.8918 0.0167
-9.000 -0.0478 0.06243 0.05971 -0.1375 0.8751 0.0167
-8.750 -0.0619 0.05669 0.05387 -0.1421 0.8597 0.0168
-8.500 -0.0785 0.05264 0.04970 -0.1430 0.8474 0.0167
-8.250 -0.0964 0.04969 0.04662 -0.1413 0.8372 0.0168
-8.000 -0.1072 0.04663 0.04343 -0.1396 0.8286 0.0172
-7.750 -0.1126 0.04319 0.03978 -0.1380 0.8221 0.0179
-7.500 -0.1244 0.03917 0.03517 -0.1342 0.8147 0.0191
-7.250 -0.1252 0.03473 0.03056 -0.1327 0.8097 0.0196
-7.000 -0.1124 0.03299 0.02877 -0.1318 0.8049 0.0200
-6.750 -0.0987 0.03139 0.02706 -0.1308 0.8002 0.0205
-6.500 -0.1028 0.02213 0.01658 -0.1248 0.7958 0.0115
-6.250 -0.0843 0.01967 0.01376 -0.1236 0.7920 0.0112
-6.000 -0.0628 0.01798 0.01178 -0.1225 0.7879 0.0113
-5.750 -0.0389 0.01683 0.01039 -0.1218 0.7841 0.0115
-5.500 -0.0139 0.01591 0.00927 -0.1213 0.7807 0.0116
-5.250 0.0113 0.01497 0.00818 -0.1210 0.7775 0.0119
-5.000 0.0345 0.01422 0.00746 -0.1205 0.7737 0.0129
-4.750 0.0594 0.01373 0.00694 -0.1201 0.7700 0.0138
-4.500 0.0840 0.01312 0.00625 -0.1196 0.7666 0.0142
-4.250 0.1092 0.01260 0.00565 -0.1192 0.7634 0.0146
-4.000 0.1336 0.01213 0.00513 -0.1187 0.7600 0.0152
-3.750 0.1577 0.01161 0.00461 -0.1182 0.7564 0.0170
-3.500 0.1835 0.01122 0.00419 -0.1180 0.7529 0.0220
-3.250 0.2084 0.01062 0.00378 -0.1177 0.7497 0.0698
-3.000 0.2339 0.01014 0.00361 -0.1178 0.7466 0.1544
-2.750 0.2569 0.00939 0.00345 -0.1178 0.7430 0.3127
-2.500 0.2768 0.00801 0.00342 -0.1173 0.7393 0.6745
-2.250 0.3034 0.00827 0.00373 -0.1167 0.7360 0.7556
-2.000 0.3313 0.00853 0.00390 -0.1164 0.7330 0.7742
-1.750 0.3580 0.00874 0.00407 -0.1160 0.7296 0.7873
-1.500 0.3841 0.00896 0.00425 -0.1154 0.7259 0.7996
-1.250 0.4088 0.00916 0.00444 -0.1144 0.7223 0.8075
-1.000 0.4367 0.00931 0.00450 -0.1143 0.7191 0.8161
-0.750 0.4615 0.00950 0.00467 -0.1134 0.7158 0.8217
-0.500 0.4867 0.00966 0.00481 -0.1127 0.7119 0.8310
-0.250 0.5061 0.00989 0.00507 -0.1102 0.7081 0.8407
0.000 0.5282 0.01005 0.00521 -0.1086 0.7046 0.8499
0.250 0.5535 0.01020 0.00530 -0.1079 0.7012 0.8556
0.500 0.5805 0.01019 0.00528 -0.1080 0.6971 0.8589
0.750 0.6093 0.01016 0.00522 -0.1085 0.6928 0.8611
1.000 0.6361 0.01011 0.00513 -0.1084 0.6889 0.8626
1.250 0.6634 0.01013 0.00511 -0.1084 0.6850 0.8641
1.500 0.6891 0.01009 0.00509 -0.1082 0.6803 0.8656
1.750 0.7165 0.01007 0.00505 -0.1084 0.6759 0.8670
2.000 0.7455 0.01008 0.00501 -0.1088 0.6720 0.8682
2.250 0.7724 0.01007 0.00502 -0.1089 0.6673 0.8697
2.500 0.7999 0.01005 0.00500 -0.1092 0.6621 0.8708
2.750 0.8287 0.01004 0.00495 -0.1097 0.6574 0.8721
3.000 0.8560 0.01005 0.00497 -0.1099 0.6519 0.8733
3.250 0.8837 0.01004 0.00497 -0.1102 0.6462 0.8742
3.750 0.9383 0.01005 0.00498 -0.1106 0.6347 0.8761
4.000 0.9642 0.01004 0.00497 -0.1105 0.6286 0.8770
4.250 0.9899 0.01006 0.00501 -0.1103 0.6221 0.8779
4.500 1.0152 0.01007 0.00504 -0.1101 0.6149 0.8787
