EPPLER 543 AIRFOIL (e543-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: EPPLER 543 AIRFOIL (e543-il) Reynolds number: 100,000 Max Cl/Cd: 42.32 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e543-il-100000.txt Download as CSV file: xf-e543-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.3790 0.12683 0.12183 -0.0485 1.0000 0.1079
-12.250 -0.3906 0.12288 0.11796 -0.0511 1.0000 0.1135
-12.000 -0.4492 0.11644 0.11172 -0.0608 1.0000 0.1155
-11.750 -0.3937 0.11471 0.10991 -0.0525 1.0000 0.1191
-11.500 -0.3887 0.11163 0.10687 -0.0521 1.0000 0.1230
-11.250 -0.4413 0.10504 0.10046 -0.0600 1.0000 0.1298
-11.000 -0.4265 0.10146 0.09692 -0.0574 1.0000 0.1327
-10.750 -0.4126 0.09925 0.09473 -0.0551 1.0000 0.1361
-10.500 -0.4317 0.09469 0.09028 -0.0570 1.0000 0.1423
-10.250 -0.5073 0.08916 0.08489 -0.0603 1.0000 0.1447
-10.000 -0.5508 0.08756 0.08340 -0.0563 1.0000 0.1448
-9.750 -0.5857 0.08684 0.08278 -0.0506 1.0000 0.1446
-9.500 -0.6201 0.08619 0.08222 -0.0451 1.0000 0.1444
-9.250 -0.6511 0.08521 0.08130 -0.0400 1.0000 0.1441
-8.000 -0.6786 0.05029 0.04340 -0.0402 0.9522 0.0519
-7.750 -0.6578 0.04606 0.03877 -0.0402 0.9458 0.0484
-7.500 -0.6384 0.04283 0.03460 -0.0386 0.9389 0.0446
-7.250 -0.6127 0.04017 0.03156 -0.0385 0.9321 0.0446
-7.000 -0.5723 0.03712 0.02836 -0.0413 0.9288 0.0471
-6.750 -0.5244 0.03485 0.02589 -0.0448 0.9266 0.0499
-6.500 -0.4989 0.03343 0.02427 -0.0439 0.9188 0.0518
-6.250 -0.4452 0.03127 0.02215 -0.0478 0.9168 0.0585
-6.000 -0.3953 0.02948 0.02047 -0.0513 0.9144 0.0721
-5.750 -0.3569 0.02757 0.01886 -0.0533 0.9116 0.1038
-5.500 -0.3614 0.02683 0.01843 -0.0481 0.9006 0.1381
-5.250 -0.3770 0.02409 0.01733 -0.0423 0.8939 0.3498
-5.000 -0.2286 0.03545 0.02959 -0.0436 0.8996 0.7417
-4.750 -0.0519 0.03762 0.03110 -0.0627 0.9117 0.7818
-4.500 0.0323 0.03778 0.03098 -0.0703 0.9115 0.8187
-3.750 0.2908 0.03270 0.02524 -0.1010 0.9085 0.9618
-3.500 0.3386 0.03126 0.02368 -0.1068 0.9017 0.9794
-3.250 0.3933 0.02949 0.02177 -0.1141 0.8969 0.9926
-3.000 0.4370 0.02805 0.02023 -0.1192 0.8898 1.0000
-2.750 0.4607 0.02767 0.01978 -0.1199 0.8817 1.0000
-2.500 0.4820 0.02745 0.01950 -0.1202 0.8743 1.0000
-2.250 0.5012 0.02731 0.01931 -0.1200 0.8662 1.0000
-2.000 0.5229 0.02712 0.01906 -0.1201 0.8596 1.0000
-1.750 0.5375 0.02722 0.01914 -0.1189 0.8514 1.0000
-1.500 0.5609 0.02702 0.01889 -0.1192 0.8461 1.0000
-1.250 0.5724 0.02732 0.01920 -0.1175 0.8379 1.0000
-1.000 0.5921 0.02728 0.01913 -0.1170 0.8319 1.0000
-0.750 0.6086 0.02745 0.01930 -0.1161 0.8259 1.0000
-0.500 0.6225 0.02772 0.01958 -0.1147 0.8186 1.0000
-0.250 0.6443 0.02766 0.01950 -0.1144 0.8139 1.0000
0.000 0.6535 0.02824 0.02013 -0.1123 0.8066 1.0000
0.250 0.6707 0.02841 0.02031 -0.1113 0.8007 1.0000
0.500 0.6943 0.02832 0.02021 -0.1112 0.7965 1.0000
0.750 0.6971 0.02925 0.02122 -0.1081 0.7879 1.0000
1.000 0.7178 0.02928 0.02126 -0.1075 0.7828 1.0000
1.250 0.7297 0.02980 0.02183 -0.1056 0.7765 1.0000
1.500 0.7399 0.03035 0.02244 -0.1035 0.7691 1.0000
1.750 0.7658 0.03012 0.02223 -0.1035 0.7649 1.0000
2.000 0.7637 0.03134 0.02354 -0.0995 0.7556 1.0000
2.250 0.7862 0.03124 0.02347 -0.0990 0.7504 1.0000
2.500 0.7932 0.03199 0.02429 -0.0962 0.7427 1.0000
2.750 0.8069 0.03232 0.02469 -0.0943 0.7356 1.0000
3.000 0.8399 0.03167 0.02407 -0.0951 0.7319 1.0000
