EPPLER 604 AIRFOIL (e604-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 604 AIRFOIL (e604-il) Reynolds number: 50,000 Max Cl/Cd: 13.75 at α=14.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e604-il-50000-n5.txt Download as CSV file: xf-e604-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 604 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.4257 0.09545 0.08888 -0.0812 0.9832 0.0413
-11.500 -0.4418 0.08834 0.08166 -0.0866 0.9756 0.0411
-11.250 -0.4584 0.08194 0.07511 -0.0916 0.9687 0.0409
-11.000 -0.4763 0.07657 0.06954 -0.0949 0.9600 0.0407
-10.750 -0.4939 0.07202 0.06475 -0.0969 0.9510 0.0407
-10.500 -0.5070 0.06783 0.06027 -0.0987 0.9434 0.0408
-10.250 -0.5229 0.06496 0.05714 -0.0977 0.9330 0.0408
-10.000 -0.5388 0.06202 0.05384 -0.0964 0.9242 0.0413
-9.750 -0.5392 0.05969 0.05134 -0.0955 0.9161 0.0421
-9.500 -0.5237 0.05735 0.04885 -0.0966 0.9116 0.0438
-9.250 -0.5290 0.05572 0.04703 -0.0936 0.9021 0.0449
-9.000 -0.5175 0.05303 0.04392 -0.0935 0.8970 0.0469
-8.750 -0.5144 0.05104 0.04153 -0.0911 0.8898 0.0483
-8.500 -0.4976 0.04911 0.03941 -0.0904 0.8845 0.0505
-8.250 -0.4715 0.04738 0.03751 -0.0912 0.8809 0.0545
-8.000 -0.4445 0.04563 0.03545 -0.0912 0.8771 0.0592
-7.750 -0.4340 0.04489 0.03470 -0.0889 0.8703 0.0631
-7.500 -0.3980 0.04365 0.03330 -0.0897 0.8674 0.0705
-7.250 -0.3597 0.04258 0.03211 -0.0907 0.8650 0.0815
-7.000 -0.3253 0.04149 0.03100 -0.0916 0.8627 0.0948
-6.750 -0.3343 0.04136 0.03092 -0.0864 0.8537 0.1004
-6.500 -0.3179 0.04047 0.03006 -0.0851 0.8494 0.1155
-6.250 -0.2992 0.03936 0.02901 -0.0846 0.8461 0.1377
-6.000 -0.3174 0.03929 0.02903 -0.0781 0.8368 0.1453
-5.750 -0.3105 0.03817 0.02812 -0.0761 0.8321 0.1745
-5.500 -0.3112 0.03712 0.02736 -0.0731 0.8269 0.2135
-5.250 -0.3229 0.03639 0.02699 -0.0683 0.8195 0.2566
-5.000 -0.3195 0.03550 0.02736 -0.0641 0.8154 0.4030
-4.750 -0.2876 0.03790 0.03007 -0.0600 0.8129 0.5559
-4.500 -0.3003 0.03845 0.03052 -0.0542 0.8047 0.5852
-4.250 -0.2856 0.03926 0.03104 -0.0517 0.8002 0.6232
-4.000 -0.2584 0.04069 0.03223 -0.0492 0.7972 0.6511
-3.750 -0.2583 0.04164 0.03306 -0.0442 0.7908 0.6700
-3.500 -0.2477 0.04249 0.03374 -0.0406 0.7858 0.6917
-3.250 -0.2221 0.04378 0.03485 -0.0375 0.7826 0.7124
-3.000 -0.1918 0.04459 0.03544 -0.0359 0.7801 0.7317
-2.750 -0.2022 0.04506 0.03586 -0.0303 0.7727 0.7446
-2.500 -0.1890 0.04519 0.03581 -0.0282 0.7682 0.7580
-2.250 -0.1587 0.04537 0.03578 -0.0280 0.7653 0.7658
-2.000 -0.1548 0.04536 0.03564 -0.0253 0.7600 0.7755
-1.750 -0.1452 0.04558 0.03575 -0.0228 0.7543 0.7818
-1.500 -0.1279 0.04540 0.03539 -0.0221 0.7504 0.7896
-1.250 -0.0988 0.04528 0.03508 -0.0227 0.7476 0.7943
-1.000 -0.1013 0.04558 0.03533 -0.0191 0.7405 0.8001
-0.750 -0.0867 0.04552 0.03513 -0.0184 0.7358 0.8060
-0.500 -0.0600 0.04545 0.03490 -0.0189 0.7325 0.8096
-0.250 -0.0467 0.04564 0.03499 -0.0176 0.7275 0.8137
0.000 -0.0373 0.04586 0.03513 -0.0161 0.7214 0.8184
0.250 -0.0133 0.04586 0.03499 -0.0168 0.7175 0.8226
0.500 0.0173 0.04583 0.03483 -0.0178 0.7147 0.8254
0.750 0.0171 0.04639 0.03538 -0.0150 0.7068 0.8296
1.000 0.0394 0.04656 0.03546 -0.0153 0.7024 0.8332
1.250 0.0695 0.04661 0.03538 -0.0166 0.6992 0.8365
1.500 0.0763 0.04719 0.03593 -0.0151 0.6921 0.8405
1.750 0.0960 0.04750 0.03619 -0.0149 0.6870 0.8438
2.000 0.1252 0.04764 0.03625 -0.0159 0.6835 0.8470
2.250 0.1369 0.04826 0.03684 -0.0151 0.6768 0.8507
2.500 0.1572 0.04873 0.03726 -0.0155 0.6711 0.8546
