EPPLER 547 AIRFOIL (e547-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 547 AIRFOIL (e547-il) Reynolds number: 100,000 Max Cl/Cd: 40.96 at α=9.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e547-il-100000-n5.txt Download as CSV file: xf-e547-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.4640 0.09321 0.08803 -0.0603 1.0000 0.0176
-12.500 -0.4872 0.08490 0.07968 -0.0651 1.0000 0.0172
-12.250 -0.5131 0.07791 0.07259 -0.0685 1.0000 0.0171
-12.000 -0.5334 0.07278 0.06736 -0.0701 1.0000 0.0165
-11.750 -0.5576 0.06787 0.06231 -0.0707 1.0000 0.0164
-11.500 -0.5811 0.06364 0.05792 -0.0702 1.0000 0.0165
-11.250 -0.6001 0.06027 0.05440 -0.0688 1.0000 0.0165
-11.000 -0.6193 0.05711 0.05108 -0.0667 1.0000 0.0164
-10.750 -0.6368 0.05450 0.04832 -0.0639 1.0000 0.0164
-10.500 -0.6542 0.05224 0.04591 -0.0603 1.0000 0.0164
-10.250 -0.6735 0.05058 0.04413 -0.0557 1.0000 0.0165
-10.000 -0.6897 0.04889 0.04226 -0.0516 0.9964 0.0170
-9.750 -0.6799 0.04543 0.03831 -0.0524 0.9822 0.0176
-9.500 -0.6631 0.04222 0.03462 -0.0530 0.9700 0.0178
-9.250 -0.6409 0.03931 0.03127 -0.0538 0.9595 0.0183
-9.000 -0.6125 0.03700 0.02879 -0.0553 0.9514 0.0189
-8.750 -0.5779 0.03480 0.02638 -0.0574 0.9450 0.0197
-8.500 -0.5383 0.03269 0.02405 -0.0599 0.9399 0.0208
-8.250 -0.4995 0.03093 0.02207 -0.0618 0.9330 0.0220
-8.000 -0.4624 0.02941 0.02049 -0.0642 0.9267 0.0245
-7.750 -0.4313 0.02826 0.01922 -0.0653 0.9162 0.0277
-7.500 -0.4021 0.02695 0.01788 -0.0664 0.9064 0.0304
-7.250 -0.3735 0.02584 0.01663 -0.0673 0.8962 0.0350
-7.000 -0.3528 0.02484 0.01562 -0.0670 0.8837 0.0418
-6.750 -0.3337 0.02389 0.01465 -0.0662 0.8715 0.0509
-6.500 -0.3159 0.02298 0.01379 -0.0651 0.8603 0.0676
-6.250 -0.3001 0.02207 0.01308 -0.0637 0.8495 0.1010
-6.000 -0.2920 0.02123 0.01253 -0.0610 0.8374 0.1542
-5.750 -0.2930 0.02016 0.01191 -0.0572 0.8258 0.2374
-5.500 -0.3032 0.01877 0.01119 -0.0519 0.8148 0.3597
-5.250 -0.2687 0.02072 0.01428 -0.0484 0.8070 0.5936
-5.000 -0.2607 0.02073 0.01409 -0.0452 0.7976 0.6284
-4.750 -0.2476 0.02099 0.01413 -0.0425 0.7884 0.6537
-4.500 -0.2188 0.02201 0.01497 -0.0411 0.7804 0.6714
-4.250 -0.1873 0.02305 0.01583 -0.0399 0.7729 0.6874
-4.000 -0.1483 0.02455 0.01716 -0.0392 0.7659 0.7041
-3.750 -0.1187 0.02522 0.01767 -0.0382 0.7583 0.7172
-3.500 -0.0887 0.02532 0.01760 -0.0382 0.7513 0.7218
-3.250 -0.0806 0.02484 0.01698 -0.0357 0.7430 0.7305
