EPPLER 422 AIRFOIL (e422-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 422 AIRFOIL (e422-il) Reynolds number: 500,000 Max Cl/Cd: 108.97 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e422-il-500000-n5.txt Download as CSV file: xf-e422-il-500000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 0.0052 0.10187 0.09761 -0.0857 0.6026 0.0159
-10.250 0.0110 0.09882 0.09456 -0.0869 0.5959 0.0159
-9.750 0.0161 0.09061 0.08629 -0.0886 0.5840 0.0104
-9.500 0.0246 0.08850 0.08417 -0.0893 0.5773 0.0103
-9.250 0.0315 0.08610 0.08175 -0.0901 0.5705 0.0102
-9.000 0.0362 0.08332 0.07895 -0.0910 0.5645 0.0100
-8.750 0.0407 0.08043 0.07606 -0.0920 0.5589 0.0099
-8.500 -0.1235 0.05141 0.04716 -0.1033 0.5737 0.0080
-8.250 -0.1695 0.03194 0.02720 -0.1235 0.5740 0.0078
-8.000 -0.1552 0.02582 0.02059 -0.1285 0.5681 0.0078
-7.750 -0.1369 0.02333 0.01776 -0.1294 0.5619 0.0078
-7.500 -0.1162 0.02166 0.01580 -0.1295 0.5550 0.0079
-7.000 -0.0714 0.01922 0.01288 -0.1289 0.5424 0.0080
-6.750 -0.0477 0.01831 0.01177 -0.1286 0.5363 0.0081
-6.250 0.0006 0.01666 0.00978 -0.1277 0.5260 0.0083
-6.000 0.0255 0.01597 0.00897 -0.1273 0.5206 0.0084
-5.750 0.0509 0.01545 0.00833 -0.1269 0.5151 0.0087
-5.500 0.0768 0.01501 0.00778 -0.1265 0.5103 0.0089
-5.250 0.1031 0.01458 0.00726 -0.1261 0.5053 0.0091
-5.000 0.1294 0.01420 0.00677 -0.1257 0.5004 0.0094
-4.750 0.1557 0.01386 0.00632 -0.1253 0.4961 0.0098
-4.500 0.1825 0.01354 0.00590 -0.1249 0.4924 0.0102
-4.250 0.2096 0.01325 0.00553 -0.1246 0.4884 0.0105
-4.000 0.2363 0.01292 0.00514 -0.1242 0.4842 0.0111
-3.750 0.2631 0.01271 0.00484 -0.1239 0.4800 0.0117
-3.500 0.2901 0.01252 0.00457 -0.1235 0.4763 0.0124
-3.250 0.3176 0.01232 0.00431 -0.1233 0.4728 0.0133
-3.000 0.3450 0.01213 0.00408 -0.1230 0.4694 0.0148
-2.750 0.3722 0.01196 0.00388 -0.1226 0.4660 0.0175
-2.500 0.3992 0.01181 0.00369 -0.1223 0.4628 0.0225
-2.250 0.4260 0.01164 0.00352 -0.1220 0.4597 0.0328
-2.000 0.4534 0.01143 0.00337 -0.1217 0.4568 0.0509
-1.750 0.4804 0.01124 0.00328 -0.1215 0.4536 0.0785
-1.500 0.5075 0.01114 0.00324 -0.1212 0.4504 0.1026
-1.250 0.5347 0.01110 0.00322 -0.1209 0.4475 0.1210
-1.000 0.5617 0.01110 0.00322 -0.1206 0.4447 0.1382
-0.750 0.5889 0.01111 0.00323 -0.1203 0.4423 0.1510
-0.500 0.6165 0.01109 0.00323 -0.1201 0.4398 0.1620
-0.250 0.6440 0.01111 0.00323 -0.1199 0.4371 0.1709
0.000 0.6712 0.01111 0.00325 -0.1196 0.4342 0.1796
0.250 0.6983 0.01116 0.00325 -0.1193 0.4315 0.1870
0.500 0.7251 0.01119 0.00328 -0.1190 0.4291 0.1958
0.750 0.7519 0.01126 0.00332 -0.1187 0.4267 0.2042
1.000 0.7790 0.01128 0.00336 -0.1184 0.4247 0.2133
1.250 0.8062 0.01131 0.00341 -0.1182 0.4224 0.2230
1.500 0.8332 0.01134 0.00347 -0.1179 0.4199 0.2341
1.750 0.8600 0.01138 0.00353 -0.1176 0.4174 0.2458
2.000 0.8866 0.01144 0.00360 -0.1173 0.4149 0.2600
2.250 0.9129 0.01150 0.00368 -0.1170 0.4127 0.2757
2.500 0.9390 0.01158 0.00378 -0.1166 0.4106 0.2955
2.750 0.9653 0.01163 0.00389 -0.1163 0.4086 0.3198
3.000 0.9918 0.01165 0.00400 -0.1160 0.4065 0.3494
