E423 (e423-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: E423 (e423-il) Reynolds number: 500,000 Max Cl/Cd: 120.55 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e423-il-500000-n5.txt Download as CSV file: xf-e423-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 0.3319 0.09186 0.08759 -0.1660 0.7036 0.0148
-9.750 0.3399 0.08982 0.08553 -0.1664 0.6969 0.0150
-6.250 0.3787 0.01900 0.01342 -0.2251 0.6325 0.0097
-6.000 0.4119 0.01684 0.01097 -0.2284 0.6292 0.0101
-5.750 0.4420 0.01580 0.00973 -0.2298 0.6256 0.0104
-5.500 0.4711 0.01507 0.00881 -0.2306 0.6220 0.0107
-5.250 0.5000 0.01438 0.00796 -0.2314 0.6183 0.0112
-5.000 0.5284 0.01392 0.00734 -0.2319 0.6148 0.0117
-4.750 0.5572 0.01349 0.00682 -0.2323 0.6118 0.0123
-4.500 0.5857 0.01314 0.00636 -0.2326 0.6087 0.0131
-4.250 0.6140 0.01281 0.00594 -0.2328 0.6056 0.0141
-4.000 0.6419 0.01257 0.00561 -0.2329 0.6023 0.0160
-3.750 0.6696 0.01236 0.00531 -0.2330 0.5992 0.0182
-3.500 0.6974 0.01218 0.00507 -0.2330 0.5962 0.0214
-3.250 0.7254 0.01201 0.00486 -0.2331 0.5935 0.0256
-3.000 0.7533 0.01187 0.00469 -0.2331 0.5908 0.0299
-2.750 0.7807 0.01177 0.00455 -0.2330 0.5878 0.0348
-2.500 0.8079 0.01169 0.00443 -0.2329 0.5848 0.0403
-2.250 0.8348 0.01164 0.00434 -0.2327 0.5818 0.0460
-1.750 0.8894 0.01154 0.00421 -0.2325 0.5769 0.0596
-1.500 0.9166 0.01150 0.00417 -0.2323 0.5742 0.0670
-1.250 0.9433 0.01147 0.00414 -0.2321 0.5713 0.0747
-1.000 0.9696 0.01146 0.00413 -0.2318 0.5684 0.0824
-0.750 0.9958 0.01148 0.00412 -0.2314 0.5658 0.0901
-0.500 1.0218 0.01153 0.00413 -0.2310 0.5632 0.0978
-0.250 1.0479 0.01156 0.00417 -0.2307 0.5607 0.1060
0.000 1.0740 0.01158 0.00419 -0.2303 0.5581 0.1137
0.250 1.0998 0.01160 0.00424 -0.2299 0.5554 0.1229
0.500 1.1254 0.01165 0.00429 -0.2295 0.5527 0.1309
0.750 1.1505 0.01171 0.00435 -0.2289 0.5498 0.1390
1.000 1.1753 0.01179 0.00440 -0.2283 0.5470 0.1457
1.250 1.2002 0.01189 0.00449 -0.2278 0.5444 0.1539
1.500 1.2256 0.01195 0.00457 -0.2273 0.5421 0.1607
1.750 1.2509 0.01201 0.00467 -0.2269 0.5394 0.1687
2.000 1.2756 0.01209 0.00476 -0.2263 0.5364 0.1762
2.250 1.3001 0.01219 0.00487 -0.2257 0.5334 0.1838
2.500 1.3243 0.01230 0.00498 -0.2251 0.5306 0.1922
2.750 1.3482 0.01243 0.00510 -0.2244 0.5279 0.2004
3.000 1.3726 0.01254 0.00524 -0.2238 0.5252 0.2100
3.250 1.3968 0.01263 0.00539 -0.2232 0.5222 0.2201
3.500 1.4206 0.01274 0.00554 -0.2225 0.5192 0.2313
3.750 1.4439 0.01287 0.00570 -0.2217 0.5159 0.2450
4.000 1.4668 0.01301 0.00587 -0.2209 0.5129 0.2607
4.250 1.4894 0.01318 0.00605 -0.2201 0.5099 0.2789
