EPPLER 543 AIRFOIL (e543-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 543 AIRFOIL (e543-il) Reynolds number: 500,000 Max Cl/Cd: 86.22 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e543-il-500000.txt Download as CSV file: xf-e543-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 543 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
------ -------- --------- --------- -------- -------- --------
-12.250 -0.3441 0.09274 0.09073 -0.0609 1.0000 0.0195
-12.000 -0.3919 0.07585 0.07380 -0.0699 1.0000 0.0191
-10.250 -0.6620 0.03650 0.03210 -0.0690 0.9558 0.0121
-10.000 -0.6321 0.03456 0.03011 -0.0723 0.9476 0.0125
-9.750 -0.6071 0.02615 0.02051 -0.0725 0.9440 0.0094
-9.500 -0.5641 0.02407 0.01820 -0.0761 0.9375 0.0095
-9.250 -0.5184 0.02251 0.01651 -0.0804 0.9292 0.0098
-9.000 -0.4767 0.02166 0.01557 -0.0845 0.9145 0.0106
-8.750 -0.4385 0.02054 0.01425 -0.0867 0.9003 0.0110
-8.500 -0.4080 0.01973 0.01328 -0.0875 0.8849 0.0112
-8.250 -0.3833 0.01895 0.01236 -0.0872 0.8705 0.0113
-8.000 -0.3633 0.01831 0.01161 -0.0861 0.8570 0.0115
-7.750 -0.3457 0.01773 0.01092 -0.0847 0.8446 0.0118
-7.500 -0.3326 0.01703 0.01015 -0.0827 0.8325 0.0119
-7.250 -0.3207 0.01634 0.00942 -0.0805 0.8215 0.0128
-7.000 -0.3060 0.01583 0.00882 -0.0786 0.8118 0.0136
-6.750 -0.2912 0.01536 0.00828 -0.0768 0.8023 0.0144
-6.500 -0.2785 0.01478 0.00766 -0.0746 0.7940 0.0165
-6.250 -0.2657 0.01424 0.00708 -0.0723 0.7855 0.0218
-6.000 -0.2564 0.01359 0.00647 -0.0695 0.7780 0.0354
-5.750 -0.2485 0.01296 0.00598 -0.0665 0.7698 0.0628
-5.500 -0.2440 0.01237 0.00553 -0.0629 0.7628 0.1025
-5.250 -0.2433 0.01185 0.00521 -0.0584 0.7552 0.1475
-5.000 -0.2416 0.01112 0.00478 -0.0542 0.7489 0.2261
-4.750 -0.2457 0.01003 0.00423 -0.0493 0.7426 0.3524
-4.500 -0.2546 0.00840 0.00347 -0.0435 0.7363 0.5498
-4.250 -0.2346 0.00849 0.00393 -0.0417 0.7313 0.6729
-4.000 -0.2082 0.00875 0.00411 -0.0414 0.7258 0.6961
-3.750 -0.1796 0.00920 0.00451 -0.0411 0.7206 0.7085
-3.500 -0.1504 0.00959 0.00482 -0.0411 0.7162 0.7164
-3.250 -0.1220 0.00997 0.00516 -0.0410 0.7116 0.7243
-3.000 -0.0931 0.01045 0.00561 -0.0407 0.7069 0.7313
-2.750 -0.0627 0.01123 0.00638 -0.0404 0.7025 0.7396
-2.500 -0.0318 0.01210 0.00723 -0.0399 0.6984 0.7473
-2.250 -0.0004 0.01284 0.00799 -0.0396 0.6940 0.7512
-2.000 0.0263 0.01281 0.00790 -0.0396 0.6898 0.7540
-1.750 0.0515 0.01257 0.00755 -0.0399 0.6859 0.7578
-1.500 0.0779 0.01239 0.00727 -0.0402 0.6821 0.7602
-1.250 0.1045 0.01231 0.00717 -0.0401 0.6779 0.7612
-1.000 0.1317 0.01225 0.00708 -0.0402 0.6739 0.7622
-0.750 0.1594 0.01222 0.00700 -0.0404 0.6703 0.7631
-0.500 0.1877 0.01223 0.00694 -0.0407 0.6667 0.7641
-0.250 0.2144 0.01214 0.00686 -0.0408 0.6630 0.7651
0.000 0.2415 0.01209 0.00679 -0.0410 0.6592 0.7663
0.250 0.2690 0.01202 0.00669 -0.0412 0.6556 0.7676
0.500 0.2972 0.01197 0.00656 -0.0417 0.6522 0.7687
0.750 0.3245 0.01189 0.00647 -0.0421 0.6486 0.7700
1.000 0.3516 0.01179 0.00637 -0.0424 0.6447 0.7717
1.250 0.3794 0.01169 0.00624 -0.0428 0.6408 0.7730
1.500 0.4078 0.01163 0.00611 -0.0434 0.6371 0.7741
1.750 0.4359 0.01158 0.00604 -0.0440 0.6330 0.7751
2.000 0.4624 0.01147 0.00594 -0.0440 0.6285 0.7760
2.250 0.4893 0.01140 0.00588 -0.0441 0.6242 0.7769
2.500 0.5174 0.01139 0.00584 -0.0445 0.6202 0.7776
2.750 0.5440 0.01136 0.00584 -0.0445 0.6159 0.7783
