EPPLER 435 AIRFOIL (e435-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
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Airfoil: EPPLER 435 AIRFOIL (e435-il) Reynolds number: 1,000,000 Max Cl/Cd: 148.67 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e435-il-1000000.txt Download as CSV file: xf-e435-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.1332 0.10400 0.10223 -0.1035 0.9568 0.0113
-11.750 -0.1202 0.09893 0.09714 -0.1086 0.9498 0.0115
-9.000 -0.2581 0.02106 0.01625 -0.1539 0.8007 0.0080
-8.750 -0.2379 0.02054 0.01564 -0.1533 0.7962 0.0079
-8.500 -0.2237 0.01815 0.01309 -0.1521 0.7915 0.0076
-8.250 -0.2054 0.01686 0.01161 -0.1512 0.7870 0.0074
-8.000 -0.1848 0.01587 0.01049 -0.1505 0.7828 0.0073
-7.750 -0.1639 0.01490 0.00942 -0.1498 0.7789 0.0072
-7.500 -0.1418 0.01417 0.00859 -0.1493 0.7749 0.0072
-7.250 -0.1192 0.01350 0.00782 -0.1489 0.7711 0.0071
-7.000 -0.0957 0.01290 0.00714 -0.1486 0.7674 0.0072
-6.750 -0.0716 0.01234 0.00653 -0.1484 0.7640 0.0072
-6.500 -0.0468 0.01185 0.00598 -0.1483 0.7606 0.0073
-6.250 -0.0212 0.01141 0.00548 -0.1483 0.7572 0.0074
-6.000 0.0051 0.01104 0.00504 -0.1484 0.7538 0.0075
-5.750 0.0320 0.01070 0.00465 -0.1486 0.7505 0.0077
-5.500 0.0588 0.01028 0.00419 -0.1487 0.7475 0.0082
-5.250 0.0862 0.00996 0.00384 -0.1490 0.7444 0.0090
-5.000 0.1140 0.00967 0.00352 -0.1493 0.7412 0.0112
-4.750 0.1420 0.00932 0.00319 -0.1497 0.7379 0.0228
-4.500 0.1705 0.00907 0.00300 -0.1502 0.7348 0.0404
-4.250 0.1988 0.00881 0.00283 -0.1506 0.7320 0.0595
-4.000 0.2274 0.00856 0.00267 -0.1512 0.7289 0.0866
-3.750 0.2562 0.00826 0.00252 -0.1518 0.7259 0.1294
-3.500 0.2856 0.00770 0.00230 -0.1530 0.7228 0.2360
-3.250 0.3171 0.00673 0.00202 -0.1551 0.7193 0.4578
-3.000 0.3466 0.00652 0.00203 -0.1557 0.7167 0.5389
-2.750 0.3758 0.00652 0.00202 -0.1561 0.7137 0.5578
-2.500 0.4049 0.00652 0.00202 -0.1564 0.7106 0.5718
-2.250 0.4339 0.00655 0.00203 -0.1567 0.7075 0.5836
-2.000 0.4632 0.00664 0.00204 -0.1571 0.7040 0.5926
-1.750 0.4921 0.00665 0.00207 -0.1574 0.7010 0.5997
-1.500 0.5209 0.00669 0.00207 -0.1576 0.6978 0.6060
-1.250 0.5496 0.00670 0.00209 -0.1579 0.6944 0.6125
-1.000 0.5782 0.00678 0.00214 -0.1581 0.6909 0.6203
-0.750 0.6071 0.00688 0.00218 -0.1584 0.6869 0.6271
-0.500 0.6352 0.00690 0.00223 -0.1585 0.6838 0.6329
-0.250 0.6637 0.00692 0.00225 -0.1588 0.6801 0.6367
0.000 0.6921 0.00696 0.00226 -0.1590 0.6762 0.6392
0.250 0.7205 0.00703 0.00227 -0.1592 0.6721 0.6412
0.500 0.7487 0.00703 0.00227 -0.1595 0.6682 0.6437
0.750 0.7767 0.00702 0.00229 -0.1596 0.6638 0.6460
1.000 0.8045 0.00705 0.00231 -0.1597 0.6593 0.6481
1.250 0.8323 0.00713 0.00235 -0.1599 0.6547 0.6504
1.500 0.8602 0.00714 0.00239 -0.1600 0.6504 0.6530
1.750 0.8879 0.00718 0.00242 -0.1601 0.6455 0.6554
2.000 0.9151 0.00726 0.00246 -0.1602 0.6405 0.6575
2.250 0.9427 0.00730 0.00251 -0.1603 0.6354 0.6596
2.500 0.9698 0.00732 0.00255 -0.1603 0.6296 0.6622
2.750 0.9960 0.00740 0.00261 -0.1601 0.6238 0.6645
3.000 1.0233 0.00744 0.00268 -0.1602 0.6180 0.6669
3.250 1.0496 0.00752 0.00275 -0.1600 0.6114 0.6696
3.500 1.0757 0.00761 0.00283 -0.1598 0.6050 0.6724
3.750 1.1019 0.00769 0.00291 -0.1597 0.5973 0.6747
