E423 (e423-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: E423 (e423-il) Reynolds number: 1,000,000 Max Cl/Cd: 156.53 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e423-il-1000000.txt Download as CSV file: xf-e423-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 0.3336 0.09252 0.08930 -0.1719 0.7457 0.0133
-10.250 0.3390 0.09024 0.08698 -0.1725 0.7351 0.0134
-10.000 0.3449 0.08822 0.08489 -0.1728 0.7240 0.0134
-9.750 0.3518 0.08599 0.08265 -0.1733 0.7158 0.0134
-9.500 0.3573 0.08377 0.08038 -0.1736 0.7072 0.0135
-9.250 0.3646 0.08152 0.07812 -0.1739 0.7002 0.0135
-9.000 0.3751 0.07987 0.07643 -0.1736 0.6930 0.0137
-8.750 0.3842 0.07827 0.07481 -0.1736 0.6858 0.0138
-8.500 0.3923 0.07640 0.07292 -0.1739 0.6797 0.0139
-8.250 0.4011 0.07485 0.07135 -0.1738 0.6735 0.0141
-8.000 0.4087 0.07311 0.06959 -0.1739 0.6679 0.0142
-7.750 0.4167 0.07131 0.06780 -0.1740 0.6633 0.0143
-7.500 0.4239 0.06958 0.06606 -0.1739 0.6581 0.0147
-7.250 0.4292 0.06778 0.06423 -0.1736 0.6527 0.0151
-7.000 0.4352 0.06599 0.06245 -0.1734 0.6487 0.0152
-6.750 0.3424 0.01856 0.01412 -0.2281 0.6483 0.0092
-6.500 0.3764 0.01556 0.01081 -0.2325 0.6442 0.0093
-6.250 0.4060 0.01439 0.00943 -0.2340 0.6398 0.0095
-6.000 0.4344 0.01356 0.00842 -0.2348 0.6354 0.0097
-5.750 0.4634 0.01291 0.00761 -0.2355 0.6316 0.0100
-5.500 0.4925 0.01234 0.00693 -0.2361 0.6286 0.0103
-5.250 0.5209 0.01192 0.00640 -0.2364 0.6251 0.0107
-5.000 0.5499 0.01129 0.00563 -0.2370 0.6214 0.0115
-4.750 0.5776 0.01102 0.00525 -0.2370 0.6175 0.0121
-4.500 0.6059 0.01079 0.00494 -0.2372 0.6140 0.0129
-4.250 0.6344 0.01056 0.00465 -0.2373 0.6116 0.0135
-4.000 0.6632 0.01021 0.00424 -0.2376 0.6087 0.0150
-3.750 0.6912 0.01001 0.00397 -0.2376 0.6055 0.0167
-3.500 0.7189 0.00982 0.00373 -0.2375 0.6023 0.0202
-3.250 0.7464 0.00973 0.00360 -0.2375 0.5987 0.0260
-3.000 0.7745 0.00964 0.00349 -0.2375 0.5960 0.0313
-2.750 0.8021 0.00953 0.00339 -0.2374 0.5937 0.0362
-2.500 0.8295 0.00945 0.00331 -0.2373 0.5911 0.0416
-2.250 0.8565 0.00939 0.00324 -0.2371 0.5883 0.0472
-2.000 0.8832 0.00935 0.00320 -0.2368 0.5854 0.0543
-1.750 0.9099 0.00934 0.00318 -0.2366 0.5824 0.0624
-1.500 0.9379 0.00938 0.00319 -0.2366 0.5790 0.0712
-1.250 0.9643 0.00932 0.00316 -0.2363 0.5771 0.0801
-1.000 0.9908 0.00930 0.00315 -0.2359 0.5748 0.0882
-0.750 1.0174 0.00928 0.00316 -0.2357 0.5723 0.0968
-0.500 1.0438 0.00928 0.00316 -0.2353 0.5697 0.1051
-0.250 1.0695 0.00934 0.00319 -0.2349 0.5669 0.1117
0.000 1.0957 0.00940 0.00324 -0.2345 0.5636 0.1211
0.250 1.1226 0.00948 0.00330 -0.2344 0.5609 0.1277
0.500 1.1485 0.00947 0.00334 -0.2340 0.5589 0.1375
0.750 1.1742 0.00950 0.00338 -0.2335 0.5565 0.1443
1.000 1.2000 0.00953 0.00344 -0.2331 0.5539 0.1537
1.250 1.2254 0.00960 0.00349 -0.2326 0.5512 0.1596
1.500 1.2507 0.00967 0.00357 -0.2322 0.5484 0.1687
1.750 1.2764 0.00981 0.00367 -0.2318 0.5449 0.1758
2.000 1.3021 0.00986 0.00375 -0.2314 0.5427 0.1840
2.250 1.3275 0.00990 0.00383 -0.2310 0.5404 0.1921
2.500 1.3528 0.00995 0.00390 -0.2305 0.5378 0.2003
2.750 1.3776 0.01002 0.00400 -0.2300 0.5350 0.2098
3.000 1.4018 0.01012 0.00410 -0.2293 0.5320 0.2199
3.250 1.4259 0.01026 0.00423 -0.2287 0.5286 0.2310
