EPPLER 422 AIRFOIL (e422-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 422 AIRFOIL (e422-il) Reynolds number: 500,000 Max Cl/Cd: 105.84 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e422-il-500000.txt Download as CSV file: xf-e422-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 422 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 0.0323 0.10070 0.09707 -0.0880 0.6999 0.0213
-10.000 0.0376 0.09800 0.09430 -0.0889 0.6857 0.0218
-9.500 0.0349 0.09086 0.08709 -0.0928 0.6640 0.0225
-9.250 0.0457 0.08886 0.08503 -0.0926 0.6519 0.0227
-8.750 0.0663 0.08503 0.08111 -0.0928 0.6301 0.0233
-8.250 0.0798 0.08041 0.07643 -0.0940 0.6131 0.0243
-8.000 0.0853 0.07801 0.07401 -0.0948 0.6055 0.0247
-7.750 0.0692 0.07234 0.06837 -0.0989 0.6018 0.0261
-7.500 0.0724 0.06955 0.06560 -0.0993 0.5950 0.0263
-7.250 0.0818 0.06809 0.06410 -0.0987 0.5874 0.0265
-7.000 0.0885 0.06639 0.06239 -0.0985 0.5810 0.0268
-6.750 0.0916 0.06461 0.06062 -0.0983 0.5746 0.0271
-6.500 0.0970 0.06244 0.05842 -0.0992 0.5687 0.0277
-6.250 0.0285 0.02412 0.01871 -0.1306 0.5773 0.0158
-6.000 0.0472 0.02179 0.01606 -0.1303 0.5708 0.0154
-5.750 0.0680 0.01986 0.01376 -0.1298 0.5647 0.0151
-5.500 0.0909 0.01832 0.01192 -0.1292 0.5586 0.0148
-5.250 0.1147 0.01718 0.01051 -0.1285 0.5526 0.0147
-5.000 0.1393 0.01629 0.00938 -0.1279 0.5471 0.0148
-4.750 0.1650 0.01552 0.00847 -0.1273 0.5419 0.0150
-4.500 0.1908 0.01491 0.00770 -0.1268 0.5366 0.0154
-4.250 0.2167 0.01446 0.00709 -0.1262 0.5315 0.0158
-4.000 0.2423 0.01379 0.00636 -0.1257 0.5268 0.0165
-3.750 0.2688 0.01339 0.00593 -0.1253 0.5219 0.0174
-3.500 0.2955 0.01308 0.00552 -0.1249 0.5173 0.0184
-3.250 0.3219 0.01277 0.00510 -0.1244 0.5128 0.0196
-3.000 0.3492 0.01247 0.00479 -0.1241 0.5092 0.0214
-2.750 0.3764 0.01217 0.00445 -0.1238 0.5053 0.0244
-2.500 0.4034 0.01189 0.00414 -0.1234 0.5013 0.0321
-2.250 0.4296 0.01141 0.00380 -0.1230 0.4975 0.0756
-2.000 0.4567 0.01132 0.00377 -0.1227 0.4937 0.1079
-1.750 0.4843 0.01125 0.00377 -0.1225 0.4903 0.1282
-1.500 0.5119 0.01125 0.00378 -0.1223 0.4869 0.1444
-1.250 0.5395 0.01128 0.00379 -0.1221 0.4836 0.1579
-1.000 0.5670 0.01137 0.00383 -0.1218 0.4804 0.1710
-0.750 0.5945 0.01147 0.00390 -0.1216 0.4769 0.1826
-0.500 0.6220 0.01143 0.00389 -0.1214 0.4742 0.1930
-0.250 0.6495 0.01146 0.00390 -0.1211 0.4711 0.2028
0.000 0.6767 0.01143 0.00389 -0.1209 0.4681 0.2125
0.250 0.7041 0.01148 0.00390 -0.1206 0.4654 0.2221
0.500 0.7312 0.01152 0.00392 -0.1204 0.4626 0.2328
0.750 0.7587 0.01165 0.00400 -0.1202 0.4596 0.2435
1.000 0.7856 0.01162 0.00404 -0.1199 0.4573 0.2565
1.250 0.8126 0.01161 0.00408 -0.1197 0.4546 0.2708
1.500 0.8395 0.01162 0.00414 -0.1194 0.4518 0.2882
1.750 0.8664 0.01165 0.00420 -0.1191 0.4493 0.3105
2.000 0.8931 0.01168 0.00429 -0.1189 0.4468 0.3407
2.250 0.9198 0.01176 0.00443 -0.1187 0.4441 0.3849
2.500 0.9458 0.01172 0.00460 -0.1184 0.4418 0.4635
2.750 0.9950 0.01083 0.00481 -0.1230 0.4391 1.0000
3.000 1.0208 0.01095 0.00489 -0.1225 0.4366 1.0000
3.250 1.0467 0.01108 0.00498 -0.1220 0.4341 1.0000
3.500 1.0725 0.01122 0.00508 -0.1216 0.4319 1.0000
3.750 1.0984 0.01139 0.00520 -0.1212 0.4296 1.0000
