EPPLER 422 AIRFOIL (e422-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 422 AIRFOIL (e422-il) Reynolds number: 1,000,000 Max Cl/Cd: 140.92 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e422-il-1000000.txt Download as CSV file: xf-e422-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 0.0574 0.08731 0.08382 -0.0936 0.5883 0.0141
-9.000 0.0641 0.08486 0.08135 -0.0944 0.5813 0.0145
-8.750 0.0698 0.08216 0.07864 -0.0953 0.5746 0.0148
-8.500 0.0745 0.07945 0.07591 -0.0962 0.5679 0.0151
-8.250 0.0653 0.07351 0.07000 -0.0988 0.5645 0.0159
-8.000 0.0678 0.07039 0.06689 -0.0999 0.5590 0.0159
-7.750 0.0626 0.06659 0.06311 -0.1008 0.5541 0.0161
-7.500 0.0646 0.06424 0.06074 -0.1012 0.5479 0.0162
-7.250 -0.0641 0.02405 0.01955 -0.1322 0.5609 0.0106
-7.000 -0.0494 0.02114 0.01641 -0.1321 0.5544 0.0101
-6.750 -0.0311 0.01897 0.01390 -0.1317 0.5476 0.0099
-6.500 -0.0098 0.01729 0.01195 -0.1312 0.5419 0.0097
-6.250 0.0131 0.01609 0.01051 -0.1306 0.5356 0.0096
-6.000 0.0368 0.01512 0.00933 -0.1299 0.5295 0.0095
-5.750 0.0618 0.01428 0.00834 -0.1294 0.5246 0.0095
-5.500 0.0871 0.01362 0.00754 -0.1289 0.5192 0.0095
-5.250 0.1125 0.01309 0.00687 -0.1283 0.5133 0.0095
-5.000 0.1389 0.01258 0.00627 -0.1279 0.5089 0.0096
-4.750 0.1654 0.01214 0.00574 -0.1275 0.5040 0.0097
-4.500 0.1918 0.01178 0.00527 -0.1270 0.4989 0.0099
-4.250 0.2185 0.01148 0.00488 -0.1266 0.4941 0.0101
-4.000 0.2460 0.01120 0.00454 -0.1263 0.4907 0.0104
-3.750 0.2728 0.01077 0.00403 -0.1259 0.4867 0.0110
-3.500 0.3000 0.01055 0.00375 -0.1256 0.4827 0.0117
-3.250 0.3270 0.01042 0.00355 -0.1252 0.4778 0.0126
-3.000 0.3548 0.01019 0.00328 -0.1249 0.4749 0.0137
-2.750 0.3826 0.01001 0.00307 -0.1247 0.4716 0.0153
-2.500 0.4102 0.00983 0.00287 -0.1244 0.4682 0.0186
-2.250 0.4373 0.00961 0.00266 -0.1241 0.4648 0.0314
-2.000 0.4638 0.00941 0.00254 -0.1237 0.4609 0.0601
-1.750 0.4913 0.00925 0.00247 -0.1235 0.4584 0.0876
-1.500 0.5192 0.00915 0.00244 -0.1233 0.4559 0.1078
-1.250 0.5469 0.00909 0.00243 -0.1231 0.4529 0.1263
-1.000 0.5745 0.00907 0.00243 -0.1229 0.4498 0.1418
-0.750 0.6019 0.00910 0.00245 -0.1227 0.4467 0.1543
-0.500 0.6288 0.00916 0.00251 -0.1224 0.4432 0.1669
-0.250 0.6568 0.00914 0.00251 -0.1222 0.4414 0.1769
0.000 0.6848 0.00915 0.00253 -0.1221 0.4393 0.1856
0.250 0.7126 0.00914 0.00253 -0.1219 0.4368 0.1949
0.500 0.7402 0.00916 0.00255 -0.1217 0.4342 0.2031
0.750 0.7674 0.00919 0.00257 -0.1214 0.4316 0.2126
1.000 0.7943 0.00926 0.00262 -0.1211 0.4286 0.2217
1.250 0.8211 0.00933 0.00270 -0.1208 0.4258 0.2331
1.500 0.8489 0.00933 0.00273 -0.1207 0.4243 0.2446
1.750 0.8764 0.00934 0.00278 -0.1205 0.4223 0.2596
2.000 0.9038 0.00934 0.00283 -0.1204 0.4201 0.2780
2.250 0.9308 0.00935 0.00289 -0.1201 0.4177 0.3017
2.500 0.9575 0.00938 0.00297 -0.1199 0.4154 0.3328
2.750 0.9837 0.00942 0.00308 -0.1195 0.4129 0.3706
3.000 1.0093 0.00948 0.00323 -0.1191 0.4099 0.4250
3.250 1.0279 0.00876 0.00342 -0.1174 0.4084 0.8005
3.500 1.0856 0.00862 0.00357 -0.1238 0.4063 1.0000
3.750 1.1115 0.00871 0.00364 -0.1233 0.4042 1.0000
4.000 1.1372 0.00880 0.00372 -0.1228 0.4021 1.0000