3.500 1.4509 0.01035 0.00436 -0.2283 0.5258 0.2453
3.750 1.4754 0.01040 0.00447 -0.2277 0.5233 0.2634
4.000 1.4998 0.01046 0.00460 -0.2272 0.5203 0.2859
4.250 1.5237 0.01054 0.00474 -0.2265 0.5169 0.3202
4.500 1.5467 0.01064 0.00491 -0.2258 0.5133 0.3716
4.750 1.5686 0.01010 0.00530 -0.2250 0.5094 1.0000
5.000 1.5923 0.01019 0.00542 -0.2243 0.5063 1.0000
5.250 1.6154 0.01032 0.00554 -0.2235 0.5025 1.0000
5.500 1.6372 0.01049 0.00570 -0.2225 0.4985 1.0000
5.750 1.6578 0.01074 0.00589 -0.2213 0.4941 1.0000
6.000 1.6811 0.01087 0.00606 -0.2206 0.4908 1.0000
6.250 1.7039 0.01102 0.00622 -0.2198 0.4867 1.0000
6.500 1.7250 0.01122 0.00641 -0.2187 0.4822 1.0000
6.750 1.7435 0.01152 0.00668 -0.2172 0.4774 1.0000
7.000 1.7659 0.01168 0.00687 -0.2164 0.4734 1.0000
7.250 1.7871 0.01189 0.00709 -0.2154 0.4686 1.0000
7.500 1.8057 0.01219 0.00737 -0.2139 0.4634 1.0000
7.750 1.8252 0.01247 0.00766 -0.2126 0.4587 1.0000
8.000 1.8456 0.01271 0.00792 -0.2115 0.4535 1.0000
8.250 1.8627 0.01306 0.00827 -0.2099 0.4477 1.0000
8.500 1.8807 0.01341 0.00862 -0.2084 0.4424 1.0000
8.750 1.8997 0.01372 0.00895 -0.2071 0.4365 1.0000
9.000 1.9141 0.01420 0.00941 -0.2051 0.4300 1.0000
9.250 1.9318 0.01457 0.00982 -0.2037 0.4241 1.0000
9.500 1.9469 0.01505 0.01030 -0.2018 0.4168 1.0000
9.750 1.9602 0.01562 0.01086 -0.1997 0.4100 1.0000
10.000 1.9754 0.01614 0.01139 -0.1980 0.4024 1.0000
10.250 1.9857 0.01688 0.01212 -0.1956 0.3947 1.0000
10.500 1.9989 0.01751 0.01277 -0.1936 0.3861 1.0000
10.750 2.0079 0.01838 0.01363 -0.1911 0.3778 1.0000
11.000 2.0178 0.01925 0.01450 -0.1888 0.3685 1.0000
11.250 2.0255 0.02026 0.01551 -0.1863 0.3591 1.0000
11.500 2.0298 0.02153 0.01675 -0.1835 0.3487 1.0000
11.750 2.0362 0.02273 0.01797 -0.1811 0.3381 1.0000
12.000 2.0389 0.02424 0.01946 -0.1783 0.3273 1.0000
12.250 2.0381 0.02607 0.02126 -0.1753 0.3155 1.0000
12.500 2.0391 0.02786 0.02305 -0.1727 0.3037 1.0000
12.750 2.0388 0.02985 0.02503 -0.1701 0.2922 1.0000
13.000 2.0349 0.03223 0.02739 -0.1674 0.2803 1.0000
13.250 2.0291 0.03487 0.03001 -0.1647 0.2689 1.0000
13.500 2.0261 0.03740 0.03254 -0.1624 0.2577 1.0000
13.750 2.0217 0.04015 0.03529 -0.1603 0.2471 1.0000
14.000 2.0148 0.04324 0.03837 -0.1581 0.2371 1.0000
14.250 2.0105 0.04616 0.04130 -0.1563 0.2272 1.0000
14.500 2.0064 0.04916 0.04431 -0.1547 0.2182 1.0000
14.750 1.9982 0.05268 0.04782 -0.1530 0.2088 1.0000
15.000 1.9954 0.05570 0.05087 -0.1517 0.2004 1.0000
15.250 1.9883 0.05927 0.05445 -0.1503 0.1923 1.0000
15.500 1.9852 0.06245 0.05764 -0.1492 0.1841 1.0000
15.750 1.9799 0.06597 0.06117 -0.1482 0.1765 1.0000
16.000 1.9748 0.06951 0.06473 -0.1473 0.1689 1.0000
16.250 1.9712 0.07292 0.06816 -0.1466 0.1616 1.0000
16.500 1.9657 0.07664 0.07189 -0.1459 0.1544 1.0000
16.750 1.9622 0.08016 0.07543 -0.1454 0.1479 1.0000
17.000 1.9581 0.08377 0.07907 -0.1449 0.1413 1.0000
17.250 1.9541 0.08743 0.08276 -0.1446 0.1353 1.0000
17.500 1.9515 0.09091 0.08626 -0.1443 0.1292 1.0000
17.750 1.9463 0.09483 0.09020 -0.1441 0.1234 1.0000
18.000 1.9453 0.09816 0.09355 -0.1441 0.1179 1.0000
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Polar data table (+)
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