3.000 0.5706 0.01131 0.00582 -0.0446 0.6111 0.7791
3.250 0.5979 0.01129 0.00580 -0.0448 0.6066 0.7798
3.500 0.6257 0.01131 0.00581 -0.0451 0.6021 0.7806
3.750 0.6515 0.01127 0.00582 -0.0450 0.5969 0.7815
4.000 0.6783 0.01124 0.00581 -0.0451 0.5917 0.7823
4.250 0.7057 0.01128 0.00583 -0.0453 0.5865 0.7834
4.500 0.7309 0.01124 0.00587 -0.0451 0.5805 0.7845
4.750 0.7572 0.01123 0.00586 -0.0451 0.5744 0.7856
5.000 0.7832 0.01123 0.00589 -0.0451 0.5682 0.7866
5.250 0.8085 0.01120 0.00591 -0.0449 0.5611 0.7875
5.500 0.8347 0.01123 0.00593 -0.0449 0.5547 0.7885
5.750 0.8592 0.01121 0.00597 -0.0446 0.5464 0.7895
6.000 0.8840 0.01125 0.00601 -0.0443 0.5381 0.7903
6.250 0.9077 0.01126 0.00606 -0.0438 0.5277 0.7912
6.500 0.9304 0.01125 0.00610 -0.0431 0.5163 0.7921
6.750 0.9521 0.01129 0.00617 -0.0422 0.5040 0.7930
7.000 0.9723 0.01136 0.00626 -0.0410 0.4886 0.7940
7.250 0.9907 0.01149 0.00639 -0.0394 0.4698 0.7952
7.500 1.0060 0.01171 0.00656 -0.0373 0.4476 0.7964
7.750 1.0170 0.01199 0.00677 -0.0344 0.4196 0.7976
8.000 1.0230 0.01237 0.00705 -0.0306 0.3902 0.7989
8.250 1.0278 0.01291 0.00746 -0.0268 0.3594 0.8003
8.500 1.0334 0.01353 0.00796 -0.0233 0.3308 0.8017
8.750 1.0373 0.01425 0.00855 -0.0197 0.3012 0.8032
9.000 1.0416 0.01501 0.00920 -0.0163 0.2750 0.8047
9.250 1.0458 0.01583 0.00990 -0.0132 0.2487 0.8060
9.500 1.0509 0.01666 0.01066 -0.0103 0.2264 0.8072
9.750 1.0555 0.01752 0.01145 -0.0075 0.2054 0.8087
10.000 1.0596 0.01847 0.01235 -0.0048 0.1868 0.8103
10.250 1.0641 0.01950 0.01333 -0.0023 0.1679 0.8119
10.500 1.0689 0.02058 0.01437 -0.0001 0.1503 0.8135
10.750 1.0740 0.02172 0.01546 0.0020 0.1349 0.8150
11.000 1.0791 0.02292 0.01663 0.0039 0.1203 0.8166
11.250 1.0837 0.02422 0.01788 0.0057 0.1060 0.8183
11.500 1.0887 0.02556 0.01917 0.0073 0.0932 0.8199
11.750 1.0934 0.02696 0.02054 0.0088 0.0814 0.8214
12.000 1.0984 0.02841 0.02196 0.0102 0.0711 0.8228
12.250 1.1026 0.02990 0.02344 0.0116 0.0616 0.8245
12.500 1.1065 0.03146 0.02501 0.0129 0.0541 0.8261
12.750 1.1100 0.03313 0.02667 0.0141 0.0464 0.8278
13.000 1.1155 0.03472 0.02828 0.0150 0.0412 0.8296
13.250 1.1206 0.03638 0.02998 0.0159 0.0359 0.8316
13.500 1.1251 0.03817 0.03177 0.0167 0.0317 0.8337
13.750 1.1302 0.03996 0.03358 0.0173 0.0280 0.8358
14.000 1.1358 0.04178 0.03546 0.0178 0.0255 0.8377
14.250 1.1395 0.04377 0.03748 0.0182 0.0228 0.8396
14.500 1.1454 0.04560 0.03939 0.0186 0.0206 0.8417
14.750 1.1480 0.04781 0.04165 0.0190 0.0187 0.8438
15.000 1.1542 0.04974 0.04367 0.0191 0.0167 0.8462
15.250 1.1564 0.05213 0.04614 0.0192 0.0155 0.8486
15.500 1.1598 0.05449 0.04857 0.0192 0.0139 0.8510
15.750 1.1621 0.05705 0.05118 0.0190 0.0125 0.8534
16.000 1.1619 0.05988 0.05412 0.0188 0.0114 0.8560
16.250 1.1645 0.06246 0.05680 0.0185 0.0102 0.8589
16.500 1.1604 0.06596 0.06039 0.0180 0.0093 0.8617
16.750 1.1618 0.06889 0.06344 0.0174 0.0082 0.8650
17.000 1.1595 0.07239 0.06702 0.0165 0.0071 0.8683
17.250 1.1583 0.07578 0.07054 0.0156 0.0065 0.8718
17.500 1.1543 0.07964 0.07453 0.0145 0.0060 0.8758
17.750 1.1484 0.08392 0.07894 0.0132 0.0059 0.8803
18.250 1.1353 0.09288 0.08818 0.0100 0.0053 0.8918
18.750 1.1203 0.10239 0.09804 0.0063 0.0047 0.9136
19.000 1.1175 0.10742 0.10326 0.0032 0.0044 0.9420
19.250 1.1075 0.11323 0.10919 -0.0001 0.0042 1.0000
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