4.500 1.5131 0.01328 0.00625 -0.2194 0.5068 0.3045
4.750 1.5359 0.01340 0.00646 -0.2187 0.5033 0.3389
5.000 1.5580 0.01352 0.00669 -0.2178 0.4995 0.3899
5.500 1.5985 0.01326 0.00724 -0.2153 0.4921 1.0000
5.750 1.6202 0.01346 0.00745 -0.2144 0.4880 1.0000
6.000 1.6406 0.01369 0.00770 -0.2131 0.4833 1.0000
6.250 1.6591 0.01399 0.00796 -0.2116 0.4787 1.0000
6.500 1.6790 0.01425 0.00823 -0.2103 0.4744 1.0000
6.750 1.6989 0.01451 0.00852 -0.2091 0.4694 1.0000
7.000 1.7172 0.01483 0.00884 -0.2076 0.4645 1.0000
7.250 1.7341 0.01521 0.00920 -0.2059 0.4597 1.0000
7.500 1.7532 0.01551 0.00954 -0.2046 0.4544 1.0000
7.750 1.7701 0.01591 0.00994 -0.2029 0.4488 1.0000
8.000 1.7849 0.01637 0.01040 -0.2010 0.4432 1.0000
8.250 1.8022 0.01677 0.01084 -0.1994 0.4371 1.0000
8.500 1.8159 0.01732 0.01138 -0.1974 0.4306 1.0000
8.750 1.8307 0.01784 0.01193 -0.1955 0.4248 1.0000
9.000 1.8446 0.01842 0.01253 -0.1936 0.4177 1.0000
9.250 1.8554 0.01915 0.01325 -0.1912 0.4109 1.0000
9.500 1.8686 0.01981 0.01395 -0.1893 0.4033 1.0000
9.750 1.8768 0.02074 0.01486 -0.1867 0.3958 1.0000
10.000 1.8885 0.02153 0.01569 -0.1847 0.3877 1.0000
10.250 1.8944 0.02267 0.01682 -0.1820 0.3794 1.0000
10.500 1.9037 0.02368 0.01786 -0.1799 0.3703 1.0000
10.750 1.9085 0.02501 0.01919 -0.1773 0.3618 1.0000
11.000 1.9141 0.02636 0.02056 -0.1750 0.3522 1.0000
11.250 1.9176 0.02792 0.02213 -0.1725 0.3427 1.0000
11.500 1.9173 0.02983 0.02404 -0.1698 0.3323 1.0000
11.750 1.9206 0.03158 0.02581 -0.1676 0.3219 1.0000
12.000 1.9191 0.03378 0.02801 -0.1652 0.3110 1.0000
12.250 1.9149 0.03632 0.03054 -0.1627 0.2998 1.0000
12.500 1.9142 0.03868 0.03292 -0.1606 0.2890 1.0000
12.750 1.9106 0.04137 0.03561 -0.1585 0.2782 1.0000
13.000 1.9044 0.04442 0.03866 -0.1565 0.2676 1.0000
13.250 1.9009 0.04730 0.04156 -0.1547 0.2571 1.0000
13.500 1.8967 0.05035 0.04462 -0.1531 0.2472 1.0000
13.750 1.8898 0.05377 0.04804 -0.1515 0.2377 1.0000
14.000 1.8865 0.05689 0.05119 -0.1502 0.2280 1.0000
14.250 1.8816 0.06025 0.05456 -0.1489 0.2193 1.0000
14.500 1.8772 0.06364 0.05797 -0.1478 0.2104 1.0000
14.750 1.8743 0.06690 0.06125 -0.1469 0.2022 1.0000
15.250 1.8674 0.07373 0.06813 -0.1453 0.1861 1.0000
15.500 1.8612 0.07760 0.07201 -0.1446 0.1785 1.0000
15.750 1.8601 0.08083 0.07528 -0.1441 0.1707 1.0000
16.000 1.8554 0.08458 0.07905 -0.1436 0.1640 1.0000
16.250 1.8544 0.08788 0.08239 -0.1433 0.1569 1.0000
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Polar data table (+)
Polar graphs
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