2.750 0.1856 0.04888 0.03737 -0.0162 0.6675 0.8577
3.000 0.1966 0.04959 0.03808 -0.0152 0.6606 0.8616
3.250 0.2169 0.05010 0.03857 -0.0154 0.6547 0.8651
3.500 0.2483 0.05033 0.03877 -0.0168 0.6511 0.8686
3.750 0.2567 0.05123 0.03969 -0.0158 0.6431 0.8727
4.000 0.2790 0.05166 0.04013 -0.0159 0.6377 0.8767
4.250 0.3112 0.05181 0.04027 -0.0171 0.6342 0.8807
4.500 0.3164 0.05303 0.04153 -0.0162 0.6248 0.8854
4.750 0.3435 0.05333 0.04184 -0.0168 0.6202 0.8891
5.000 0.3603 0.05405 0.04260 -0.0166 0.6134 0.8936
5.250 0.3781 0.05480 0.04341 -0.0167 0.6063 0.8988
5.500 0.4104 0.05487 0.04351 -0.0177 0.6024 0.9036
5.750 0.4148 0.05619 0.04489 -0.0166 0.5924 0.9095
6.000 0.4447 0.05642 0.04517 -0.0176 0.5877 0.9152
6.250 0.4549 0.05758 0.04643 -0.0171 0.5785 0.9211
6.500 0.4821 0.05793 0.04685 -0.0179 0.5727 0.9276
6.750 0.4975 0.05894 0.04795 -0.0180 0.5643 0.9350
7.000 0.5231 0.05946 0.04858 -0.0189 0.5575 0.9435
7.500 0.5709 0.06101 0.05035 -0.0214 0.5417 0.9663
7.750 0.5851 0.06206 0.05151 -0.0219 0.5317 1.0000
8.000 0.6153 0.06245 0.05199 -0.0233 0.5255 1.0000
8.250 0.6286 0.06398 0.05360 -0.0239 0.5150 1.0000
8.500 0.6617 0.06412 0.05383 -0.0254 0.5092 1.0000
8.750 0.6723 0.06588 0.05570 -0.0258 0.4977 1.0000
9.000 0.7093 0.06561 0.05553 -0.0272 0.4927 1.0000
9.250 0.7175 0.06759 0.05761 -0.0276 0.4804 1.0000
9.500 0.7569 0.06694 0.05710 -0.0289 0.4761 1.0000
9.750 0.7635 0.06908 0.05934 -0.0291 0.4631 1.0000
10.000 0.7754 0.07080 0.06116 -0.0296 0.4515 1.0000
10.250 0.8106 0.07021 0.06072 -0.0303 0.4458 1.0000
10.500 0.8182 0.07231 0.06293 -0.0306 0.4329 1.0000
10.750 0.8547 0.07135 0.06210 -0.0311 0.4277 1.0000
11.000 0.8643 0.07316 0.06404 -0.0313 0.4151 1.0000
11.250 0.8728 0.07518 0.06617 -0.0314 0.4024 1.0000
11.500 0.9123 0.07337 0.06452 -0.0315 0.3977 1.0000
11.750 0.9179 0.07566 0.06692 -0.0316 0.3841 1.0000
12.250 0.9687 0.07515 0.06671 -0.0314 0.3663 1.0000
12.500 0.9750 0.07733 0.06900 -0.0314 0.3527 1.0000
13.000 1.0335 0.07546 0.06740 -0.0307 0.3339 1.0000
13.250 1.0394 0.07765 0.06970 -0.0306 0.3199 1.0000
13.750 1.0600 0.08092 0.07319 -0.0305 0.2939 1.0000
14.000 1.0803 0.08112 0.07347 -0.0301 0.2817 1.0000
14.250 1.1041 0.08079 0.07317 -0.0296 0.2693 1.0000
14.500 1.1207 0.08150 0.07391 -0.0293 0.2561 1.0000
14.750 1.1207 0.08464 0.07715 -0.0296 0.2429 1.0000
15.000 1.1230 0.08752 0.08013 -0.0299 0.2303 1.0000
15.250 1.1291 0.08986 0.08252 -0.0301 0.2182 1.0000
15.500 1.1391 0.09157 0.08423 -0.0301 0.2064 1.0000
15.750 1.1517 0.09283 0.08547 -0.0301 0.1948 1.0000
16.000 1.1420 0.09778 0.09060 -0.0313 0.1844 1.0000
16.250 1.1438 0.10091 0.09379 -0.0320 0.1745 1.0000
16.500 1.1552 0.10237 0.09520 -0.0321 0.1644 1.0000
16.750 1.1441 0.10784 0.10089 -0.0339 0.1560 1.0000
17.000 1.1482 0.11064 0.10372 -0.0347 0.1475 1.0000
17.250 1.1472 0.11437 0.10754 -0.0360 0.1394 1.0000
17.500 1.1426 0.11890 0.11218 -0.0377 0.1325 1.0000
17.750 1.1446 0.12213 0.11546 -0.0390 0.1251 1.0000
18.000 1.1362 0.12753 0.12101 -0.0414 0.1193 1.0000
18.250 1.1254 0.13353 0.12716 -0.0443 0.1137 1.0000
18.500 1.1327 0.13584 0.12947 -0.0454 0.1078 1.0000
18.750 1.0926 0.14856 0.14247 -0.0523 0.1045 1.0000
19.000 1.0957 0.15190 0.14585 -0.0541 0.0992 1.0000
19.250 1.0867 0.15817 0.15217 -0.0577 0.0952 1.0000
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Polar data table (+)
Polar graphs
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