EPPLER 544 AIRFOIL (e544-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 544 AIRFOIL (e544-il) Reynolds number: 200,000 Max Cl/Cd: 61.74 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e544-il-200000-n5.txt Download as CSV file: xf-e544-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 544 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
------ -------- --------- --------- -------- -------- --------
-13.750 -0.5013 0.09507 0.09127 -0.0614 1.0000 0.0076
-13.500 -0.5232 0.08530 0.08140 -0.0673 1.0000 0.0075
-13.250 -0.5473 0.07718 0.07315 -0.0719 1.0000 0.0074
-13.000 -0.5760 0.06993 0.06572 -0.0749 1.0000 0.0074
-12.750 -0.5949 0.06517 0.06082 -0.0760 1.0000 0.0073
-12.500 -0.6200 0.06008 0.05554 -0.0761 1.0000 0.0074
-12.250 -0.6372 0.05640 0.05169 -0.0754 1.0000 0.0073
-12.000 -0.6567 0.05268 0.04777 -0.0738 1.0000 0.0073
-11.750 -0.6728 0.04958 0.04447 -0.0717 1.0000 0.0073
-11.500 -0.6861 0.04705 0.04177 -0.0690 1.0000 0.0073
-10.750 -0.6732 0.03735 0.03103 -0.0691 0.9709 0.0075
-10.500 -0.6537 0.03484 0.02816 -0.0699 0.9599 0.0077
-10.250 -0.6281 0.03273 0.02581 -0.0715 0.9508 0.0079
-10.000 -0.5976 0.03098 0.02390 -0.0740 0.9433 0.0082
-9.750 -0.5662 0.02948 0.02225 -0.0763 0.9342 0.0085
-9.500 -0.5315 0.02799 0.02059 -0.0789 0.9260 0.0090
-9.250 -0.4977 0.02673 0.01914 -0.0812 0.9153 0.0098
-9.000 -0.4653 0.02561 0.01791 -0.0836 0.9038 0.0108
-8.750 -0.4343 0.02461 0.01680 -0.0855 0.8917 0.0118
-8.500 -0.4064 0.02370 0.01571 -0.0866 0.8792 0.0130
-8.250 -0.3862 0.02274 0.01470 -0.0866 0.8663 0.0137
-8.000 -0.3675 0.02194 0.01380 -0.0861 0.8544 0.0147
-7.750 -0.3504 0.02118 0.01290 -0.0851 0.8433 0.0163
-7.500 -0.3350 0.02050 0.01216 -0.0839 0.8322 0.0183
-7.250 -0.3202 0.01988 0.01149 -0.0824 0.8221 0.0214
-7.000 -0.3060 0.01924 0.01078 -0.0808 0.8132 0.0262
-6.750 -0.2943 0.01859 0.01012 -0.0788 0.8039 0.0332
-6.500 -0.2828 0.01794 0.00946 -0.0767 0.7963 0.0453
-6.250 -0.2746 0.01729 0.00889 -0.0741 0.7877 0.0642
-6.000 -0.2699 0.01666 0.00836 -0.0709 0.7804 0.0928
-5.750 -0.2661 0.01604 0.00791 -0.0674 0.7722 0.1315
-5.250 -0.2651 0.01414 0.00672 -0.0597 0.7585 0.2905
-5.000 -0.2709 0.01275 0.00606 -0.0549 0.7521 0.4424
-4.750 -0.2531 0.01309 0.00710 -0.0519 0.7473 0.6002
-4.500 -0.2297 0.01325 0.00714 -0.0511 0.7413 0.6304
-4.250 -0.2032 0.01359 0.00733 -0.0506 0.7362 0.6478
-4.000 -0.1761 0.01407 0.00768 -0.0500 0.7316 0.6634
-3.750 -0.1497 0.01471 0.00827 -0.0491 0.7262 0.6782
-3.500 -0.1212 0.01554 0.00904 -0.0482 0.7216 0.6913
-3.250 -0.0907 0.01613 0.00954 -0.0479 0.7177 0.6966
-3.000 -0.0642 0.01615 0.00948 -0.0477 0.7130 0.6991
-2.750 -0.0389 0.01605 0.00928 -0.0475 0.7080 0.7018
-2.500 -0.0135 0.01586 0.00896 -0.0475 0.7038 0.7050
-2.250 0.0115 0.01555 0.00848 -0.0478 0.7002 0.7088
-2.000 0.0377 0.01550 0.00838 -0.0477 0.6956 0.7099
-1.750 0.0643 0.01545 0.00827 -0.0477 0.6913 0.7110
-1.500 0.0916 0.01541 0.00815 -0.0478 0.6875 0.7123
-1.250 0.1190 0.01535 0.00801 -0.0480 0.6840 0.7137
-1.000 0.1449 0.01528 0.00790 -0.0480 0.6797 0.7150
-0.750 0.1713 0.01522 0.00779 -0.0480 0.6757 0.7168
-0.500 0.1984 0.01514 0.00764 -0.0483 0.6720 0.7186
0.000 0.2521 0.01495 0.00734 -0.0488 0.6647 0.7220
0.250 0.2787 0.01486 0.00720 -0.0491 0.6608 0.7241
0.500 0.3059 0.01482 0.00712 -0.0493 0.6571 0.7254
0.750 0.3339 0.01481 0.00708 -0.0496 0.6540 0.7263
1.000 0.3605 0.01481 0.00709 -0.0497 0.6503 0.7272
1.250 0.3866 0.01481 0.00711 -0.0497 0.6462 0.7282
1.500 0.4136 0.01481 0.00711 -0.0498 0.6423 0.7293