3.250 0.8290 0.03325 0.02576 -0.0898 0.7206 1.0000
3.500 0.8635 0.03246 0.02502 -0.0907 0.7164 1.0000
3.750 0.7873 0.03576 0.02832 -0.0731 0.7039 0.9869
4.000 0.8337 0.03453 0.02717 -0.0758 0.7004 0.9878
4.250 0.7624 0.03750 0.03015 -0.0598 0.6872 0.9791
4.500 0.8201 0.03583 0.02855 -0.0641 0.6842 0.9805
4.750 0.7725 0.03807 0.03084 -0.0526 0.6709 0.9771
5.000 0.8394 0.03601 0.02887 -0.0581 0.6682 0.9783
5.250 0.7800 0.03841 0.03129 -0.0447 0.6545 0.9748
5.500 0.8065 0.03788 0.03086 -0.0442 0.6474 0.9753
5.750 0.8190 0.03765 0.03072 -0.0415 0.6386 0.9754
6.000 0.9162 0.03434 0.02757 -0.0512 0.6359 0.9773
6.250 0.8657 0.03627 0.02954 -0.0391 0.6228 0.9752
6.500 0.8397 0.03727 0.03058 -0.0308 0.6110 0.9750
6.750 0.9445 0.03359 0.02711 -0.0411 0.6064 0.9762
7.000 0.9475 0.03360 0.02722 -0.0370 0.5953 0.9771
7.250 1.0439 0.03013 0.02388 -0.0464 0.5875 0.9784
7.500 1.0364 0.03031 0.02419 -0.0404 0.5744 0.9787
7.750 1.0408 0.03002 0.02401 -0.0361 0.5619 0.9791
8.000 1.0604 0.02914 0.02322 -0.0340 0.5485 0.9797
8.250 1.0776 0.02830 0.02246 -0.0316 0.5338 0.9805
8.500 1.0873 0.02768 0.02194 -0.0280 0.5179 0.9820
8.750 1.1007 0.02706 0.02141 -0.0253 0.4987 0.9839
9.000 1.1163 0.02638 0.02076 -0.0228 0.4773 0.9857
9.250 1.1043 0.02642 0.02085 -0.0163 0.4581 0.9881
9.500 1.0985 0.02639 0.02081 -0.0108 0.4359 0.9908
9.750 1.0959 0.02656 0.02093 -0.0063 0.4107 0.9938
10.000 1.0974 0.02704 0.02130 -0.0030 0.3805 0.9976
10.250 1.0918 0.02772 0.02181 0.0012 0.3542 1.0000
10.500 1.0716 0.02840 0.02242 0.0079 0.3365 1.0000
10.750 1.0515 0.02907 0.02300 0.0143 0.3200 1.0000
11.000 1.0316 0.02969 0.02353 0.0206 0.3044 1.0000
11.250 1.0137 0.03038 0.02412 0.0262 0.2884 1.0000
11.500 1.0046 0.03154 0.02520 0.0296 0.2677 1.0000
11.750 1.0024 0.03303 0.02651 0.0315 0.2448 1.0000
12.000 1.0003 0.03487 0.02829 0.0329 0.2219 1.0000
12.250 1.0017 0.03673 0.02994 0.0339 0.2002 1.0000
12.500 1.0018 0.03886 0.03205 0.0345 0.1798 1.0000
12.750 1.0035 0.04101 0.03412 0.0350 0.1611 1.0000
13.000 1.0072 0.04313 0.03613 0.0354 0.1445 1.0000
13.250 1.0128 0.04525 0.03811 0.0356 0.1290 1.0000
13.500 1.0194 0.04740 0.04022 0.0358 0.1155 1.0000
13.750 1.0251 0.04968 0.04254 0.0358 0.1040 1.0000
14.000 1.0337 0.05192 0.04483 0.0359 0.0938 1.0000
14.250 1.0448 0.05411 0.04703 0.0360 0.0846 1.0000
14.500 1.0604 0.05609 0.04888 0.0359 0.0760 1.0000
14.750 1.0610 0.05893 0.05200 0.0358 0.0707 1.0000
15.000 1.0757 0.06120 0.05421 0.0357 0.0643 1.0000
15.250 1.0745 0.06434 0.05763 0.0355 0.0604 1.0000
15.500 1.0887 0.06681 0.05999 0.0352 0.0551 1.0000
15.750 1.0799 0.07069 0.06423 0.0348 0.0528 1.0000
16.000 1.0771 0.07420 0.06793 0.0343 0.0501 1.0000
16.250 1.0869 0.07716 0.07084 0.0338 0.0465 1.0000
16.500 1.0689 0.08216 0.07620 0.0327 0.0456 1.0000
16.750 1.0523 0.08752 0.08188 0.0311 0.0448 1.0000
17.000 1.0342 0.09336 0.08801 0.0291 0.0443 1.0000
17.250 1.0144 0.09969 0.09460 0.0265 0.0442 1.0000
17.500 0.9905 0.10695 0.10211 0.0231 0.0442 1.0000
17.750 0.9647 0.11502 0.11041 0.0188 0.0445 1.0000
18.000 0.9384 0.12376 0.11935 0.0137 0.0452 1.0000
18.250 0.9139 0.13284 0.12857 0.0083 0.0460 1.0000
18.500 0.8877 0.14302 0.13885 0.0021 0.0466 1.0000
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Polar data table (+)
Polar graphs
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