EPPLER 604 AIRFOIL (e604-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 604 AIRFOIL (e604-il) Reynolds number: 100,000 Max Cl/Cd: 30.12 at α=10.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e604-il-100000-n5.txt Download as CSV file: xf-e604-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.3204 0.10908 0.10420 -0.0800 0.9825 0.0226
-12.750 -0.4431 0.07538 0.07000 -0.1009 0.9740 0.0204
-12.500 -0.4601 0.06868 0.06308 -0.1062 0.9651 0.0203
-12.250 -0.4733 0.06275 0.05686 -0.1109 0.9574 0.0203
-12.000 -0.4861 0.05774 0.05153 -0.1138 0.9473 0.0203
-11.750 -0.4898 0.05341 0.04686 -0.1166 0.9398 0.0204
-11.500 -0.4854 0.05011 0.04334 -0.1186 0.9319 0.0206
-11.250 -0.4755 0.04722 0.04024 -0.1206 0.9254 0.0210
-11.000 -0.4674 0.04464 0.03740 -0.1215 0.9167 0.0214
-10.750 -0.4517 0.04202 0.03451 -0.1231 0.9114 0.0221
-10.500 -0.4411 0.03999 0.03222 -0.1228 0.9020 0.0227
-10.250 -0.4208 0.03775 0.02960 -0.1238 0.8965 0.0240
-10.000 -0.4064 0.03631 0.02802 -0.1234 0.8880 0.0254
-9.750 -0.3854 0.03492 0.02649 -0.1240 0.8817 0.0271
-9.500 -0.3601 0.03341 0.02471 -0.1242 0.8764 0.0289
-9.250 -0.3405 0.03222 0.02348 -0.1237 0.8694 0.0304
-9.000 -0.3174 0.03110 0.02225 -0.1240 0.8642 0.0331
-8.750 -0.3003 0.03020 0.02126 -0.1231 0.8575 0.0362
-8.500 -0.2831 0.02935 0.02035 -0.1222 0.8509 0.0397
-8.250 -0.2620 0.02835 0.01929 -0.1221 0.8462 0.0440
-8.000 -0.2515 0.02778 0.01863 -0.1199 0.8386 0.0490
-7.750 -0.2381 0.02700 0.01788 -0.1185 0.8329 0.0548
-7.500 -0.2223 0.02624 0.01707 -0.1174 0.8285 0.0617
-7.250 -0.2181 0.02586 0.01668 -0.1141 0.8210 0.0691
-7.000 -0.2053 0.02522 0.01602 -0.1124 0.8158 0.0797
-6.750 -0.1915 0.02455 0.01538 -0.1109 0.8113 0.0941
-6.500 -0.1868 0.02415 0.01507 -0.1078 0.8045 0.1092
-6.250 -0.1748 0.02354 0.01456 -0.1059 0.8000 0.1343
-6.000 -0.1605 0.02273 0.01395 -0.1046 0.7965 0.1763
-5.750 -0.1612 0.02223 0.01372 -0.1008 0.7895 0.2225
-5.500 -0.1567 0.02124 0.01316 -0.0983 0.7844 0.3066
-5.250 -0.1454 0.02065 0.01346 -0.0954 0.7811 0.4539
-5.000 -0.1239 0.02151 0.01454 -0.0928 0.7773 0.5440
-4.750 -0.1091 0.02187 0.01479 -0.0907 0.7719 0.5781
-4.500 -0.0843 0.02232 0.01507 -0.0897 0.7681 0.6024
-4.250 -0.0565 0.02268 0.01524 -0.0894 0.7653 0.6221
-4.000 -0.0273 0.02327 0.01569 -0.0887 0.7629 0.6360
-3.750 -0.0171 0.02399 0.01637 -0.0852 0.7569 0.6473
-3.500 0.0047 0.02458 0.01686 -0.0834 0.7530 0.6611
-3.250 0.0308 0.02499 0.01713 -0.0826 0.7500 0.6751
-3.000 0.0615 0.02554 0.01757 -0.0817 0.7479 0.6813
-2.750 0.0715 0.02562 0.01757 -0.0795 0.7426 0.6915
-2.500 0.0887 0.02597 0.01787 -0.0772 0.7380 0.6952
-2.250 0.1140 0.02602 0.01782 -0.0767 0.7349 0.6999
-2.000 0.1432 0.02571 0.01734 -0.0779 0.7324 0.7067
-1.750 0.1747 0.02556 0.01707 -0.0787 0.7306 0.7100
-1.500 0.1727 0.02606 0.01761 -0.0738 0.7231 0.7134
-1.250 0.1961 0.02602 0.01748 -0.0735 0.7195 0.7168
-1.000 0.2263 0.02580 0.01715 -0.0746 0.7170 0.7208
-0.750 0.2608 0.02547 0.01668 -0.0768 0.7151 0.7250
-0.500 0.2617 0.02596 0.01721 -0.0726 0.7082 0.7274
-0.250 0.2816 0.02606 0.01728 -0.0716 0.7040 0.7300
0.000 0.3107 0.02597 0.01711 -0.0722 0.7014 0.7325
