E423 (e423-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: E423 (e423-il) Reynolds number: 200,000 Max Cl/Cd: 84.29 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e423-il-200000-n5.txt Download as CSV file: xf-e423-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 0.3176 0.09387 0.08891 -0.1629 0.7885 0.0265
-9.500 0.3338 0.09121 0.08617 -0.1636 0.7774 0.0269
-9.250 0.3435 0.08918 0.08407 -0.1644 0.7663 0.0269
-9.000 0.3540 0.08715 0.08198 -0.1649 0.7569 0.0272
-8.750 0.3629 0.08520 0.07998 -0.1653 0.7478 0.0275
-8.500 0.3716 0.08325 0.07798 -0.1658 0.7402 0.0276
-8.000 0.3870 0.07938 0.07403 -0.1664 0.7258 0.0277
-7.500 0.3931 0.07394 0.06855 -0.1667 0.7130 0.0192
-7.250 0.3999 0.07201 0.06658 -0.1667 0.7071 0.0189
-7.000 0.4065 0.07030 0.06488 -0.1664 0.7015 0.0184
-6.750 0.4101 0.06837 0.06295 -0.1660 0.6959 0.0181
-6.500 0.4124 0.06638 0.06096 -0.1655 0.6910 0.0181
-6.250 0.4140 0.06457 0.05914 -0.1648 0.6866 0.0179
-6.000 0.4148 0.06268 0.05728 -0.1642 0.6817 0.0177
-5.750 0.4195 0.06052 0.05513 -0.1647 0.6768 0.0178
-5.500 0.4264 0.05811 0.05270 -0.1659 0.6726 0.0178
-5.250 0.4363 0.05539 0.04994 -0.1682 0.6688 0.0185
-4.750 0.5312 0.02238 0.01568 -0.2238 0.6616 0.0208
-4.500 0.5671 0.02019 0.01298 -0.2275 0.6578 0.0222
-4.250 0.5986 0.01919 0.01172 -0.2291 0.6542 0.0237
-4.000 0.6304 0.01842 0.01064 -0.2304 0.6509 0.0263
-3.750 0.6580 0.01796 0.01009 -0.2308 0.6469 0.0294
-3.500 0.6864 0.01751 0.00952 -0.2312 0.6430 0.0334
-3.250 0.7152 0.01714 0.00901 -0.2316 0.6396 0.0383
-3.000 0.7443 0.01687 0.00860 -0.2320 0.6364 0.0442
-2.750 0.7739 0.01669 0.00826 -0.2325 0.6335 0.0507
-2.500 0.8009 0.01654 0.00807 -0.2324 0.6300 0.0575
-2.250 0.8277 0.01642 0.00791 -0.2323 0.6263 0.0644
-2.000 0.8550 0.01632 0.00776 -0.2323 0.6230 0.0715
-1.750 0.8828 0.01624 0.00760 -0.2323 0.6200 0.0792
-1.500 0.9113 0.01620 0.00745 -0.2324 0.6170 0.0878
-1.250 0.9397 0.01622 0.00739 -0.2326 0.6142 0.0967
-1.000 0.9651 0.01622 0.00742 -0.2321 0.6108 0.1052
-0.750 0.9912 0.01624 0.00741 -0.2318 0.6075 0.1143
-0.500 1.0175 0.01631 0.00744 -0.2315 0.6044 0.1240
-0.250 1.0444 0.01636 0.00747 -0.2314 0.6014 0.1329
0.000 1.0723 0.01644 0.00743 -0.2314 0.5986 0.1427
0.250 1.0996 0.01652 0.00751 -0.2313 0.5959 0.1515
0.500 1.1240 0.01661 0.00759 -0.2307 0.5927 0.1604
0.750 1.1490 0.01668 0.00771 -0.2302 0.5895 0.1690
1.000 1.1743 0.01678 0.00776 -0.2298 0.5863 0.1780
1.250 1.2005 0.01685 0.00785 -0.2295 0.5833 0.1869
1.500 1.2281 0.01696 0.00790 -0.2295 0.5808 0.1967
1.750 1.2547 0.01708 0.00803 -0.2294 0.5781 0.2064
2.000 1.2772 0.01721 0.00821 -0.2284 0.5748 0.2162
2.250 1.3006 0.01733 0.00839 -0.2277 0.5714 0.2268
2.500 1.3250 0.01745 0.00855 -0.2271 0.5682 0.2379
2.750 1.3504 0.01759 0.00868 -0.2268 0.5654 0.2512
3.000 1.3775 0.01771 0.00880 -0.2268 0.5628 0.2668
