EPPLER 433 AIRFOIL (e433-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 433 AIRFOIL (e433-il) Reynolds number: 500,000 Max Cl/Cd: 116.11 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e433-il-500000.txt Download as CSV file: xf-e433-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 433 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.0990 0.03000 0.02708 -0.1477 0.9012 0.0190
-8.250 -0.1090 0.02800 0.02499 -0.1453 0.8929 0.0191
-8.000 -0.1070 0.02592 0.02281 -0.1442 0.8872 0.0193
-7.750 -0.1058 0.02399 0.02080 -0.1426 0.8810 0.0196
-7.500 -0.1008 0.02208 0.01877 -0.1413 0.8756 0.0202
-7.250 -0.0942 0.01963 0.01609 -0.1402 0.8711 0.0212
-7.000 -0.0939 0.01809 0.01391 -0.1364 0.8644 0.0233
-6.750 -0.1042 0.02018 0.01465 -0.1390 0.8690 0.0119
-6.500 -0.0844 0.01860 0.01282 -0.1378 0.8646 0.0119
-6.250 -0.0604 0.01746 0.01144 -0.1372 0.8609 0.0117
-6.000 -0.0358 0.01620 0.01005 -0.1370 0.8578 0.0120
-5.750 -0.0108 0.01566 0.00949 -0.1368 0.8545 0.0130
-5.500 0.0123 0.01502 0.00877 -0.1361 0.8504 0.0135
-5.250 0.0367 0.01423 0.00788 -0.1355 0.8468 0.0138
-5.000 0.0618 0.01348 0.00704 -0.1351 0.8436 0.0139
-4.750 0.0878 0.01286 0.00633 -0.1349 0.8405 0.0142
-4.500 0.1100 0.01240 0.00584 -0.1340 0.8366 0.0147
-4.250 0.1333 0.01177 0.00518 -0.1334 0.8327 0.0157
-4.000 0.1600 0.01140 0.00477 -0.1334 0.8294 0.0184
-3.750 0.1870 0.01089 0.00426 -0.1334 0.8264 0.0298
-3.500 0.2108 0.01033 0.00398 -0.1331 0.8228 0.0888
-3.250 0.2352 0.00983 0.00380 -0.1331 0.8188 0.1721
-3.000 0.2601 0.00890 0.00355 -0.1336 0.8152 0.3668
-2.750 0.2854 0.00793 0.00355 -0.1339 0.8121 0.6602
-2.500 0.3132 0.00803 0.00365 -0.1338 0.8088 0.7020
-2.250 0.3396 0.00812 0.00371 -0.1334 0.8047 0.7217
-2.000 0.3674 0.00823 0.00376 -0.1333 0.8008 0.7373
-1.750 0.3959 0.00835 0.00384 -0.1332 0.7974 0.7504
-1.500 0.4237 0.00848 0.00393 -0.1331 0.7940 0.7592
-1.250 0.4500 0.00857 0.00397 -0.1328 0.7895 0.7681
-1.000 0.4761 0.00864 0.00405 -0.1322 0.7853 0.7748
-0.750 0.5044 0.00876 0.00411 -0.1322 0.7816 0.7851
-0.500 0.5286 0.00895 0.00432 -0.1311 0.7774 0.7950
-0.250 0.5535 0.00901 0.00439 -0.1303 0.7725 0.8022
0.000 0.5807 0.00904 0.00438 -0.1301 0.7682 0.8061
0.250 0.6104 0.00906 0.00434 -0.1306 0.7644 0.8093
0.500 0.6363 0.00905 0.00432 -0.1305 0.7591 0.8124
0.750 0.6650 0.00902 0.00425 -0.1308 0.7541 0.8149
1.250 0.7185 0.00898 0.00420 -0.1306 0.7439 0.8187
1.500 0.7458 0.00897 0.00416 -0.1306 0.7384 0.8209
1.750 0.7741 0.00897 0.00414 -0.1309 0.7334 0.8230
2.000 0.7998 0.00897 0.00415 -0.1306 0.7268 0.8255
2.250 0.8285 0.00897 0.00411 -0.1310 0.7211 0.8280
2.500 0.8545 0.00898 0.00413 -0.1308 0.7141 0.8304
2.750 0.8805 0.00897 0.00411 -0.1305 0.7073 0.8322
3.000 0.9056 0.00898 0.00415 -0.1301 0.7000 0.8341
3.250 0.9312 0.00900 0.00417 -0.1298 0.6922 0.8363
3.500 0.9560 0.00904 0.00422 -0.1293 0.6838 0.8389
3.750 0.9822 0.00910 0.00425 -0.1292 0.6753 0.8416
4.000 1.0064 0.00915 0.00432 -0.1286 0.6652 0.8442
4.250 1.0304 0.00920 0.00438 -0.1280 0.6550 0.8464
4.500 1.0534 0.00927 0.00445 -0.1272 0.6442 0.8486
4.750 1.0751 0.00936 0.00454 -0.1261 0.6315 0.8511
