EPPLER 604 AIRFOIL (e604-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 604 AIRFOIL (e604-il) Reynolds number: 100,000 Max Cl/Cd: 34.08 at α=12.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e604-il-100000.txt Download as CSV file: xf-e604-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3044 0.11044 0.10614 -0.0783 0.9654 0.1394
-10.500 -0.2763 0.10758 0.10324 -0.0789 0.9615 0.1447
-10.250 -0.4222 0.07724 0.07269 -0.1011 0.9505 0.0719
-10.000 -0.4585 0.07012 0.06525 -0.1044 0.9434 0.0641
-9.750 -0.4917 0.06776 0.06275 -0.1012 0.9327 0.0625
-9.500 -0.5639 0.06546 0.05974 -0.0938 0.9189 0.0576
-9.250 -0.5500 0.06085 0.05507 -0.0946 0.9150 0.0559
-9.000 -0.5526 0.05752 0.05148 -0.0932 0.9094 0.0545
-8.750 -0.5684 0.05552 0.04923 -0.0885 0.9017 0.0534
-8.500 -0.5650 0.05150 0.04465 -0.0873 0.8974 0.0518
-8.250 -0.5697 0.04912 0.04181 -0.0835 0.8913 0.0510
-8.000 -0.5645 0.04749 0.03999 -0.0810 0.8857 0.0519
-7.750 -0.5455 0.04554 0.03776 -0.0807 0.8822 0.0537
-7.500 -0.5174 0.04340 0.03515 -0.0815 0.8796 0.0562
-7.250 -0.5235 0.04287 0.03435 -0.0766 0.8732 0.0574
-7.000 -0.5044 0.04098 0.03229 -0.0754 0.8691 0.0592
-6.750 -0.4771 0.03963 0.03093 -0.0758 0.8660 0.0638
-6.500 -0.4447 0.03816 0.02935 -0.0766 0.8637 0.0709
-6.250 -0.4367 0.03779 0.02897 -0.0739 0.8592 0.0760
-6.000 -0.4292 0.03717 0.02834 -0.0709 0.8540 0.0829
-5.750 -0.4077 0.03647 0.02763 -0.0701 0.8505 0.0940
-5.500 -0.3824 0.03540 0.02678 -0.0701 0.8479 0.1112
-5.250 -0.3590 0.03457 0.02609 -0.0698 0.8450 0.1372
-5.000 -0.3692 0.03448 0.02615 -0.0647 0.8389 0.1520
-4.750 -0.3580 0.03325 0.02549 -0.0633 0.8353 0.2108
-4.500 -0.3528 0.03195 0.02651 -0.0596 0.8323 0.5522
-4.250 -0.3208 0.03428 0.02865 -0.0572 0.8294 0.6369
-4.000 -0.3324 0.03557 0.02992 -0.0506 0.8234 0.6524
-3.750 -0.3233 0.03710 0.03133 -0.0463 0.8196 0.6753
-3.500 -0.3075 0.03881 0.03296 -0.0415 0.8159 0.6936
-3.250 -0.2796 0.04048 0.03450 -0.0381 0.8129 0.7119
-3.000 -0.2908 0.04114 0.03511 -0.0330 0.8080 0.7250
-2.750 -0.2887 0.04222 0.03617 -0.0272 0.8040 0.7356
-2.500 -0.2723 0.04307 0.03690 -0.0237 0.8000 0.7501
-2.250 -0.2438 0.04398 0.03768 -0.0214 0.7968 0.7673
-2.000 -0.2537 0.04454 0.03821 -0.0159 0.7927 0.7795
-1.750 -0.2549 0.04509 0.03873 -0.0107 0.7882 0.7947
-1.500 -0.2433 0.04572 0.03928 -0.0063 0.7842 0.8126
-1.250 -0.2153 0.04618 0.03961 -0.0050 0.7810 0.8284
-1.000 -0.2185 0.04630 0.03967 -0.0017 0.7763 0.8384
-0.750 -0.2142 0.04642 0.03974 0.0014 0.7717 0.8447
-0.500 -0.1969 0.04652 0.03973 0.0018 0.7681 0.8512
-0.250 -0.1532 0.04654 0.03957 -0.0014 0.7639 0.8558
0.000 -0.1633 0.04672 0.03974 0.0028 0.7582 0.8601
0.250 -0.1506 0.04694 0.03989 0.0034 0.7540 0.8641
0.500 -0.1141 0.04704 0.03986 0.0010 0.7491 0.8674
0.750 -0.0996 0.04735 0.04009 0.0010 0.7430 0.8706
1.000 -0.0897 0.04767 0.04037 0.0021 0.7383 0.8734
1.250 -0.0557 0.04784 0.04044 0.0005 0.7332 0.8762
1.500 -0.0385 0.04823 0.04077 0.0005 0.7264 0.8789
1.750 -0.0224 0.04871 0.04121 0.0002 0.7208 0.8817
2.000 0.0215 0.04891 0.04131 -0.0029 0.7159 0.8844
2.250 0.0269 0.04954 0.04192 -0.0018 0.7081 0.8872
2.500 0.0521 0.04990 0.04224 -0.0026 0.7024 0.8894
2.750 0.1050 0.04994 0.04219 -0.0062 0.6982 0.8914
3.000 0.0936 0.05091 0.04320 -0.0035 0.6887 0.8953
3.250 0.1359 0.05107 0.04329 -0.0061 0.6836 0.8982
3.500 0.1445 0.05205 0.04427 -0.0058 0.6752 0.9011
