EPPLER 435 AIRFOIL (e435-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 435 AIRFOIL (e435-il) Reynolds number: 500,000 Max Cl/Cd: 119.48 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e435-il-500000.txt Download as CSV file: xf-e435-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 435 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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.1137 0.09379 0.09141 -0.1095 0.9489 0.0213
-10.750 -0.1024 0.08781 0.08541 -0.1159 0.9448 0.0222
-10.500 -0.1163 0.07167 0.06929 -0.1312 0.9374 0.0235
-10.250 -0.1004 0.06423 0.06179 -0.1414 0.9322 0.0237
-10.000 -0.0942 0.05547 0.05287 -0.1546 0.9210 0.0239
-9.750 -0.0973 0.04879 0.04593 -0.1642 0.9030 0.0241
-9.500 -0.1052 0.04520 0.04213 -0.1670 0.8852 0.0243
-9.250 -0.1189 0.04261 0.03936 -0.1665 0.8698 0.0245
-9.000 -0.1344 0.04073 0.03732 -0.1642 0.8574 0.0246
-8.750 -0.1383 0.03862 0.03501 -0.1630 0.8487 0.0250
-8.500 -0.1408 0.03648 0.03268 -0.1613 0.8403 0.0257
-8.250 -0.1833 0.02344 0.01799 -0.1546 0.8313 0.0127
-8.000 -0.1669 0.02156 0.01593 -0.1536 0.8259 0.0124
-7.750 -0.1477 0.01978 0.01390 -0.1528 0.8213 0.0120
-7.500 -0.1252 0.01841 0.01230 -0.1523 0.8172 0.0117
-7.250 -0.1047 0.01730 0.01105 -0.1514 0.8127 0.0116
-7.000 -0.0827 0.01639 0.01003 -0.1506 0.8082 0.0116
-6.750 -0.0596 0.01563 0.00916 -0.1502 0.8043 0.0117
-6.500 -0.0355 0.01497 0.00840 -0.1499 0.8006 0.0119
-6.250 -0.0133 0.01436 0.00776 -0.1493 0.7966 0.0123
-6.000 0.0105 0.01382 0.00716 -0.1490 0.7925 0.0127
-5.750 0.0345 0.01316 0.00644 -0.1489 0.7888 0.0136
-5.500 0.0614 0.01275 0.00598 -0.1492 0.7855 0.0150
-5.250 0.0868 0.01230 0.00550 -0.1492 0.7820 0.0174
-5.000 0.1128 0.01185 0.00506 -0.1492 0.7782 0.0239
-4.750 0.1397 0.01135 0.00464 -0.1496 0.7746 0.0456
-4.500 0.1675 0.01093 0.00436 -0.1502 0.7714 0.0787
-4.250 0.1965 0.01049 0.00412 -0.1512 0.7682 0.1382
-4.000 0.2234 0.00973 0.00382 -0.1521 0.7648 0.2557
-3.750 0.2527 0.00862 0.00355 -0.1539 0.7613 0.4914
-3.500 0.2819 0.00860 0.00361 -0.1542 0.7579 0.5534
-3.250 0.3114 0.00868 0.00363 -0.1546 0.7548 0.5770
-3.000 0.3415 0.00882 0.00369 -0.1551 0.7517 0.5931
-2.750 0.3692 0.00892 0.00376 -0.1550 0.7484 0.6064
-2.500 0.3971 0.00901 0.00385 -0.1550 0.7448 0.6163
-2.250 0.4263 0.00911 0.00387 -0.1553 0.7414 0.6258
-2.000 0.4550 0.00919 0.00393 -0.1554 0.7383 0.6325
-1.750 0.4848 0.00936 0.00401 -0.1559 0.7351 0.6408
-1.500 0.5111 0.00945 0.00415 -0.1555 0.7316 0.6488
-1.250 0.5391 0.00958 0.00425 -0.1555 0.7279 0.6572
-1.000 0.5672 0.00962 0.00428 -0.1556 0.7244 0.6625
-0.750 0.5962 0.00968 0.00429 -0.1559 0.7212 0.6662
-0.500 0.6249 0.00974 0.00432 -0.1562 0.7177 0.6695
-0.250 0.6524 0.00975 0.00432 -0.1563 0.7138 0.6727
0.000 0.6812 0.00976 0.00428 -0.1567 0.7098 0.6753
0.250 0.7099 0.00974 0.00423 -0.1570 0.7062 0.6776
0.500 0.7392 0.00980 0.00426 -0.1574 0.7026 0.6799
0.750 0.7655 0.00979 0.00429 -0.1572 0.6984 0.6822
1.000 0.7931 0.00980 0.00429 -0.1573 0.6940 0.6846
1.250 0.8217 0.00982 0.00428 -0.1576 0.6900 0.6873
1.500 0.8507 0.00989 0.00430 -0.1581 0.6859 0.6903
1.750 0.8771 0.00990 0.00433 -0.1580 0.6809 0.6928
2.000 0.9042 0.00987 0.00432 -0.1580 0.6761 0.6950
2.250 0.9328 0.00991 0.00433 -0.1582 0.6719 0.6973
2.500 0.9587 0.00994 0.00441 -0.1580 0.6668 0.6998
2.750 0.9850 0.00996 0.00445 -0.1579 0.6615 0.7026
3.000 1.0129 0.01000 0.00446 -0.1580 0.6565 0.7056
