EPPLER 433 AIRFOIL (e433-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 433 AIRFOIL (e433-il) Reynolds number: 1,000,000 Max Cl/Cd: 126.12 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e433-il-1000000-n5.txt Download as CSV file: xf-e433-il-1000000-n5.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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.1190 0.08199 0.07996 -0.1265 0.9306 0.0028
-11.000 -0.1109 0.07521 0.07312 -0.1340 0.9196 0.0029
-10.750 -0.3865 0.02757 0.02425 -0.1505 0.8617 0.0026
-10.500 -0.4036 0.02541 0.02182 -0.1458 0.8528 0.0026
-10.250 -0.4199 0.02196 0.01789 -0.1416 0.8447 0.0028
-10.000 -0.4103 0.02055 0.01625 -0.1398 0.8397 0.0028
-9.750 -0.3951 0.01957 0.01514 -0.1386 0.8354 0.0029
-9.500 -0.3785 0.01862 0.01404 -0.1375 0.8311 0.0030
-9.250 -0.3569 0.01825 0.01361 -0.1369 0.8274 0.0031
-9.000 -0.3388 0.01727 0.01246 -0.1359 0.8237 0.0031
-8.750 -0.3182 0.01655 0.01162 -0.1353 0.8201 0.0032
-8.500 -0.2964 0.01594 0.01092 -0.1347 0.8166 0.0034
-8.250 -0.2748 0.01524 0.01008 -0.1341 0.8132 0.0034
-8.000 -0.2526 0.01459 0.00931 -0.1335 0.8099 0.0035
-7.750 -0.2296 0.01398 0.00860 -0.1330 0.8068 0.0036
-7.500 -0.2058 0.01347 0.00801 -0.1327 0.8035 0.0037
-7.250 -0.1820 0.01297 0.00741 -0.1323 0.8001 0.0038
-7.000 -0.1582 0.01245 0.00679 -0.1318 0.7969 0.0039
-6.750 -0.1335 0.01203 0.00630 -0.1315 0.7941 0.0040
-6.500 -0.1084 0.01164 0.00586 -0.1313 0.7911 0.0041
-6.250 -0.0834 0.01122 0.00539 -0.1311 0.7878 0.0041
-6.000 -0.0580 0.01088 0.00498 -0.1309 0.7845 0.0042
-5.750 -0.0323 0.01058 0.00462 -0.1307 0.7815 0.0043
-5.500 -0.0066 0.01023 0.00423 -0.1306 0.7786 0.0045
-5.250 0.0194 0.00990 0.00388 -0.1305 0.7754 0.0049
-5.000 0.0460 0.00966 0.00361 -0.1305 0.7722 0.0052
-4.750 0.0726 0.00943 0.00335 -0.1305 0.7689 0.0055
-4.500 0.0993 0.00922 0.00310 -0.1305 0.7658 0.0058
-4.250 0.1265 0.00902 0.00286 -0.1305 0.7628 0.0061
-4.000 0.1537 0.00881 0.00263 -0.1306 0.7595 0.0072
-3.750 0.1810 0.00864 0.00245 -0.1307 0.7559 0.0090
-3.500 0.2081 0.00846 0.00227 -0.1307 0.7523 0.0140
-3.250 0.2353 0.00828 0.00213 -0.1308 0.7489 0.0270
-3.000 0.2628 0.00810 0.00201 -0.1310 0.7450 0.0435
-2.750 0.2900 0.00787 0.00189 -0.1312 0.7408 0.0762
-2.500 0.3170 0.00757 0.00178 -0.1314 0.7366 0.1373
-2.250 0.3443 0.00725 0.00168 -0.1318 0.7327 0.2122
-2.000 0.3721 0.00695 0.00159 -0.1322 0.7281 0.2882
-1.750 0.3997 0.00664 0.00151 -0.1326 0.7232 0.3746
-1.500 0.4277 0.00602 0.00139 -0.1335 0.7184 0.5508
-1.250 0.4560 0.00579 0.00141 -0.1339 0.7130 0.6455
-1.000 0.4839 0.00580 0.00143 -0.1340 0.7075 0.6708
-0.750 0.5118 0.00583 0.00145 -0.1341 0.7025 0.6864
-0.500 0.5398 0.00585 0.00147 -0.1342 0.6967 0.6996
-0.250 0.5671 0.00591 0.00151 -0.1342 0.6908 0.7134
0.000 0.5948 0.00597 0.00158 -0.1342 0.6846 0.7283
0.250 0.6219 0.00605 0.00162 -0.1342 0.6772 0.7378
0.500 0.6491 0.00610 0.00166 -0.1342 0.6703 0.7412
0.750 0.6760 0.00617 0.00169 -0.1341 0.6625 0.7433
1.000 0.7031 0.00623 0.00172 -0.1341 0.6550 0.7453
1.250 0.7295 0.00631 0.00176 -0.1339 0.6462 0.7473
1.500 0.7563 0.00639 0.00180 -0.1339 0.6372 0.7494
1.750 0.7822 0.00649 0.00186 -0.1336 0.6270 0.7514
2.000 0.8074 0.00660 0.00192 -0.1333 0.6155 0.7531
2.250 0.8328 0.00671 0.00200 -0.1329 0.6033 0.7548
2.500 0.8573 0.00683 0.00208 -0.1324 0.5897 0.7566
2.750 0.8812 0.00699 0.00218 -0.1318 0.5747 0.7586