3.250 1.0180 0.01167 0.00412 -0.1157 0.4042 0.3889
3.500 1.0437 0.01166 0.00426 -0.1153 0.4018 0.4464
4.000 1.1131 0.01100 0.00464 -0.1184 0.3973 1.0000
4.250 1.1379 0.01116 0.00476 -0.1178 0.3951 1.0000
4.500 1.1625 0.01134 0.00490 -0.1172 0.3929 1.0000
4.750 1.1880 0.01146 0.00503 -0.1168 0.3909 1.0000
5.000 1.2132 0.01160 0.00517 -0.1163 0.3888 1.0000
5.250 1.2382 0.01174 0.00533 -0.1158 0.3866 1.0000
5.500 1.2628 0.01190 0.00548 -0.1152 0.3844 1.0000
5.750 1.2871 0.01206 0.00563 -0.1146 0.3820 1.0000
6.000 1.3108 0.01225 0.00580 -0.1139 0.3796 1.0000
6.250 1.3342 0.01246 0.00600 -0.1131 0.3774 1.0000
6.500 1.3586 0.01261 0.00618 -0.1126 0.3754 1.0000
6.750 1.3828 0.01276 0.00637 -0.1120 0.3730 1.0000
7.000 1.4063 0.01293 0.00657 -0.1113 0.3702 1.0000
7.250 1.4293 0.01312 0.00676 -0.1105 0.3674 1.0000
7.500 1.4512 0.01332 0.00696 -0.1095 0.3643 1.0000
7.750 1.4723 0.01356 0.00719 -0.1085 0.3611 1.0000
8.000 1.4952 0.01373 0.00741 -0.1077 0.3582 1.0000
8.250 1.5168 0.01392 0.00764 -0.1067 0.3550 1.0000
8.500 1.5367 0.01413 0.00788 -0.1054 0.3518 1.0000
8.750 1.5548 0.01438 0.00813 -0.1039 0.3486 1.0000
9.000 1.5728 0.01465 0.00842 -0.1023 0.3456 1.0000
9.250 1.5927 0.01486 0.00870 -0.1011 0.3422 1.0000
9.500 1.6111 0.01512 0.00900 -0.0996 0.3382 1.0000
9.750 1.6280 0.01543 0.00933 -0.0980 0.3343 1.0000
10.000 1.6439 0.01579 0.00969 -0.0962 0.3305 1.0000
10.250 1.6625 0.01608 0.01006 -0.0950 0.3267 1.0000
10.500 1.6787 0.01644 0.01046 -0.0934 0.3222 1.0000
10.750 1.6927 0.01690 0.01093 -0.0915 0.3178 1.0000
11.000 1.7081 0.01733 0.01142 -0.0899 0.3136 1.0000
11.250 1.7229 0.01780 0.01194 -0.0883 0.3083 1.0000
11.500 1.7333 0.01845 0.01260 -0.0862 0.3027 1.0000
12.000 1.7566 0.01981 0.01405 -0.0826 0.2910 1.0000
12.250 1.7646 0.02073 0.01499 -0.0806 0.2848 1.0000
12.500 1.7726 0.02171 0.01603 -0.0788 0.2774 1.0000
12.750 1.7772 0.02298 0.01731 -0.0768 0.2704 1.0000
13.000 1.7809 0.02440 0.01877 -0.0750 0.2619 1.0000
13.250 1.7823 0.02609 0.02049 -0.0732 0.2538 1.0000
13.500 1.7790 0.02826 0.02267 -0.0714 0.2448 1.0000
13.750 1.7781 0.03038 0.02483 -0.0700 0.2361 1.0000
14.000 1.7707 0.03317 0.02764 -0.0685 0.2273 1.0000
14.250 1.7617 0.03625 0.03075 -0.0672 0.2183 1.0000
14.500 1.7531 0.03942 0.03396 -0.0661 0.2104 1.0000
14.750 1.7380 0.04337 0.03793 -0.0652 0.2023 1.0000
15.000 1.7294 0.04677 0.04138 -0.0645 0.1952 1.0000
15.250 1.7125 0.05120 0.04585 -0.0639 0.1877 1.0000
15.500 1.7010 0.05517 0.04987 -0.0636 0.1804 1.0000
15.750 1.6864 0.05962 0.05435 -0.0634 0.1745 1.0000
16.000 1.6757 0.06371 0.05849 -0.0634 0.1675 1.0000
16.250 1.6610 0.06838 0.06319 -0.0636 0.1617 1.0000
16.500 1.6526 0.07237 0.06723 -0.0638 0.1552 1.0000
16.750 1.6396 0.07703 0.07191 -0.0642 0.1495 1.0000
17.000 1.6332 0.08089 0.07583 -0.0646 0.1440 1.0000
17.250 1.6223 0.08544 0.08041 -0.0652 0.1381 1.0000
17.500 1.6160 0.08940 0.08443 -0.0658 0.1329 1.0000
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Polar data table (+)
Polar graphs
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