-3.000 -0.0506 0.02480 0.01677 -0.0358 0.7364 0.7328
-2.750 -0.0260 0.02470 0.01654 -0.0354 0.7288 0.7358
-2.500 -0.0040 0.02442 0.01610 -0.0347 0.7229 0.7402
-2.250 0.0057 0.02399 0.01557 -0.0325 0.7148 0.7462
-2.000 0.0339 0.02386 0.01530 -0.0326 0.7090 0.7481
-1.750 0.0569 0.02375 0.01512 -0.0319 0.7018 0.7506
-1.500 0.0794 0.02355 0.01480 -0.0314 0.6956 0.7536
-1.250 0.0977 0.02324 0.01438 -0.0304 0.6897 0.7577
-1.000 0.1139 0.02291 0.01398 -0.0292 0.6828 0.7616
-0.750 0.1414 0.02278 0.01374 -0.0292 0.6777 0.7631
-0.500 0.1636 0.02270 0.01362 -0.0285 0.6711 0.7650
-0.250 0.1873 0.02257 0.01342 -0.0282 0.6653 0.7671
0.000 0.2122 0.02240 0.01315 -0.0280 0.6605 0.7695
0.250 0.2309 0.02225 0.01299 -0.0271 0.6537 0.7723
0.500 0.2534 0.02202 0.01267 -0.0269 0.6486 0.7751
0.750 0.2774 0.02191 0.01251 -0.0267 0.6436 0.7773
1.000 0.3000 0.02190 0.01250 -0.0261 0.6374 0.7788
1.250 0.3261 0.02181 0.01237 -0.0261 0.6326 0.7802
1.500 0.3502 0.02178 0.01232 -0.0259 0.6275 0.7819
1.750 0.3726 0.02177 0.01233 -0.0254 0.6217 0.7839
2.000 0.3985 0.02171 0.01222 -0.0255 0.6171 0.7862
2.250 0.4225 0.02168 0.01218 -0.0254 0.6121 0.7885
2.500 0.4449 0.02168 0.01220 -0.0251 0.6063 0.7906
2.750 0.4716 0.02163 0.01214 -0.0254 0.6019 0.7922
3.000 0.4964 0.02168 0.01220 -0.0252 0.5971 0.7936
3.250 0.5181 0.02179 0.01237 -0.0245 0.5912 0.7953
3.500 0.5444 0.02181 0.01242 -0.0246 0.5867 0.7972
3.750 0.5696 0.02187 0.01251 -0.0245 0.5820 0.7992
4.000 0.5908 0.02201 0.01272 -0.0239 0.5760 0.8014
4.250 0.6178 0.02203 0.01277 -0.0242 0.5713 0.8033
4.500 0.6432 0.02211 0.01288 -0.0244 0.5663 0.8054
4.750 0.6647 0.02227 0.01313 -0.0239 0.5600 0.8074
5.000 0.6917 0.02229 0.01320 -0.0239 0.5553 0.8089
5.250 0.7129 0.02247 0.01348 -0.0232 0.5493 0.8109
5.500 0.7349 0.02261 0.01371 -0.0225 0.5430 0.8132
5.750 0.7649 0.02257 0.01370 -0.0231 0.5382 0.8153
6.000 0.7808 0.02285 0.01413 -0.0216 0.5304 0.8180
6.250 0.8086 0.02285 0.01417 -0.0220 0.5244 0.8202
6.500 0.8281 0.02307 0.01452 -0.0211 0.5169 0.8227
6.750 0.8517 0.02310 0.01464 -0.0206 0.5100 0.8246
7.000 0.8709 0.02328 0.01495 -0.0195 0.5025 0.8269
7.250 0.8932 0.02335 0.01512 -0.0188 0.4949 0.8295
7.500 0.9112 0.02355 0.01545 -0.0176 0.4866 0.8326
7.750 0.9351 0.02358 0.01555 -0.0172 0.4784 0.8359
8.000 0.9485 0.02386 0.01598 -0.0153 0.4688 0.8391
8.250 0.9693 0.02389 0.01611 -0.0142 0.4599 0.8419
