E423 (e423-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: E423 (e423-il) Reynolds number: 100,000 Max Cl/Cd: 51.9 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e423-il-100000-n5.txt Download as CSV file: xf-e423-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E423
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
------ -------- --------- --------- -------- -------- --------
-9.250 0.2438 0.10172 0.09599 -0.1370 0.8342 0.0452
-9.000 0.2569 0.09932 0.09354 -0.1405 0.8240 0.0456
-8.750 0.2754 0.09652 0.09064 -0.1455 0.8163 0.0457
-8.500 0.2950 0.09303 0.08712 -0.1464 0.8075 0.0464
-8.250 0.3162 0.09022 0.08423 -0.1492 0.7999 0.0484
-8.000 0.3287 0.08806 0.08202 -0.1509 0.7910 0.0497
-7.750 0.3411 0.08591 0.07982 -0.1533 0.7830 0.0510
-7.500 0.3445 0.08457 0.07847 -0.1553 0.7747 0.0518
-7.250 0.3626 0.08156 0.07543 -0.1553 0.7680 0.0537
-7.000 0.3768 0.07934 0.07314 -0.1570 0.7621 0.0544
-6.750 0.3827 0.07770 0.07152 -0.1567 0.7549 0.0556
-6.500 0.3885 0.07592 0.06973 -0.1568 0.7482 0.0562
-6.250 0.3985 0.07386 0.06761 -0.1578 0.7430 0.0561
-6.000 0.3971 0.07254 0.06634 -0.1560 0.7359 0.0556
-5.500 0.4004 0.06620 0.05991 -0.1593 0.7255 0.0350
-5.250 0.4079 0.06446 0.05820 -0.1591 0.7202 0.0346
-5.000 0.4153 0.06251 0.05626 -0.1595 0.7147 0.0342
-4.750 0.4287 0.06013 0.05384 -0.1616 0.7100 0.0337
-4.500 0.4490 0.05712 0.05075 -0.1658 0.7063 0.0334
-4.250 0.4586 0.05477 0.04843 -0.1674 0.7008 0.0336
-4.000 0.4824 0.04999 0.04358 -0.1750 0.6960 0.0351
-3.750 0.5055 0.04889 0.04244 -0.1764 0.6921 0.0370
-3.500 0.5494 0.04372 0.03706 -0.1869 0.6889 0.0385
-3.250 0.6034 0.03693 0.02997 -0.2006 0.6850 0.0421
-2.750 0.7164 0.02560 0.01699 -0.2226 0.6769 0.0601
-2.500 0.7490 0.02494 0.01605 -0.2241 0.6735 0.0681
-2.250 0.7833 0.02438 0.01518 -0.2256 0.6706 0.0768
-2.000 0.8088 0.02432 0.01507 -0.2254 0.6667 0.0840
-1.750 0.8316 0.02423 0.01492 -0.2247 0.6622 0.0913
-1.500 0.8594 0.02396 0.01445 -0.2249 0.6583 0.1005
-1.250 0.8892 0.02382 0.01411 -0.2254 0.6551 0.1109
-1.000 0.9202 0.02380 0.01403 -0.2260 0.6523 0.1207
-0.750 0.9450 0.02382 0.01396 -0.2256 0.6488 0.1307
-0.500 0.9653 0.02399 0.01406 -0.2244 0.6443 0.1408
-0.250 0.9894 0.02409 0.01416 -0.2238 0.6405 0.1501
0.000 1.0177 0.02408 0.01399 -0.2239 0.6373 0.1619
0.250 1.0482 0.02409 0.01392 -0.2245 0.6347 0.1730
0.500 1.0745 0.02418 0.01395 -0.2243 0.6315 0.1834
0.750 1.0905 0.02453 0.01432 -0.2223 0.6270 0.1929