4.750 1.0407 0.01011 0.00509 -0.1099 0.6079 0.8796
5.000 1.0653 0.01015 0.00516 -0.1095 0.5997 0.8806
5.250 1.0896 0.01021 0.00524 -0.1091 0.5913 0.8818
5.500 1.1137 0.01029 0.00531 -0.1087 0.5825 0.8831
5.750 1.1372 0.01037 0.00543 -0.1081 0.5725 0.8842
6.000 1.1605 0.01048 0.00554 -0.1075 0.5624 0.8853
6.250 1.1827 0.01062 0.00567 -0.1068 0.5513 0.8865
6.500 1.2040 0.01075 0.00583 -0.1058 0.5387 0.8877
6.750 1.2243 0.01093 0.00600 -0.1047 0.5250 0.8889
7.000 1.2424 0.01113 0.00619 -0.1032 0.5105 0.8901
7.250 1.2562 0.01133 0.00638 -0.1007 0.4946 0.8916
7.500 1.2683 0.01163 0.00665 -0.0980 0.4775 0.8936
7.750 1.2806 0.01199 0.00699 -0.0954 0.4588 0.8955
8.000 1.2928 0.01240 0.00737 -0.0929 0.4397 0.8973
8.250 1.3031 0.01291 0.00782 -0.0901 0.4199 0.8994
8.500 1.3123 0.01349 0.00836 -0.0873 0.3991 0.9016
8.750 1.3214 0.01414 0.00895 -0.0847 0.3777 0.9038
9.250 1.3342 0.01566 0.01036 -0.0787 0.3359 0.9087
9.500 1.3394 0.01657 0.01121 -0.0757 0.3149 0.9117
9.750 1.3446 0.01756 0.01214 -0.0730 0.2943 0.9151
10.000 1.3506 0.01862 0.01315 -0.0705 0.2734 0.9188
10.250 1.3539 0.01975 0.01424 -0.0677 0.2540 0.9229
10.500 1.3584 0.02092 0.01537 -0.0652 0.2356 0.9276
10.750 1.3641 0.02213 0.01654 -0.0631 0.2175 0.9328
11.000 1.3688 0.02333 0.01774 -0.0608 0.2014 0.9402
11.250 1.3740 0.02469 0.01907 -0.0589 0.1841 0.9524
11.500 1.3805 0.02617 0.02053 -0.0577 0.1672 1.0000
11.750 1.3875 0.02777 0.02207 -0.0565 0.1508 1.0000
12.000 1.3939 0.02944 0.02369 -0.0554 0.1345 1.0000
12.250 1.3993 0.03121 0.02540 -0.0543 0.1190 1.0000
12.500 1.4032 0.03314 0.02726 -0.0531 0.1031 1.0000
12.750 1.4059 0.03520 0.02924 -0.0519 0.0881 1.0000
13.500 1.4150 0.04163 0.03554 -0.0489 0.0532 1.0000
13.750 1.4184 0.04384 0.03774 -0.0481 0.0449 1.0000
14.000 1.4202 0.04625 0.04012 -0.0474 0.0366 1.0000
14.250 1.4237 0.04858 0.04247 -0.0468 0.0310 1.0000
14.500 1.4267 0.05103 0.04495 -0.0463 0.0270 1.0000
14.750 1.4287 0.05361 0.04755 -0.0459 0.0232 1.0000
15.000 1.4319 0.05614 0.05014 -0.0456 0.0203 1.0000
15.250 1.4324 0.05904 0.05307 -0.0453 0.0176 1.0000
15.500 1.4359 0.06166 0.05579 -0.0453 0.0154 1.0000
15.750 1.4352 0.06484 0.05902 -0.0453 0.0135 1.0000
16.000 1.4373 0.06774 0.06201 -0.0454 0.0118 1.0000
16.250 1.4353 0.07124 0.06557 -0.0456 0.0101 1.0000
16.500 1.4341 0.07472 0.06914 -0.0460 0.0084 1.0000
16.750 1.4313 0.07852 0.07302 -0.0466 0.0072 1.0000
17.000 1.4243 0.08298 0.07755 -0.0473 0.0058 1.0000
17.250 1.4216 0.08692 0.08163 -0.0482 0.0050 1.0000
17.500 1.4130 0.09185 0.08665 -0.0494 0.0042 1.0000
17.750 1.4062 0.09666 0.09159 -0.0507 0.0038 1.0000
18.000 1.4004 0.10138 0.09643 -0.0522 0.0032 1.0000
18.250 1.3915 0.10668 0.10184 -0.0540 0.0029 1.0000
18.500 1.3792 0.11271 0.10801 -0.0563 0.0027 1.0000
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