8.500 0.9822 0.02411 0.01647 -0.0122 0.4493 0.8453
8.750 0.9924 0.02438 0.01687 -0.0097 0.4385 0.8492
9.000 1.0050 0.02459 0.01717 -0.0077 0.4272 0.8532
9.250 1.0166 0.02482 0.01748 -0.0054 0.4153 0.8570
9.500 1.0240 0.02527 0.01806 -0.0028 0.4022 0.8620
9.750 1.0309 0.02586 0.01876 -0.0004 0.3880 0.8678
10.000 1.0355 0.02649 0.01950 0.0023 0.3733 0.8735
10.250 1.0405 0.02724 0.02031 0.0046 0.3572 0.8805
10.500 1.0432 0.02817 0.02132 0.0070 0.3400 0.8878
10.750 1.0452 0.02929 0.02250 0.0091 0.3216 0.8967
11.000 1.0468 0.03053 0.02377 0.0111 0.3025 0.9074
11.250 1.0491 0.03195 0.02521 0.0125 0.2833 0.9223
11.500 1.0531 0.03372 0.02703 0.0128 0.2623 0.9480
11.750 1.0530 0.03560 0.02887 0.0134 0.2438 1.0000
12.000 1.0529 0.03780 0.03101 0.0139 0.2261 1.0000
12.250 1.0522 0.04014 0.03329 0.0143 0.2096 1.0000
12.500 1.0512 0.04258 0.03569 0.0146 0.1941 1.0000
12.750 1.0501 0.04511 0.03820 0.0148 0.1794 1.0000
13.000 1.0487 0.04776 0.04082 0.0149 0.1657 1.0000
13.250 1.0477 0.05046 0.04353 0.0149 0.1527 1.0000
13.500 1.0470 0.05323 0.04632 0.0147 0.1406 1.0000
13.750 1.0463 0.05608 0.04918 0.0145 0.1292 1.0000
14.000 1.0452 0.05905 0.05216 0.0142 0.1188 1.0000
14.250 1.0432 0.06217 0.05526 0.0137 0.1099 1.0000
14.500 1.0427 0.06524 0.05838 0.0132 0.1008 1.0000
14.750 1.0422 0.06837 0.06155 0.0126 0.0929 1.0000
15.000 1.0395 0.07183 0.06500 0.0118 0.0861 1.0000
15.250 1.0403 0.07495 0.06822 0.0111 0.0793 1.0000
15.500 1.0370 0.07862 0.07189 0.0101 0.0739 1.0000
15.750 1.0380 0.08184 0.07522 0.0092 0.0682 1.0000
16.000 1.0354 0.08559 0.07900 0.0080 0.0636 1.0000
16.250 1.0344 0.08916 0.08266 0.0069 0.0591 1.0000
16.500 1.0336 0.09280 0.08640 0.0057 0.0551 1.0000
16.750 1.0310 0.09668 0.09029 0.0042 0.0520 1.0000
17.000 1.0311 0.10030 0.09403 0.0030 0.0485 1.0000
17.250 1.0291 0.10432 0.09816 0.0013 0.0453 1.0000
17.500 1.0266 0.10837 0.10224 -0.0004 0.0429 1.0000
17.750 1.0262 0.11217 0.10614 -0.0020 0.0404 1.0000
18.000 1.0241 0.11639 0.11051 -0.0039 0.0379 1.0000
18.250 1.0218 0.12065 0.11485 -0.0060 0.0359 1.0000
18.500 1.0204 0.12461 0.11881 -0.0080 0.0342 1.0000
18.750 1.0171 0.12925 0.12364 -0.0103 0.0324 1.0000
19.000 1.0135 0.13400 0.12856 -0.0128 0.0309 1.0000
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Polar data table (+)
Polar graphs
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