0.250 0.3447 0.02576 0.01682 -0.0737 0.6994 0.7351
0.750 0.3712 0.02633 0.01736 -0.0708 0.6883 0.7424
1.000 0.3998 0.02627 0.01726 -0.0711 0.6855 0.7441
1.250 0.4333 0.02611 0.01705 -0.0724 0.6835 0.7460
1.500 0.4659 0.02599 0.01690 -0.0735 0.6813 0.7482
1.750 0.4526 0.02697 0.01795 -0.0677 0.6715 0.7522
2.000 0.4868 0.02684 0.01778 -0.0694 0.6690 0.7552
2.250 0.5264 0.02661 0.01750 -0.0720 0.6672 0.7578
2.500 0.5622 0.02642 0.01729 -0.0735 0.6655 0.7594
2.750 0.5372 0.02769 0.01868 -0.0658 0.6542 0.7624
3.000 0.5716 0.02751 0.01850 -0.0670 0.6521 0.7648
3.250 0.6107 0.02724 0.01822 -0.0691 0.6504 0.7674
4.000 0.6654 0.02816 0.01924 -0.0665 0.6349 0.7761
4.250 0.7049 0.02777 0.01887 -0.0684 0.6333 0.7780
4.750 0.7191 0.02919 0.02042 -0.0634 0.6190 0.7846
5.000 0.7587 0.02873 0.01999 -0.0653 0.6170 0.7877
5.500 0.7811 0.02997 0.02136 -0.0617 0.6028 0.7938
6.000 0.8037 0.03132 0.02287 -0.0584 0.5881 0.8002
6.250 0.8304 0.03131 0.02291 -0.0586 0.5834 0.8036
6.750 0.8720 0.03165 0.02342 -0.0574 0.5711 0.8105
7.250 0.9018 0.03268 0.02461 -0.0551 0.5559 0.8181
7.750 0.9363 0.03349 0.02560 -0.0535 0.5405 0.8255
8.250 0.9718 0.03412 0.02642 -0.0517 0.5247 0.8338
8.750 1.0127 0.03439 0.02687 -0.0504 0.5082 0.8430
9.000 1.0135 0.03591 0.02849 -0.0483 0.4956 0.8481
9.250 1.0305 0.03639 0.02907 -0.0476 0.4856 0.8534
9.500 1.0596 0.03580 0.02857 -0.0474 0.4773 0.8581
9.750 1.0671 0.03688 0.02974 -0.0459 0.4645 0.8638
10.250 1.1040 0.03733 0.03035 -0.0442 0.4406 0.8769
10.500 1.1251 0.03736 0.03043 -0.0435 0.4276 0.8849
10.750 1.1383 0.03787 0.03101 -0.0421 0.4131 0.8935
11.000 1.1491 0.03868 0.03188 -0.0408 0.3977 0.9038
11.250 1.1597 0.03947 0.03272 -0.0395 0.3818 0.9172
11.500 1.1695 0.04030 0.03359 -0.0382 0.3655 0.9407
11.750 1.1765 0.04146 0.03477 -0.0373 0.3484 1.0000
12.000 1.1868 0.04300 0.03630 -0.0370 0.3307 1.0000
12.250 1.1958 0.04464 0.03793 -0.0366 0.3130 1.0000
12.500 1.2038 0.04641 0.03966 -0.0363 0.2957 1.0000
12.750 1.2105 0.04829 0.04151 -0.0359 0.2790 1.0000
13.000 1.2163 0.05032 0.04351 -0.0355 0.2630 1.0000
13.250 1.2210 0.05249 0.04566 -0.0351 0.2474 1.0000
13.500 1.2250 0.05477 0.04792 -0.0348 0.2326 1.0000
13.750 1.2284 0.05716 0.05032 -0.0345 0.2185 1.0000
14.000 1.2312 0.05966 0.05280 -0.0343 0.2051 1.0000
14.250 1.2336 0.06227 0.05540 -0.0342 0.1925 1.0000
14.500 1.2353 0.06500 0.05812 -0.0341 0.1805 1.0000
14.750 1.2374 0.06778 0.06095 -0.0342 0.1689 1.0000
15.000 1.2389 0.07067 0.06388 -0.0343 0.1582 1.0000
15.250 1.2397 0.07369 0.06689 -0.0345 0.1484 1.0000
15.500 1.2403 0.07680 0.07006 -0.0349 0.1388 1.0000
15.750 1.2414 0.07992 0.07324 -0.0353 0.1299 1.0000
16.000 1.2405 0.08328 0.07659 -0.0358 0.1222 1.0000
16.250 1.2415 0.08654 0.07997 -0.0364 0.1142 1.0000
16.500 1.2408 0.09003 0.08347 -0.0371 0.1074 1.0000
16.750 1.2405 0.09354 0.08709 -0.0380 0.1005 1.0000
17.000 1.2394 0.09716 0.09073 -0.0389 0.0947 1.0000
17.250 1.2388 0.10082 0.09451 -0.0400 0.0887 1.0000
17.500 1.2368 0.10464 0.09832 -0.0411 0.0839 1.0000
17.750 1.2366 0.10834 0.10219 -0.0424 0.0784 1.0000
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