3.750 0.1752 0.05225 0.04446 -0.0069 0.6690 0.9036
4.000 0.1968 0.05281 0.04501 -0.0072 0.6617 0.9066
4.250 0.2157 0.05341 0.04561 -0.0074 0.6543 0.9104
4.500 0.2640 0.05328 0.04545 -0.0102 0.6503 0.9139
4.750 0.2613 0.05460 0.04681 -0.0087 0.6394 0.9176
5.000 0.3035 0.05447 0.04667 -0.0107 0.6350 0.9209
5.250 0.3069 0.05574 0.04797 -0.0098 0.6244 0.9251
5.500 0.3483 0.05564 0.04788 -0.0118 0.6195 0.9289
5.750 0.3542 0.05686 0.04916 -0.0111 0.6092 0.9338
6.000 0.3914 0.05675 0.04907 -0.0125 0.6040 0.9390
6.250 0.4023 0.05794 0.05030 -0.0124 0.5938 0.9446
6.500 0.4397 0.05784 0.05025 -0.0139 0.5883 0.9499
6.750 0.4890 0.05721 0.04967 -0.0163 0.5852 0.9556
7.000 0.4956 0.05885 0.05139 -0.0166 0.5726 0.9623
7.250 0.5510 0.05796 0.05057 -0.0197 0.5699 0.9696
7.500 0.5616 0.05970 0.05241 -0.0209 0.5566 0.9809
7.750 0.5742 0.06112 0.05389 -0.0216 0.5451 1.0000
8.000 0.6207 0.06038 0.05323 -0.0240 0.5407 1.0000
8.250 0.6736 0.05911 0.05203 -0.0265 0.5382 1.0000
8.500 0.6816 0.06097 0.05396 -0.0270 0.5250 1.0000
8.750 0.7360 0.05929 0.05237 -0.0294 0.5225 1.0000
9.000 0.7459 0.06104 0.05420 -0.0299 0.5093 1.0000
9.250 0.8033 0.05879 0.05206 -0.0322 0.5075 1.0000
9.500 0.8117 0.06065 0.05400 -0.0326 0.4937 1.0000
9.750 0.8254 0.06214 0.05559 -0.0332 0.4811 1.0000
10.000 0.8814 0.05946 0.05302 -0.0349 0.4786 1.0000
10.250 0.9428 0.05586 0.04958 -0.0366 0.4773 1.0000
10.500 1.0101 0.05133 0.04519 -0.0383 0.4768 1.0000
10.750 1.0923 0.04556 0.03960 -0.0408 0.4765 1.0000
11.000 1.1112 0.04585 0.03998 -0.0407 0.4631 1.0000
11.250 1.1542 0.04392 0.03817 -0.0417 0.4521 1.0000
11.500 1.2392 0.03863 0.03294 -0.0448 0.4414 1.0000
11.750 1.2620 0.03859 0.03293 -0.0447 0.4233 1.0000
12.000 1.2842 0.03862 0.03295 -0.0444 0.4036 1.0000
12.250 1.3102 0.03844 0.03268 -0.0443 0.3827 1.0000
12.500 1.3172 0.03974 0.03391 -0.0430 0.3618 1.0000
12.750 1.3209 0.04133 0.03546 -0.0417 0.3412 1.0000
13.000 1.3287 0.04267 0.03669 -0.0406 0.3206 1.0000
13.250 1.3339 0.04432 0.03821 -0.0394 0.3006 1.0000
13.500 1.3332 0.04650 0.04035 -0.0381 0.2821 1.0000
13.750 1.3332 0.04872 0.04252 -0.0370 0.2641 1.0000
14.000 1.3341 0.05096 0.04469 -0.0360 0.2470 1.0000
14.250 1.3345 0.05330 0.04697 -0.0351 0.2308 1.0000
14.500 1.3350 0.05573 0.04934 -0.0343 0.2156 1.0000
14.750 1.3354 0.05825 0.05184 -0.0336 0.2013 1.0000
15.000 1.3362 0.06082 0.05437 -0.0330 0.1879 1.0000
15.250 1.3376 0.06339 0.05690 -0.0325 0.1753 1.0000
15.500 1.3409 0.06581 0.05923 -0.0321 0.1633 1.0000
15.750 1.3407 0.06864 0.06207 -0.0319 0.1525 1.0000
16.000 1.3388 0.07181 0.06533 -0.0317 0.1425 1.0000
16.250 1.3416 0.07450 0.06800 -0.0315 0.1329 1.0000
16.500 1.3503 0.07651 0.06985 -0.0314 0.1228 1.0000
16.750 1.3415 0.08066 0.07429 -0.0316 0.1162 1.0000
17.000 1.3487 0.08294 0.07647 -0.0316 0.1080 1.0000
17.250 1.3434 0.08678 0.08051 -0.0321 0.1019 1.0000
17.500 1.3512 0.08909 0.08275 -0.0322 0.0951 1.0000
17.750 1.3444 0.09327 0.08716 -0.0329 0.0902 1.0000
18.000 1.3578 0.09493 0.08867 -0.0329 0.0838 1.0000
18.250 1.3453 0.09994 0.09402 -0.0340 0.0805 1.0000
18.500 1.3464 0.10310 0.09723 -0.0348 0.0761 1.0000
18.750 1.3517 0.10596 0.10013 -0.0353 0.0718 1.0000
19.000 1.3376 0.11143 0.10591 -0.0371 0.0695 1.0000
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Polar data table (+)
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