4.000 1.1247 0.01165 0.00538 -0.1209 0.4269 1.0000
4.250 1.1503 0.01182 0.00555 -0.1205 0.4247 1.0000
4.500 1.1754 0.01193 0.00569 -0.1199 0.4225 1.0000
4.750 1.2007 0.01207 0.00583 -0.1194 0.4202 1.0000
5.000 1.2261 0.01223 0.00598 -0.1190 0.4179 1.0000
5.250 1.2513 0.01238 0.00612 -0.1185 0.4156 1.0000
5.500 1.2766 0.01255 0.00627 -0.1181 0.4132 1.0000
5.750 1.3025 0.01282 0.00649 -0.1178 0.4106 1.0000
6.000 1.3277 0.01305 0.00673 -0.1174 0.4084 1.0000
6.250 1.3517 0.01319 0.00692 -0.1167 0.4062 1.0000
6.500 1.3758 0.01334 0.00710 -0.1161 0.4037 1.0000
6.750 1.4000 0.01349 0.00727 -0.1155 0.4011 1.0000
7.000 1.4242 0.01365 0.00744 -0.1150 0.3986 1.0000
7.250 1.4484 0.01385 0.00761 -0.1144 0.3959 1.0000
7.500 1.4735 0.01417 0.00790 -0.1141 0.3927 1.0000
7.750 1.4951 0.01427 0.00810 -0.1131 0.3902 1.0000
8.000 1.5175 0.01443 0.00830 -0.1122 0.3874 1.0000
8.250 1.5400 0.01459 0.00850 -0.1114 0.3845 1.0000
8.500 1.5622 0.01476 0.00869 -0.1105 0.3817 1.0000
8.750 1.5852 0.01501 0.00891 -0.1098 0.3787 1.0000
9.000 1.6070 0.01527 0.00921 -0.1090 0.3758 1.0000
9.250 1.6263 0.01543 0.00946 -0.1076 0.3727 1.0000
9.500 1.6458 0.01560 0.00968 -0.1063 0.3694 1.0000
9.750 1.6644 0.01578 0.00990 -0.1048 0.3662 1.0000
10.000 1.6831 0.01605 0.01015 -0.1034 0.3629 1.0000
10.250 1.7000 0.01632 0.01048 -0.1017 0.3598 1.0000
10.500 1.7144 0.01654 0.01079 -0.0996 0.3563 1.0000
10.750 1.7298 0.01679 0.01111 -0.0977 0.3527 1.0000
11.000 1.7451 0.01709 0.01142 -0.0959 0.3492 1.0000
11.250 1.7605 0.01748 0.01182 -0.0941 0.3453 1.0000
11.500 1.7735 0.01781 0.01227 -0.0920 0.3412 1.0000
11.750 1.7869 0.01819 0.01272 -0.0901 0.3369 1.0000
12.000 1.7989 0.01869 0.01322 -0.0881 0.3327 1.0000
12.250 1.8108 0.01921 0.01383 -0.0862 0.3281 1.0000
12.500 1.8221 0.01978 0.01448 -0.0843 0.3230 1.0000
12.750 1.8303 0.02053 0.01524 -0.0821 0.3179 1.0000
13.000 1.8399 0.02130 0.01610 -0.0803 0.3125 1.0000
13.250 1.8477 0.02221 0.01707 -0.0784 0.3065 1.0000
13.500 1.8519 0.02340 0.01828 -0.0763 0.3009 1.0000
13.750 1.8590 0.02454 0.01952 -0.0748 0.2941 1.0000
14.000 1.8590 0.02620 0.02118 -0.0728 0.2873 1.0000
14.250 1.8633 0.02771 0.02279 -0.0714 0.2800 1.0000
14.500 1.8586 0.02997 0.02505 -0.0696 0.2722 1.0000
14.750 1.8575 0.03212 0.02728 -0.0684 0.2635 1.0000
15.000 1.8503 0.03488 0.03007 -0.0670 0.2553 1.0000
15.250 1.8398 0.03810 0.03332 -0.0658 0.2462 1.0000
15.500 1.8301 0.04139 0.03666 -0.0648 0.2374 1.0000
15.750 1.8132 0.04550 0.04078 -0.0639 0.2285 1.0000
16.000 1.7985 0.04959 0.04492 -0.0633 0.2198 1.0000
16.250 1.7830 0.05389 0.04925 -0.0629 0.2116 1.0000
16.500 1.7631 0.05883 0.05419 -0.0626 0.2035 1.0000
16.750 1.7504 0.06310 0.05852 -0.0626 0.1955 1.0000
17.000 1.7314 0.06820 0.06362 -0.0628 0.1883 1.0000
17.250 1.7197 0.07256 0.06804 -0.0630 0.1808 1.0000
17.500 1.7037 0.07753 0.07302 -0.0635 0.1740 1.0000
17.750 1.6924 0.08202 0.07755 -0.0640 0.1670 1.0000
18.000 1.6796 0.08675 0.08230 -0.0647 0.1608 1.0000
18.250 1.6708 0.09106 0.08665 -0.0655 0.1540 1.0000
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Polar data table (+)
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