4.250 1.1626 0.00892 0.00381 -0.1223 0.4000 1.0000
4.500 1.1877 0.00905 0.00392 -0.1218 0.3977 1.0000
4.750 1.2121 0.00922 0.00405 -0.1211 0.3949 1.0000
5.000 1.2371 0.00938 0.00419 -0.1206 0.3925 1.0000
5.250 1.2629 0.00946 0.00429 -0.1202 0.3909 1.0000
5.500 1.2885 0.00955 0.00440 -0.1197 0.3890 1.0000
5.750 1.3139 0.00965 0.00450 -0.1193 0.3868 1.0000
6.000 1.3389 0.00977 0.00462 -0.1188 0.3844 1.0000
6.250 1.3634 0.00991 0.00475 -0.1182 0.3819 1.0000
6.500 1.3867 0.01012 0.00492 -0.1174 0.3785 1.0000
6.750 1.4113 0.01025 0.00507 -0.1169 0.3759 1.0000
7.000 1.4365 0.01034 0.00519 -0.1165 0.3736 1.0000
7.250 1.4612 0.01044 0.00532 -0.1160 0.3711 1.0000
7.500 1.4852 0.01058 0.00546 -0.1154 0.3683 1.0000
7.750 1.5083 0.01075 0.00562 -0.1146 0.3654 1.0000
8.000 1.5300 0.01100 0.00585 -0.1136 0.3619 1.0000
8.250 1.5541 0.01110 0.00600 -0.1131 0.3596 1.0000
8.500 1.5781 0.01121 0.00615 -0.1125 0.3568 1.0000
8.750 1.6009 0.01136 0.00631 -0.1117 0.3536 1.0000
9.000 1.6216 0.01155 0.00651 -0.1106 0.3503 1.0000
9.250 1.6396 0.01181 0.00676 -0.1089 0.3467 1.0000
9.500 1.6611 0.01195 0.00694 -0.1079 0.3440 1.0000
9.750 1.6822 0.01210 0.00714 -0.1068 0.3408 1.0000
10.000 1.7016 0.01230 0.00736 -0.1055 0.3371 1.0000
10.250 1.7185 0.01259 0.00764 -0.1038 0.3330 1.0000
10.500 1.7377 0.01282 0.00791 -0.1025 0.3293 1.0000
10.750 1.7577 0.01303 0.00816 -0.1014 0.3252 1.0000
11.000 1.7750 0.01333 0.00847 -0.0999 0.3207 1.0000
11.250 1.7899 0.01372 0.00886 -0.0980 0.3160 1.0000
11.500 1.8093 0.01396 0.00916 -0.0969 0.3116 1.0000
11.750 1.8249 0.01435 0.00956 -0.0952 0.3058 1.0000
12.000 1.8382 0.01483 0.01005 -0.0933 0.3005 1.0000
12.250 1.8544 0.01522 0.01048 -0.0919 0.2945 1.0000
12.500 1.8639 0.01590 0.01115 -0.0895 0.2874 1.0000
12.750 1.8779 0.01641 0.01170 -0.0879 0.2808 1.0000
13.000 1.8843 0.01731 0.01258 -0.0855 0.2728 1.0000
13.250 1.8942 0.01809 0.01339 -0.0836 0.2643 1.0000
13.500 1.8983 0.01924 0.01454 -0.0812 0.2553 1.0000
13.750 1.9005 0.02059 0.01589 -0.0789 0.2459 1.0000
14.000 1.9021 0.02211 0.01741 -0.0767 0.2360 1.0000
14.250 1.8991 0.02406 0.01936 -0.0745 0.2260 1.0000
14.500 1.8919 0.02649 0.02178 -0.0723 0.2157 1.0000
14.750 1.8869 0.02893 0.02424 -0.0707 0.2065 1.0000
15.000 1.8781 0.03182 0.02714 -0.0691 0.1977 1.0000
15.250 1.8648 0.03527 0.03061 -0.0676 0.1895 1.0000
15.500 1.8566 0.03839 0.03377 -0.0665 0.1824 1.0000
15.750 1.8401 0.04242 0.03783 -0.0654 0.1756 1.0000
16.000 1.8293 0.04602 0.04148 -0.0647 0.1689 1.0000
16.250 1.8108 0.05058 0.04607 -0.0640 0.1628 1.0000
16.500 1.8008 0.05432 0.04987 -0.0636 0.1572 1.0000
16.750 1.7827 0.05905 0.05463 -0.0634 0.1510 1.0000
17.000 1.7707 0.06324 0.05887 -0.0633 0.1456 1.0000
17.250 1.7570 0.06770 0.06338 -0.0634 0.1403 1.0000
17.500 1.7421 0.07242 0.06813 -0.0636 0.1351 1.0000
17.750 1.7332 0.07649 0.07225 -0.0639 0.1302 1.0000
18.000 1.7173 0.08151 0.07728 -0.0645 0.1246 1.0000
18.250 1.7106 0.08543 0.08127 -0.0650 0.1203 1.0000
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Polar data table (+)
Polar graphs
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