EPPLER 547 AIRFOIL (e547-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: EPPLER 547 AIRFOIL (e547-il) Reynolds number: 200,000 Max Cl/Cd: 61.56 at α=9.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e547-il-200000.txt Download as CSV file: xf-e547-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 547 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.3921 0.11631 0.11274 -0.0487 1.0000 0.0508
-12.250 -0.4280 0.10392 0.10045 -0.0600 1.0000 0.0533
-12.000 -0.4556 0.09618 0.09267 -0.0656 1.0000 0.0534
-9.250 -0.6519 0.04395 0.03835 -0.0577 0.9624 0.0292
-9.000 -0.6289 0.03798 0.03153 -0.0578 0.9574 0.0229
-8.750 -0.5984 0.03407 0.02741 -0.0594 0.9511 0.0223
-8.500 -0.5620 0.03079 0.02379 -0.0616 0.9467 0.0221
-8.250 -0.5192 0.02814 0.02083 -0.0645 0.9435 0.0221
-8.000 -0.4779 0.02622 0.01861 -0.0668 0.9375 0.0228
-7.750 -0.4283 0.02417 0.01665 -0.0707 0.9340 0.0252
-7.500 -0.3837 0.02302 0.01538 -0.0738 0.9282 0.0281
-7.250 -0.3472 0.02155 0.01397 -0.0753 0.9190 0.0306
-7.000 -0.3156 0.02051 0.01286 -0.0765 0.9082 0.0352
-6.750 -0.2962 0.01942 0.01179 -0.0760 0.8947 0.0419
-6.500 -0.2852 0.01846 0.01080 -0.0738 0.8804 0.0520
-6.250 -0.2843 0.01747 0.00989 -0.0699 0.8658 0.0712
-6.000 -0.2894 0.01657 0.00919 -0.0648 0.8519 0.1106
-5.500 -0.3076 0.01401 0.00777 -0.0540 0.8281 0.3332
-5.250 -0.3123 0.01339 0.00850 -0.0475 0.8186 0.5908
-5.000 -0.2913 0.01421 0.00921 -0.0453 0.8092 0.6494
-4.750 -0.2587 0.01567 0.01055 -0.0441 0.8022 0.6751
-4.500 -0.2284 0.01692 0.01171 -0.0427 0.7933 0.6899
-4.250 -0.1956 0.01795 0.01260 -0.0419 0.7867 0.7021
-4.000 -0.1714 0.01860 0.01314 -0.0404 0.7781 0.7145
-3.750 -0.1212 0.02036 0.01479 -0.0410 0.7720 0.7195
-3.500 -0.0895 0.02132 0.01566 -0.0400 0.7640 0.7318
-3.250 -0.0476 0.02268 0.01689 -0.0400 0.7572 0.7459
-3.000 0.0023 0.02328 0.01737 -0.0423 0.7505 0.7484
-2.750 0.0379 0.02335 0.01732 -0.0432 0.7432 0.7516
-2.500 0.0343 0.02277 0.01666 -0.0389 0.7359 0.7617
-2.250 0.0691 0.02276 0.01656 -0.0398 0.7285 0.7636
-2.000 0.1027 0.02271 0.01637 -0.0407 0.7228 0.7660
-1.750 0.1216 0.02249 0.01612 -0.0395 0.7151 0.7701
-1.500 0.1196 0.02179 0.01531 -0.0357 0.7092 0.7773
-1.250 0.1482 0.02170 0.01519 -0.0358 0.7022 0.7789
-1.000 0.1761 0.02156 0.01497 -0.0359 0.6959 0.7810
-0.750 0.1997 0.02138 0.01471 -0.0355 0.6905 0.7837
-0.500 0.2120 0.02102 0.01433 -0.0336 0.6837 0.7876
-0.250 0.2211 0.02041 0.01361 -0.0318 0.6785 0.7921
0.000 0.2462 0.02028 0.01348 -0.0314 0.6723 0.7935
0.250 0.2707 0.02012 0.01328 -0.0311 0.6664 0.7949
0.500 0.2977 0.01997 0.01304 -0.0313 0.6619 0.7965
0.750 0.3178 0.01982 0.01292 -0.0304 0.6556 0.7987
1.000 0.3400 0.01959 0.01264 -0.0301 0.6501 0.8005
1.250 0.3655 0.01938 0.01234 -0.0304 0.6460 0.8026
1.500 0.3834 0.01915 0.01215 -0.0297 0.6397 0.8052
1.750 0.4074 0.01888 0.01183 -0.0301 0.6345 0.8070
2.000 0.4362 0.01878 0.01165 -0.0306 0.6305 0.8080
2.250 0.4573 0.01875 0.01171 -0.0296 0.6244 0.8095
2.500 0.4828 0.01867 0.01163 -0.0296 0.6193 0.8109
2.750 0.5120 0.01860 0.01149 -0.0303 0.6153 0.8120
3.000 0.5336 0.01858 0.01155 -0.0297 0.6095 0.8134
3.250 0.5593 0.01851 0.01149 -0.0299 0.6042 0.8149
3.500 0.5890 0.01846 0.01139 -0.0307 0.6002 0.8166
3.750 0.6114 0.01847 0.01148 -0.0305 0.5942 0.8188
4.000 0.6382 0.01842 0.01144 -0.0310 0.5889 0.8204