1.000 1.1123 0.02473 0.01453 -0.2214 0.6231 0.2025
1.250 1.1388 0.02486 0.01456 -0.2212 0.6200 0.2148
1.500 1.1688 0.02489 0.01457 -0.2217 0.6172 0.2265
1.750 1.2008 0.02492 0.01451 -0.2225 0.6148 0.2399
2.000 1.2096 0.02553 0.01519 -0.2193 0.6098 0.2499
2.250 1.2278 0.02589 0.01561 -0.2177 0.6058 0.2611
2.500 1.2517 0.02611 0.01583 -0.2171 0.6025 0.2757
2.750 1.2808 0.02618 0.01588 -0.2174 0.5997 0.2931
3.000 1.3138 0.02620 0.01585 -0.2184 0.5974 0.3159
3.250 1.3193 0.02696 0.01678 -0.2147 0.5925 0.3323
3.500 1.3326 0.02751 0.01744 -0.2125 0.5882 0.3569
3.750 1.3554 0.02772 0.01778 -0.2118 0.5847 0.4036
4.000 1.3786 0.02711 0.01789 -0.2109 0.5819 1.0000
4.250 1.4127 0.02722 0.01782 -0.2120 0.5796 1.0000
4.500 1.4057 0.02844 0.01916 -0.2064 0.5742 1.0000
4.750 1.4124 0.02927 0.02000 -0.2030 0.5695 1.0000
5.000 1.4345 0.02964 0.02032 -0.2022 0.5661 1.0000
5.250 1.4659 0.02976 0.02034 -0.2029 0.5635 1.0000
5.500 1.4937 0.03002 0.02054 -0.2030 0.5607 1.0000
5.750 1.4620 0.03225 0.02297 -0.1940 0.5532 1.0000
6.000 1.4786 0.03283 0.02357 -0.1924 0.5493 1.0000
6.250 1.5083 0.03289 0.02358 -0.1927 0.5466 1.0000
6.500 1.5471 0.03265 0.02325 -0.1944 0.5445 1.0000
6.750 1.4877 0.03668 0.02756 -0.1827 0.5343 1.0000
7.000 1.5105 0.03698 0.02784 -0.1821 0.5309 1.0000
7.250 1.5461 0.03659 0.02743 -0.1830 0.5286 1.0000
7.750 1.5091 0.04214 0.03321 -0.1728 0.5137 1.0000
8.000 1.5465 0.04135 0.03239 -0.1736 0.5117 1.0000
8.250 1.5910 0.04020 0.03121 -0.1752 0.5101 1.0000
8.500 1.5145 0.04767 0.03891 -0.1658 0.4956 1.0000
8.750 1.5542 0.04642 0.03765 -0.1664 0.4942 1.0000
9.250 1.5120 0.05475 0.04619 -0.1596 0.4752 1.0000
9.750 1.5179 0.05903 0.05059 -0.1565 0.4617 1.0000
10.000 1.5567 0.05731 0.04889 -0.1565 0.4606 1.0000
10.500 1.5483 0.06324 0.05498 -0.1531 0.4445 1.0000
11.000 1.5460 0.06880 0.06069 -0.1504 0.4286 1.0000
11.500 1.5345 0.07587 0.06793 -0.1480 0.4104 1.0000
12.000 1.5523 0.07917 0.07137 -0.1463 0.3971 1.0000
12.500 1.5597 0.08398 0.07634 -0.1447 0.3815 1.0000
12.750 1.5391 0.08999 0.08246 -0.1441 0.3687 1.0000
13.000 1.5694 0.08855 0.08108 -0.1434 0.3660 1.0000
13.250 1.6033 0.08661 0.07916 -0.1426 0.3636 1.0000
13.500 1.5812 0.09289 0.08556 -0.1422 0.3506 1.0000
13.750 1.6116 0.09138 0.08410 -0.1414 0.3472 1.0000
14.000 1.5947 0.09702 0.08986 -0.1412 0.3351 1.0000
14.250 1.6237 0.09566 0.08853 -0.1404 0.3311 1.0000
14.500 1.6100 0.10089 0.09387 -0.1404 0.3196 1.0000
|
Polar data table (+)
Polar graphs
<< Back to E423 (e423-il)