3.250 1.4017 0.01788 0.00902 -0.2262 0.5598 0.2835
3.500 1.4227 0.01805 0.00930 -0.2251 0.5564 0.3042
3.750 1.4451 0.01821 0.00956 -0.2242 0.5530 0.3324
4.000 1.4683 0.01833 0.00978 -0.2235 0.5497 0.3750
4.250 1.4891 0.01778 0.01000 -0.2222 0.5469 0.9314
4.500 1.5163 0.01799 0.01011 -0.2222 0.5443 1.0000
4.750 1.5339 0.01829 0.01045 -0.2204 0.5407 1.0000
5.000 1.5517 0.01856 0.01077 -0.2187 0.5369 1.0000
5.250 1.5711 0.01882 0.01102 -0.2172 0.5334 1.0000
5.500 1.5930 0.01906 0.01123 -0.2162 0.5302 1.0000
5.750 1.6186 0.01929 0.01139 -0.2160 0.5273 1.0000
6.000 1.6322 0.01964 0.01182 -0.2135 0.5233 1.0000
6.250 1.6473 0.01999 0.01224 -0.2114 0.5191 1.0000
6.500 1.6647 0.02029 0.01255 -0.2096 0.5150 1.0000
6.750 1.6865 0.02053 0.01275 -0.2087 0.5114 1.0000
7.000 1.7016 0.02091 0.01318 -0.2066 0.5072 1.0000
7.250 1.7132 0.02136 0.01372 -0.2040 0.5022 1.0000
7.500 1.7287 0.02173 0.01411 -0.2020 0.4977 1.0000
7.750 1.7493 0.02200 0.01434 -0.2010 0.4938 1.0000
8.000 1.7581 0.02260 0.01507 -0.1980 0.4886 1.0000
8.250 1.7692 0.02314 0.01568 -0.1955 0.4833 1.0000
8.500 1.7854 0.02355 0.01608 -0.1938 0.4787 1.0000
8.750 1.7965 0.02417 0.01676 -0.1914 0.4736 1.0000
9.000 1.8048 0.02491 0.01760 -0.1887 0.4678 1.0000
9.250 1.8181 0.02547 0.01816 -0.1867 0.4624 1.0000
9.500 1.8264 0.02630 0.01907 -0.1841 0.4567 1.0000
9.750 1.8333 0.02722 0.02006 -0.1814 0.4503 1.0000
10.000 1.8457 0.02790 0.02075 -0.1795 0.4446 1.0000
10.250 1.8480 0.02918 0.02215 -0.1765 0.4376 1.0000
10.500 1.8553 0.03023 0.02323 -0.1742 0.4310 1.0000
10.750 1.8602 0.03149 0.02456 -0.1717 0.4242 1.0000
11.000 1.8634 0.03293 0.02606 -0.1692 0.4167 1.0000
11.250 1.8683 0.03431 0.02749 -0.1669 0.4094 1.0000
11.500 1.8689 0.03610 0.02936 -0.1644 0.4012 1.0000
11.750 1.8723 0.03774 0.03103 -0.1623 0.3933 1.0000
12.000 1.8718 0.03980 0.03316 -0.1600 0.3846 1.0000
12.250 1.8723 0.04184 0.03524 -0.1579 0.3758 1.0000
12.500 1.8715 0.04409 0.03754 -0.1559 0.3665 1.0000
12.750 1.8697 0.04655 0.04006 -0.1540 0.3571 1.0000
13.000 1.8687 0.04895 0.04245 -0.1522 0.3476 1.0000
13.250 1.8649 0.05180 0.04538 -0.1505 0.3374 1.0000
13.500 1.8618 0.05463 0.04824 -0.1489 0.3272 1.0000
13.750 1.8581 0.05756 0.05118 -0.1474 0.3167 1.0000
14.000 1.8538 0.06073 0.05440 -0.1461 0.3061 1.0000
14.250 1.8496 0.06391 0.05761 -0.1449 0.2958 1.0000
14.500 1.8444 0.06725 0.06095 -0.1437 0.2853 1.0000
14.750 1.8402 0.07063 0.06438 -0.1427 0.2747 1.0000
15.000 1.8357 0.07407 0.06783 -0.1419 0.2649 1.0000
15.250 1.8301 0.07768 0.07145 -0.1411 0.2548 1.0000
15.500 1.8267 0.08113 0.07496 -0.1405 0.2451 1.0000
15.750 1.8219 0.08477 0.07861 -0.1399 0.2361 1.0000
16.000 1.8179 0.08837 0.08225 -0.1395 0.2268 1.0000
16.250 1.8145 0.09193 0.08585 -0.1392 0.2182 1.0000
16.500 1.8098 0.09568 0.08962 -0.1390 0.2096 1.0000
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