4.250 0.6699 0.01837 0.01132 -0.0323 0.5845 0.8218
4.500 0.6913 0.01839 0.01146 -0.0317 0.5781 0.8232
4.750 0.7175 0.01834 0.01144 -0.0317 0.5726 0.8244
5.000 0.7461 0.01834 0.01143 -0.0321 0.5676 0.8257
5.250 0.7672 0.01838 0.01159 -0.0313 0.5607 0.8275
5.500 0.7959 0.01833 0.01154 -0.0317 0.5552 0.8294
5.750 0.8194 0.01839 0.01168 -0.0314 0.5486 0.8314
6.000 0.8458 0.01836 0.01169 -0.0316 0.5420 0.8332
6.250 0.8743 0.01837 0.01172 -0.0321 0.5360 0.8350
6.500 0.8979 0.01839 0.01183 -0.0320 0.5283 0.8369
6.750 0.9275 0.01833 0.01175 -0.0326 0.5220 0.8385
7.000 0.9461 0.01833 0.01192 -0.0312 0.5135 0.8403
7.250 0.9734 0.01829 0.01187 -0.0312 0.5063 0.8422
7.500 0.9925 0.01828 0.01201 -0.0300 0.4971 0.8447
7.750 1.0161 0.01827 0.01206 -0.0295 0.4886 0.8474
8.000 1.0393 0.01823 0.01206 -0.0290 0.4790 0.8499
8.250 1.0593 0.01826 0.01221 -0.0281 0.4686 0.8525
8.500 1.0791 0.01823 0.01223 -0.0268 0.4584 0.8547
8.750 1.0975 0.01821 0.01228 -0.0253 0.4472 0.8572
9.000 1.1106 0.01825 0.01245 -0.0230 0.4344 0.8603
9.250 1.1241 0.01833 0.01261 -0.0208 0.4207 0.8637
9.500 1.1358 0.01845 0.01279 -0.0184 0.4058 0.8676
9.750 1.1402 0.01857 0.01297 -0.0145 0.3904 0.8716
10.000 1.1448 0.01888 0.01331 -0.0110 0.3732 0.8763
10.250 1.1488 0.01937 0.01382 -0.0077 0.3534 0.8814
10.500 1.1494 0.01999 0.01445 -0.0041 0.3325 0.8866
10.750 1.1474 0.02084 0.01525 -0.0005 0.3113 0.8930
11.000 1.1453 0.02190 0.01628 0.0028 0.2887 0.9001
11.250 1.1404 0.02321 0.01753 0.0060 0.2680 0.9088
11.500 1.1368 0.02463 0.01895 0.0087 0.2468 0.9195
11.750 1.1336 0.02630 0.02060 0.0108 0.2270 0.9359
12.000 1.1374 0.02837 0.02268 0.0105 0.2048 0.9742
12.250 1.1373 0.03053 0.02479 0.0109 0.1864 1.0000
12.500 1.1364 0.03294 0.02714 0.0112 0.1693 1.0000
12.750 1.1348 0.03545 0.02959 0.0115 0.1539 1.0000
13.000 1.1326 0.03806 0.03214 0.0117 0.1396 1.0000
13.250 1.1312 0.04067 0.03471 0.0120 0.1269 1.0000
13.500 1.1295 0.04337 0.03738 0.0121 0.1149 1.0000
13.750 1.1274 0.04617 0.04017 0.0122 0.1041 1.0000
14.000 1.1241 0.04916 0.04311 0.0123 0.0947 1.0000
14.250 1.1205 0.05224 0.04615 0.0122 0.0863 1.0000
14.500 1.1208 0.05504 0.04901 0.0120 0.0781 1.0000
14.750 1.1173 0.05824 0.05215 0.0118 0.0717 1.0000
15.000 1.1177 0.06117 0.05514 0.0114 0.0654 1.0000
15.250 1.1156 0.06432 0.05829 0.0112 0.0603 1.0000
15.500 1.1169 0.06728 0.06134 0.0106 0.0555 1.0000
15.750 1.1148 0.07046 0.06443 0.0103 0.0512 1.0000
16.000 1.1169 0.07348 0.06761 0.0095 0.0475 1.0000
16.250 1.1165 0.07677 0.07092 0.0087 0.0442 1.0000
16.500 1.1179 0.07967 0.07383 0.0083 0.0411 1.0000
16.750 1.1186 0.08303 0.07733 0.0073 0.0383 1.0000
17.000 1.1179 0.08652 0.08085 0.0061 0.0358 1.0000
17.250 1.1188 0.08960 0.08394 0.0055 0.0331 1.0000
17.500 1.1183 0.09329 0.08779 0.0041 0.0310 1.0000
17.750 1.1172 0.09703 0.09158 0.0026 0.0291 1.0000
18.000 1.1202 0.09977 0.09429 0.0021 0.0269 1.0000
18.250 1.1171 0.10403 0.09876 0.0004 0.0255 1.0000
18.500 1.1154 0.10802 0.10287 -0.0014 0.0240 1.0000
18.750 1.1152 0.11171 0.10658 -0.0031 0.0227 1.0000
19.000 1.1169 0.11481 0.10970 -0.0041 0.0213 1.0000
19.250 1.1093 0.12012 0.11523 -0.0068 0.0203 1.0000
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Polar data table (+)
Polar graphs
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