5.000 1.0963 0.00947 0.00465 -0.1249 0.6177 0.8540
5.250 1.1170 0.00962 0.00478 -0.1236 0.6025 0.8573
5.500 1.1367 0.00981 0.00493 -0.1222 0.5857 0.8604
5.750 1.1532 0.00998 0.00509 -0.1201 0.5675 0.8632
6.000 1.1669 0.01019 0.00526 -0.1174 0.5476 0.8666
6.250 1.1791 0.01048 0.00550 -0.1145 0.5267 0.8704
6.500 1.1920 0.01084 0.00580 -0.1118 0.5040 0.8744
6.750 1.2030 0.01123 0.00613 -0.1088 0.4819 0.8783
7.000 1.2131 0.01168 0.00651 -0.1057 0.4585 0.8829
7.250 1.2238 0.01218 0.00694 -0.1028 0.4355 0.8879
7.500 1.2340 0.01269 0.00740 -0.0999 0.4126 0.8926
7.750 1.2425 0.01327 0.00791 -0.0968 0.3893 0.8980
8.000 1.2534 0.01387 0.00845 -0.0943 0.3675 0.9040
8.250 1.2617 0.01447 0.00902 -0.0912 0.3456 0.9106
8.500 1.2708 0.01516 0.00965 -0.0885 0.3247 0.9188
8.750 1.2781 0.01580 0.01027 -0.0855 0.3034 0.9291
9.000 1.2849 0.01648 0.01093 -0.0824 0.2841 0.9453
9.250 1.2972 0.01722 0.01164 -0.0807 0.2629 1.0000
9.500 1.3100 0.01818 0.01250 -0.0794 0.2407 1.0000
9.750 1.3217 0.01920 0.01344 -0.0778 0.2195 1.0000
10.000 1.3334 0.02022 0.01438 -0.0763 0.1993 1.0000
10.250 1.3439 0.02132 0.01539 -0.0747 0.1806 1.0000
10.500 1.3543 0.02244 0.01644 -0.0731 0.1637 1.0000
10.750 1.3650 0.02355 0.01750 -0.0716 0.1479 1.0000
11.000 1.3749 0.02472 0.01863 -0.0701 0.1326 1.0000
11.250 1.3842 0.02597 0.01983 -0.0685 0.1180 1.0000
11.500 1.3930 0.02727 0.02110 -0.0669 0.1047 1.0000
11.750 1.4015 0.02862 0.02241 -0.0654 0.0928 1.0000
12.000 1.4092 0.03007 0.02382 -0.0639 0.0812 1.0000
12.250 1.4162 0.03161 0.02533 -0.0624 0.0704 1.0000
12.500 1.4223 0.03325 0.02695 -0.0610 0.0612 1.0000
12.750 1.4292 0.03488 0.02858 -0.0596 0.0533 1.0000
13.000 1.4360 0.03656 0.03027 -0.0584 0.0464 1.0000
13.250 1.4413 0.03841 0.03213 -0.0572 0.0404 1.0000
13.500 1.4455 0.04042 0.03413 -0.0560 0.0349 1.0000
13.750 1.4523 0.04223 0.03600 -0.0550 0.0310 1.0000
14.000 1.4544 0.04455 0.03833 -0.0539 0.0273 1.0000
14.250 1.4623 0.04634 0.04019 -0.0533 0.0242 1.0000
14.500 1.4638 0.04886 0.04274 -0.0524 0.0217 1.0000
14.750 1.4708 0.05084 0.04480 -0.0519 0.0195 1.0000
15.000 1.4728 0.05343 0.04744 -0.0513 0.0177 1.0000
15.250 1.4764 0.05591 0.05001 -0.0509 0.0162 1.0000
15.500 1.4795 0.05850 0.05269 -0.0506 0.0149 1.0000
15.750 1.4785 0.06165 0.05591 -0.0504 0.0136 1.0000
16.000 1.4806 0.06451 0.05887 -0.0503 0.0126 1.0000
16.250 1.4819 0.06754 0.06200 -0.0504 0.0114 1.0000
16.500 1.4780 0.07135 0.06588 -0.0507 0.0104 1.0000
16.750 1.4787 0.07462 0.06928 -0.0510 0.0095 1.0000
17.000 1.4773 0.07825 0.07301 -0.0516 0.0085 1.0000
17.250 1.4700 0.08285 0.07771 -0.0525 0.0078 1.0000
17.500 1.4687 0.08666 0.08165 -0.0534 0.0069 1.0000
17.750 1.4636 0.09113 0.08622 -0.0546 0.0062 1.0000
18.000 1.4538 0.09649 0.09170 -0.0562 0.0055 1.0000
18.250 1.4476 0.10135 0.09670 -0.0578 0.0049 1.0000
18.500 1.4392 0.10668 0.10214 -0.0598 0.0044 1.0000
18.750 1.4235 0.11341 0.10900 -0.0626 0.0041 1.0000
19.000 1.4158 0.11885 0.11459 -0.0650 0.0036 1.0000
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Polar data table (+)
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