4.000 1.1269 0.00779 0.00301 -0.1593 0.5896 0.6773
4.250 1.1524 0.00786 0.00310 -0.1590 0.5812 0.6801
4.500 1.1769 0.00798 0.00322 -0.1585 0.5729 0.6828
4.750 1.2009 0.00811 0.00335 -0.1579 0.5630 0.6855
5.000 1.2250 0.00824 0.00348 -0.1574 0.5532 0.6884
5.250 1.2472 0.00842 0.00362 -0.1564 0.5419 0.6911
5.750 1.2882 0.00880 0.00397 -0.1539 0.5145 0.6975
6.000 1.3060 0.00902 0.00416 -0.1521 0.4995 0.7007
6.250 1.3228 0.00928 0.00439 -0.1501 0.4836 0.7040
6.500 1.3387 0.00961 0.00466 -0.1480 0.4666 0.7072
6.750 1.3540 0.00998 0.00497 -0.1458 0.4487 0.7104
7.000 1.3690 0.01034 0.00530 -0.1436 0.4302 0.7140
7.250 1.3834 0.01075 0.00567 -0.1414 0.4111 0.7177
7.500 1.3957 0.01125 0.00609 -0.1388 0.3905 0.7215
7.750 1.4075 0.01179 0.00655 -0.1362 0.3710 0.7254
8.000 1.4186 0.01235 0.00705 -0.1335 0.3511 0.7297
8.250 1.4298 0.01294 0.00760 -0.1310 0.3317 0.7343
8.500 1.4399 0.01360 0.00820 -0.1283 0.3123 0.7389
8.750 1.4484 0.01436 0.00888 -0.1255 0.2929 0.7434
9.000 1.4572 0.01514 0.00961 -0.1228 0.2750 0.7485
9.250 1.4667 0.01592 0.01036 -0.1203 0.2585 0.7540
9.500 1.4756 0.01680 0.01118 -0.1179 0.2411 0.7595
9.750 1.4837 0.01773 0.01208 -0.1154 0.2242 0.7658
10.000 1.4916 0.01872 0.01303 -0.1130 0.2084 0.7730
10.250 1.4996 0.01976 0.01404 -0.1108 0.1936 0.7807
10.500 1.5073 0.02086 0.01512 -0.1086 0.1791 0.7898
10.750 1.5149 0.02200 0.01625 -0.1065 0.1657 0.8000
11.000 1.5218 0.02322 0.01746 -0.1044 0.1525 0.8122
11.250 1.5285 0.02449 0.01874 -0.1023 0.1402 0.8281
11.500 1.5341 0.02583 0.02010 -0.1003 0.1271 0.8517
11.750 1.5362 0.02690 0.02135 -0.0973 0.1162 0.9459
12.000 1.5432 0.02837 0.02278 -0.0957 0.1052 1.0000
12.250 1.5491 0.02996 0.02433 -0.0941 0.0942 1.0000
12.500 1.5559 0.03152 0.02586 -0.0927 0.0853 1.0000
12.750 1.5605 0.03332 0.02762 -0.0911 0.0753 1.0000
13.000 1.5656 0.03512 0.02939 -0.0897 0.0669 1.0000
13.250 1.5716 0.03688 0.03113 -0.0885 0.0594 1.0000
13.500 1.5778 0.03868 0.03293 -0.0873 0.0534 1.0000
13.750 1.5831 0.04061 0.03485 -0.0862 0.0476 1.0000
14.000 1.5887 0.04257 0.03681 -0.0852 0.0427 1.0000
14.250 1.5944 0.04455 0.03880 -0.0843 0.0382 1.0000
14.500 1.5989 0.04670 0.04096 -0.0834 0.0343 1.0000
14.750 1.6038 0.04887 0.04315 -0.0826 0.0306 1.0000
15.000 1.6089 0.05105 0.04537 -0.0819 0.0276 1.0000
15.250 1.6123 0.05348 0.04781 -0.0813 0.0247 1.0000
15.500 1.6173 0.05577 0.05015 -0.0808 0.0224 1.0000
15.750 1.6207 0.05829 0.05270 -0.0803 0.0204 1.0000
16.000 1.6249 0.06079 0.05525 -0.0800 0.0187 1.0000
16.250 1.6280 0.06345 0.05797 -0.0797 0.0171 1.0000
16.500 1.6311 0.06617 0.06074 -0.0796 0.0158 1.0000
16.750 1.6335 0.06903 0.06366 -0.0795 0.0145 1.0000
17.000 1.6350 0.07205 0.06673 -0.0795 0.0133 1.0000
17.250 1.6373 0.07504 0.06980 -0.0796 0.0124 1.0000
17.500 1.6374 0.07837 0.07318 -0.0798 0.0114 1.0000
17.750 1.6379 0.08168 0.07657 -0.0802 0.0106 1.0000
18.000 1.6386 0.08503 0.08000 -0.0806 0.0098 1.0000
18.250 1.6369 0.08876 0.08380 -0.0812 0.0091 1.0000
18.500 1.6354 0.09254 0.08765 -0.0819 0.0084 1.0000
18.750 1.6352 0.09617 0.09137 -0.0827 0.0079 1.0000
19.000 1.6326 0.10020 0.09547 -0.0837 0.0073 1.0000
19.250 1.6278 0.10461 0.09997 -0.0849 0.0068 1.0000
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