1.750 0.4414 0.01481 0.00709 -0.0501 0.6390 0.7304
2.000 0.4685 0.01483 0.00711 -0.0503 0.6353 0.7317
2.250 0.4940 0.01485 0.00717 -0.0502 0.6306 0.7333
2.500 0.5207 0.01485 0.00718 -0.0503 0.6262 0.7349
2.750 0.5490 0.01485 0.00715 -0.0507 0.6222 0.7364
3.000 0.5745 0.01486 0.00720 -0.0506 0.6170 0.7378
3.250 0.6006 0.01486 0.00722 -0.0507 0.6118 0.7393
3.500 0.6285 0.01486 0.00721 -0.0511 0.6073 0.7407
3.750 0.6540 0.01490 0.00730 -0.0509 0.6023 0.7416
4.000 0.6786 0.01493 0.00741 -0.0505 0.5963 0.7426
4.250 0.7055 0.01495 0.00745 -0.0506 0.5910 0.7437
4.500 0.7295 0.01501 0.00759 -0.0501 0.5846 0.7450
4.750 0.7542 0.01505 0.00769 -0.0497 0.5781 0.7465
5.000 0.7800 0.01509 0.00778 -0.0496 0.5720 0.7480
5.250 0.8031 0.01514 0.00792 -0.0490 0.5640 0.7495
5.500 0.8284 0.01518 0.00797 -0.0488 0.5569 0.7510
5.750 0.8509 0.01523 0.00812 -0.0481 0.5477 0.7526
6.000 0.8744 0.01529 0.00823 -0.0475 0.5388 0.7542
6.250 0.8972 0.01535 0.00832 -0.0469 0.5287 0.7558
6.500 0.9179 0.01543 0.00850 -0.0458 0.5171 0.7572
6.750 0.9378 0.01552 0.00866 -0.0446 0.5047 0.7584
7.000 0.9562 0.01564 0.00883 -0.0430 0.4898 0.7599
7.250 0.9729 0.01579 0.00903 -0.0412 0.4723 0.7616
7.500 0.9872 0.01599 0.00922 -0.0389 0.4517 0.7635
7.750 0.9973 0.01624 0.00945 -0.0359 0.4287 0.7656
8.250 1.0103 0.01718 0.01021 -0.0291 0.3774 0.7698
8.500 1.0148 0.01787 0.01081 -0.0257 0.3513 0.7719
9.000 1.0208 0.01951 0.01232 -0.0190 0.3032 0.7756
9.250 1.0227 0.02049 0.01324 -0.0158 0.2808 0.7777
9.500 1.0256 0.02154 0.01424 -0.0131 0.2581 0.7799
9.750 1.0280 0.02269 0.01534 -0.0105 0.2374 0.7823
10.000 1.0307 0.02394 0.01655 -0.0081 0.2175 0.7851
10.250 1.0345 0.02522 0.01778 -0.0061 0.1985 0.7878
10.500 1.0376 0.02655 0.01910 -0.0041 0.1807 0.7902
10.750 1.0408 0.02796 0.02049 -0.0023 0.1641 0.7925
11.000 1.0446 0.02941 0.02193 -0.0006 0.1488 0.7951
11.250 1.0484 0.03094 0.02344 0.0009 0.1340 0.7978
11.500 1.0530 0.03248 0.02499 0.0021 0.1208 0.8007
11.750 1.0578 0.03407 0.02658 0.0032 0.1085 0.8036
12.000 1.0623 0.03569 0.02822 0.0044 0.0975 0.8062
12.250 1.0667 0.03737 0.02993 0.0054 0.0878 0.8090
12.500 1.0705 0.03918 0.03176 0.0063 0.0790 0.8122
12.750 1.0761 0.04093 0.03356 0.0070 0.0706 0.8156
13.000 1.0812 0.04281 0.03548 0.0075 0.0635 0.8194
13.250 1.0842 0.04488 0.03759 0.0081 0.0569 0.8230
13.500 1.0897 0.04679 0.03959 0.0086 0.0511 0.8272
13.750 1.0931 0.04897 0.04182 0.0089 0.0460 0.8319
14.000 1.0972 0.05115 0.04407 0.0091 0.0415 0.8366
14.250 1.1001 0.05347 0.04648 0.0093 0.0380 0.8418
14.500 1.1035 0.05581 0.04892 0.0094 0.0344 0.8476
14.750 1.1050 0.05842 0.05162 0.0094 0.0318 0.8539
15.000 1.1078 0.06091 0.05425 0.0093 0.0291 0.8617
15.250 1.1080 0.06375 0.05719 0.0092 0.0270 0.8711
15.500 1.1095 0.06648 0.06008 0.0090 0.0249 0.8844
15.750 1.1108 0.06935 0.06313 0.0085 0.0229 0.9098
16.250 1.1085 0.07584 0.06987 0.0067 0.0201 1.0000
16.500 1.1085 0.07928 0.07341 0.0057 0.0188 1.0000
16.750 1.1049 0.08330 0.07749 0.0043 0.0176 1.0000
17.000 1.1040 0.08701 0.08133 0.0031 0.0164 1.0000
17.250 1.1014 0.09103 0.08548 0.0016 0.0155 1.0000
17.500 1.0982 0.09527 0.08980 -0.0002 0.0145 1.0000
17.750 1.0920 0.10001 0.09464 -0.0021 0.0141 1.0000
18.000 1.0885 0.10442 0.09920 -0.0040 0.0132 1.0000
18.250 1.0845 0.10900 0.10391 -0.0061 0.0125 1.0000
18.500 1.0794 0.11384 0.10887 -0.0085 0.0118 1.0000
18.750 1.0732 0.11895 0.11407 -0.0111 0.0115 1.0000
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Polar data table (+)
Polar graphs
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