EPPLER 422 AIRFOIL (e422-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: EPPLER 422 AIRFOIL (e422-il) Reynolds number: 100,000 Max Cl/Cd: 46.71 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e422-il-100000-n5.txt Download as CSV file: xf-e422-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 0.0391 0.08810 0.08223 -0.0873 0.7118 0.0305
-8.250 0.0418 0.08465 0.07875 -0.0891 0.7010 0.0302
-8.000 0.0532 0.08259 0.07664 -0.0895 0.6900 0.0296
-7.750 0.0572 0.07958 0.07360 -0.0908 0.6805 0.0297
-7.500 0.0611 0.07668 0.07069 -0.0920 0.6719 0.0297
-7.250 0.0627 0.07367 0.06768 -0.0931 0.6632 0.0298
-7.000 0.0624 0.07077 0.06476 -0.0940 0.6560 0.0299
-6.750 0.0643 0.06809 0.06210 -0.0951 0.6481 0.0297
-6.500 0.0675 0.06463 0.05860 -0.0974 0.6417 0.0296
-6.250 0.0741 0.06135 0.05530 -0.0999 0.6351 0.0292
-6.000 0.0806 0.05702 0.05094 -0.1036 0.6288 0.0289
-5.750 0.0882 0.05104 0.04485 -0.1092 0.6239 0.0285
-5.500 0.0896 0.03387 0.02660 -0.1242 0.6221 0.0271
-5.250 0.1092 0.03063 0.02282 -0.1254 0.6156 0.0275
-5.000 0.1311 0.02840 0.02013 -0.1256 0.6090 0.0282
-4.750 0.1546 0.02665 0.01789 -0.1254 0.6035 0.0290
-4.500 0.1786 0.02521 0.01605 -0.1250 0.5970 0.0301
-4.250 0.2030 0.02439 0.01513 -0.1246 0.5907 0.0317
-4.000 0.2287 0.02355 0.01396 -0.1242 0.5856 0.0348
-3.750 0.2538 0.02293 0.01327 -0.1238 0.5801 0.0377
-3.500 0.2791 0.02224 0.01243 -0.1234 0.5745 0.0412
-3.250 0.3052 0.02165 0.01168 -0.1230 0.5695 0.0467
-3.000 0.3316 0.02112 0.01103 -0.1226 0.5651 0.0560
-2.750 0.3573 0.02062 0.01055 -0.1223 0.5595 0.0729
-2.500 0.3838 0.02033 0.01031 -0.1220 0.5545 0.1005
-2.250 0.4111 0.02037 0.01028 -0.1217 0.5504 0.1296
-2.000 0.4383 0.02051 0.01028 -0.1215 0.5465 0.1534
-1.750 0.4643 0.02063 0.01035 -0.1210 0.5416 0.1714
-1.500 0.4909 0.02069 0.01029 -0.1206 0.5371 0.1873
-1.250 0.5176 0.02068 0.01020 -0.1203 0.5332 0.2004
-1.000 0.5449 0.02065 0.01005 -0.1200 0.5298 0.2126
-0.750 0.5705 0.02068 0.01002 -0.1195 0.5254 0.2247
-0.500 0.5966 0.02069 0.01004 -0.1191 0.5215 0.2361
-0.250 0.6232 0.02070 0.00998 -0.1188 0.5179 0.2481
0.000 0.6506 0.02072 0.00989 -0.1186 0.5147 0.2614
0.250 0.6774 0.02075 0.00988 -0.1183 0.5115 0.2748
0.500 0.7022 0.02085 0.01004 -0.1177 0.5074 0.2887
0.750 0.7284 0.02095 0.01014 -0.1174 0.5036 0.3051
1.000 0.7553 0.02104 0.01023 -0.1171 0.5004 0.3240
1.250 0.7827 0.02112 0.01029 -0.1170 0.4976 0.3471
1.500 0.8105 0.02118 0.01033 -0.1169 0.4951 0.3768
1.750 0.8342 0.02132 0.01063 -0.1163 0.4914 0.4159
2.000 0.8574 0.02133 0.01092 -0.1155 0.4877 0.4890
2.500 0.9240 0.02102 0.01125 -0.1176 0.4814 1.0000
2.750 0.9506 0.02132 0.01139 -0.1173 0.4790 1.0000
3.000 0.9763 0.02166 0.01161 -0.1170 0.4765 1.0000
3.250 0.9971 0.02215 0.01213 -0.1159 0.4728 1.0000
3.500 1.0195 0.02257 0.01254 -0.1151 0.4694 1.0000
3.750 1.0432 0.02296 0.01288 -0.1144 0.4664 1.0000
4.000 1.0681 0.02332 0.01317 -0.1139 0.4639 1.0000
4.250 1.0942 0.02364 0.01340 -0.1136 0.4617 1.0000
4.500 1.1194 0.02403 0.01373 -0.1132 0.4594 1.0000
4.750 1.1365 0.02468 0.01448 -0.1117 0.4556 1.0000
5.000 1.1564 0.02523 0.01507 -0.1106 0.4522 1.0000
5.250 1.1783 0.02570 0.01555 -0.1098 0.4494 1.0000
5.500 1.2019 0.02612 0.01595 -0.1092 0.4470 1.0000
5.750 1.2276 0.02646 0.01625 -0.1089 0.4447 1.0000
6.000 1.2533 0.02683 0.01656 -0.1087 0.4425 1.0000
6.250 1.2639 0.02776 0.01767 -0.1064 0.4386 1.0000
6.500 1.2797 0.02851 0.01851 -0.1048 0.4353 1.0000
6.750 1.2987 0.02910 0.01916 -0.1037 0.4324 1.0000
7.000 1.3210 0.02952 0.01960 -0.1030 0.4298 1.0000
7.250 1.3472 0.02982 0.01985 -0.1028 0.4276 1.0000
7.500 1.3688 0.03035 0.02042 -0.1021 0.4252 1.0000
7.750 1.3682 0.03174 0.02204 -0.0985 0.4209 1.0000
8.000 1.3776 0.03270 0.02310 -0.0963 0.4173 1.0000
8.250 1.3948 0.03327 0.02372 -0.0950 0.4143 1.0000
8.500 1.4187 0.03357 0.02403 -0.0945 0.4119 1.0000
8.750 1.4495 0.03365 0.02408 -0.0949 0.4098 1.0000
9.000 1.4203 0.03601 0.02671 -0.0880 0.4047 1.0000
9.250 1.4082 0.03783 0.02866 -0.0836 0.4002 1.0000
9.500 1.4234 0.03843 0.02930 -0.0823 0.3972 1.0000
9.750 1.4537 0.03828 0.02917 -0.0824 0.3948 1.0000
10.000 1.2178 0.06080 0.05213 -0.0727 0.3707 1.0000
10.250 1.2749 0.05668 0.04803 -0.0717 0.3733 1.0000
10.500 1.3318 0.05301 0.04436 -0.0711 0.3746 1.0000
10.750 1.4019 0.04859 0.03992 -0.0714 0.3760 1.0000
13.750 1.1994 0.10890 0.10120 -0.0733 0.2760 1.0000
14.000 1.2219 0.10843 0.10079 -0.0726 0.2742 1.0000
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Polar data table (+)
Polar graphs
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