3.000 0.9043 0.00717 0.00231 -0.1310 0.5579 0.7608
3.250 0.9266 0.00737 0.00244 -0.1300 0.5403 0.7630
3.500 0.9483 0.00759 0.00258 -0.1290 0.5204 0.7650
3.750 0.9693 0.00784 0.00275 -0.1278 0.4994 0.7670
4.000 0.9888 0.00812 0.00293 -0.1263 0.4779 0.7688
4.250 1.0072 0.00838 0.00312 -0.1247 0.4565 0.7708
4.500 1.0242 0.00867 0.00333 -0.1227 0.4350 0.7730
4.750 1.0414 0.00897 0.00356 -0.1208 0.4143 0.7755
5.000 1.0586 0.00930 0.00381 -0.1189 0.3928 0.7780
5.250 1.0758 0.00965 0.00408 -0.1171 0.3729 0.7804
5.500 1.0929 0.01001 0.00436 -0.1153 0.3527 0.7826
5.750 1.1105 0.01036 0.00464 -0.1136 0.3342 0.7847
6.000 1.1273 0.01073 0.00495 -0.1118 0.3155 0.7870
6.500 1.1599 0.01154 0.00564 -0.1081 0.2794 0.7919
6.750 1.1754 0.01199 0.00602 -0.1062 0.2606 0.7946
7.000 1.1912 0.01245 0.00641 -0.1044 0.2429 0.7974
7.250 1.2055 0.01297 0.00686 -0.1023 0.2244 0.8000
7.500 1.2201 0.01348 0.00733 -0.1004 0.2078 0.8027
7.750 1.2350 0.01401 0.00780 -0.0985 0.1929 0.8055
8.000 1.2496 0.01456 0.00831 -0.0967 0.1775 0.8085
8.250 1.2636 0.01516 0.00886 -0.0948 0.1625 0.8115
8.500 1.2774 0.01579 0.00944 -0.0930 0.1477 0.8144
8.750 1.2905 0.01646 0.01007 -0.0910 0.1332 0.8176
9.000 1.3026 0.01720 0.01076 -0.0891 0.1176 0.8213
9.250 1.3150 0.01796 0.01147 -0.0872 0.1040 0.8250
9.500 1.3275 0.01873 0.01221 -0.0854 0.0923 0.8286
9.750 1.3386 0.01961 0.01304 -0.0834 0.0787 0.8321
10.000 1.3519 0.02037 0.01380 -0.0818 0.0719 0.8361
10.250 1.3595 0.02150 0.01485 -0.0796 0.0550 0.8406
10.500 1.3708 0.02245 0.01577 -0.0779 0.0464 0.8449
10.750 1.3810 0.02346 0.01677 -0.0761 0.0383 0.8496
11.000 1.3923 0.02443 0.01776 -0.0745 0.0326 0.8552
11.500 1.4147 0.02644 0.01981 -0.0714 0.0240 0.8682
12.000 1.4351 0.02862 0.02207 -0.0684 0.0175 0.8851
12.250 1.4451 0.02972 0.02323 -0.0669 0.0151 0.8970
12.500 1.4533 0.03087 0.02446 -0.0651 0.0130 0.9169
13.000 1.4718 0.03332 0.02706 -0.0625 0.0096 1.0000
13.250 1.4813 0.03472 0.02849 -0.0614 0.0082 1.0000
13.500 1.4906 0.03616 0.02998 -0.0603 0.0072 1.0000
13.750 1.4997 0.03766 0.03152 -0.0594 0.0062 1.0000
14.000 1.5081 0.03926 0.03316 -0.0584 0.0054 1.0000
14.250 1.5152 0.04100 0.03496 -0.0575 0.0043 1.0000
14.500 1.5230 0.04273 0.03674 -0.0566 0.0038 1.0000
14.750 1.5289 0.04468 0.03875 -0.0558 0.0030 1.0000
15.000 1.5351 0.04666 0.04078 -0.0551 0.0026 1.0000
15.250 1.5405 0.04876 0.04295 -0.0544 0.0021 1.0000
15.500 1.5452 0.05097 0.04523 -0.0538 0.0018 1.0000
15.750 1.5489 0.05337 0.04770 -0.0533 0.0014 1.0000
16.000 1.5512 0.05598 0.05038 -0.0529 0.0010 1.0000
16.250 1.5540 0.05861 0.05310 -0.0526 0.0008 1.0000
16.500 1.5547 0.06157 0.05614 -0.0524 0.0005 1.0000
16.750 1.5551 0.06461 0.05927 -0.0524 0.0004 1.0000
17.000 1.5555 0.06775 0.06250 -0.0525 0.0003 1.0000
17.250 1.5561 0.07095 0.06579 -0.0528 0.0003 1.0000
17.500 1.5548 0.07447 0.06942 -0.0532 0.0003 1.0000
17.750 1.5537 0.07805 0.07309 -0.0538 0.0002 1.0000
18.000 1.5507 0.08198 0.07713 -0.0545 0.0002 1.0000
18.250 1.5471 0.08608 0.08133 -0.0555 0.0002 1.0000
18.500 1.5430 0.09038 0.08574 -0.0566 0.0002 1.0000
18.750 1.5377 0.09493 0.09040 -0.0580 0.0002 1.0000
19.000 1.5306 0.09987 0.09546 -0.0596 0.0001 1.0000
19.250 1.5244 0.10472 0.10043 -0.0614 0.0001 1.0000
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Polar data table (+)
Polar graphs
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