3.250 1.0389 0.01006 0.00454 -0.1579 0.6508 0.7087
3.500 1.0644 0.01006 0.00458 -0.1575 0.6447 0.7113
3.750 1.0918 0.01012 0.00462 -0.1576 0.6391 0.7139
4.000 1.1155 0.01015 0.00473 -0.1569 0.6322 0.7167
4.250 1.1410 0.01021 0.00479 -0.1566 0.6256 0.7198
4.500 1.1657 0.01028 0.00489 -0.1562 0.6184 0.7230
4.750 1.1902 0.01036 0.00497 -0.1557 0.6106 0.7262
5.000 1.2136 0.01043 0.00509 -0.1550 0.6026 0.7293
5.250 1.2367 0.01053 0.00520 -0.1542 0.5941 0.7327
5.500 1.2592 0.01063 0.00536 -0.1533 0.5849 0.7363
5.750 1.2813 0.01079 0.00549 -0.1524 0.5755 0.7400
6.000 1.3021 0.01091 0.00565 -0.1512 0.5644 0.7435
6.250 1.3214 0.01106 0.00584 -0.1497 0.5528 0.7470
6.500 1.3383 0.01125 0.00603 -0.1477 0.5402 0.7508
6.750 1.3529 0.01148 0.00624 -0.1453 0.5267 0.7552
7.000 1.3670 0.01177 0.00651 -0.1428 0.5122 0.7597
7.250 1.3800 0.01209 0.00684 -0.1402 0.4967 0.7641
7.500 1.3924 0.01247 0.00721 -0.1375 0.4799 0.7691
7.750 1.4042 0.01292 0.00762 -0.1348 0.4624 0.7744
8.000 1.4147 0.01340 0.00810 -0.1320 0.4441 0.7793
8.250 1.4235 0.01398 0.00866 -0.1289 0.4251 0.7849
8.500 1.4308 0.01468 0.00930 -0.1258 0.4052 0.7913
8.750 1.4371 0.01543 0.01002 -0.1225 0.3865 0.7975
9.000 1.4436 0.01626 0.01081 -0.1195 0.3670 0.8052
9.250 1.4498 0.01714 0.01168 -0.1165 0.3476 0.8131
9.500 1.4554 0.01813 0.01264 -0.1136 0.3284 0.8229
9.750 1.4597 0.01920 0.01369 -0.1107 0.3097 0.8335
10.000 1.4640 0.02033 0.01481 -0.1078 0.2921 0.8469
10.250 1.4680 0.02148 0.01598 -0.1050 0.2753 0.8659
10.500 1.4698 0.02256 0.01714 -0.1018 0.2595 0.9076
10.750 1.4740 0.02378 0.01835 -0.0994 0.2429 1.0000
11.000 1.4802 0.02523 0.01974 -0.0976 0.2258 1.0000
11.250 1.4860 0.02675 0.02119 -0.0958 0.2098 1.0000
11.500 1.4918 0.02831 0.02271 -0.0941 0.1948 1.0000
11.750 1.4974 0.02993 0.02428 -0.0924 0.1803 1.0000
12.000 1.5025 0.03163 0.02595 -0.0908 0.1667 1.0000
12.250 1.5071 0.03342 0.02770 -0.0893 0.1535 1.0000
12.500 1.5117 0.03528 0.02951 -0.0878 0.1406 1.0000
12.750 1.5168 0.03712 0.03133 -0.0865 0.1283 1.0000
13.000 1.5216 0.03906 0.03324 -0.0853 0.1168 1.0000
13.250 1.5262 0.04106 0.03523 -0.0841 0.1062 1.0000
13.500 1.5301 0.04318 0.03734 -0.0830 0.0967 1.0000
13.750 1.5327 0.04547 0.03961 -0.0820 0.0875 1.0000
14.000 1.5368 0.04768 0.04182 -0.0811 0.0793 1.0000
14.250 1.5407 0.04997 0.04413 -0.0803 0.0719 1.0000
14.500 1.5429 0.05251 0.04667 -0.0795 0.0652 1.0000
14.750 1.5456 0.05503 0.04921 -0.0789 0.0590 1.0000
15.000 1.5483 0.05763 0.05184 -0.0784 0.0534 1.0000
15.250 1.5480 0.06064 0.05485 -0.0779 0.0482 1.0000
15.500 1.5513 0.06328 0.05755 -0.0776 0.0437 1.0000
15.750 1.5511 0.06642 0.06072 -0.0773 0.0400 1.0000
16.000 1.5521 0.06946 0.06380 -0.0772 0.0361 1.0000
16.250 1.5520 0.07271 0.06712 -0.0772 0.0333 1.0000
16.500 1.5522 0.07600 0.07046 -0.0773 0.0304 1.0000
16.750 1.5510 0.07956 0.07409 -0.0776 0.0280 1.0000
17.000 1.5510 0.08298 0.07758 -0.0780 0.0256 1.0000
17.250 1.5475 0.08697 0.08163 -0.0785 0.0238 1.0000
17.500 1.5483 0.09040 0.08515 -0.0791 0.0219 1.0000
17.750 1.5438 0.09470 0.08951 -0.0800 0.0204 1.0000
18.000 1.5428 0.09851 0.09342 -0.0809 0.0189 1.0000
18.250 1.5405 0.10254 0.09754 -0.0819 0.0176 1.0000
18.500 1.5337 0.10736 0.10244 -0.0833 0.0166 1.0000
18.750 1.5320 0.11142 0.10661 -0.0846 0.0156 1.0000
19.000 1.5287 0.11576 0.11105 -0.0861 0.0147 1.0000
19.250 1.5227 0.12062 0.11600 -0.0879 0.0139 1.0000
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