EPPLER 428 AIRFOIL (e428-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 428 AIRFOIL (e428-il) Reynolds number: 500,000 Max Cl/Cd: 73.17 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e428-il-500000-n5.txt Download as CSV file: xf-e428-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 428 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
------ -------- --------- --------- -------- -------- --------
-15.250 -1.0193 0.08640 0.08222 -0.0070 1.0000 0.0090
-15.000 -1.0337 0.08042 0.07616 -0.0103 1.0000 0.0090
-14.750 -1.0516 0.07404 0.06969 -0.0137 1.0000 0.0090
-14.500 -1.0702 0.06752 0.06307 -0.0174 1.0000 0.0090
-14.250 -1.0929 0.06034 0.05577 -0.0215 1.0000 0.0090
-14.000 -1.1075 0.05417 0.04947 -0.0251 1.0000 0.0089
-13.750 -1.1263 0.04714 0.04230 -0.0298 1.0000 0.0090
-13.500 -1.1409 0.04091 0.03590 -0.0344 1.0000 0.0090
-13.250 -1.1520 0.03596 0.03080 -0.0379 1.0000 0.0090
-13.000 -1.1620 0.03233 0.02703 -0.0394 1.0000 0.0091
-12.750 -1.1679 0.03011 0.02469 -0.0385 1.0000 0.0092
-12.500 -1.1697 0.02844 0.02293 -0.0364 1.0000 0.0093
-12.250 -1.1615 0.02705 0.02145 -0.0351 1.0000 0.0094
-12.000 -1.1504 0.02576 0.02007 -0.0339 1.0000 0.0096
-11.750 -1.1364 0.02461 0.01882 -0.0329 1.0000 0.0098
-11.500 -1.1205 0.02355 0.01767 -0.0319 1.0000 0.0099
-11.250 -1.1033 0.02255 0.01659 -0.0310 1.0000 0.0101
-11.000 -1.0847 0.02164 0.01558 -0.0302 1.0000 0.0103
-10.750 -1.0651 0.02078 0.01464 -0.0294 1.0000 0.0105
-10.500 -1.0445 0.01999 0.01377 -0.0287 1.0000 0.0107
-10.250 -1.0230 0.01927 0.01297 -0.0280 1.0000 0.0109
-10.000 -1.0013 0.01855 0.01217 -0.0273 1.0000 0.0111
-9.750 -0.9796 0.01778 0.01132 -0.0266 1.0000 0.0114
-9.500 -0.9571 0.01711 0.01058 -0.0259 1.0000 0.0118
-9.250 -0.9339 0.01651 0.00993 -0.0252 1.0000 0.0123
-9.000 -0.9103 0.01597 0.00932 -0.0246 1.0000 0.0128
-8.750 -0.8863 0.01548 0.00877 -0.0240 1.0000 0.0134
-8.500 -0.8626 0.01494 0.00819 -0.0233 1.0000 0.0143
-8.250 -0.8388 0.01440 0.00762 -0.0227 1.0000 0.0161
-7.750 -0.7938 0.01290 0.00633 -0.0212 1.0000 0.0461
-7.500 -0.7693 0.01251 0.00595 -0.0205 1.0000 0.0530
-7.250 -0.7446 0.01215 0.00560 -0.0199 1.0000 0.0591
-7.000 -0.7201 0.01179 0.00525 -0.0192 1.0000 0.0652
-6.750 -0.6956 0.01142 0.00493 -0.0185 1.0000 0.0729
-6.500 -0.6713 0.01107 0.00464 -0.0178 1.0000 0.0845
-6.250 -0.6467 0.01076 0.00438 -0.0171 1.0000 0.0968
-6.000 -0.6220 0.01048 0.00414 -0.0164 1.0000 0.1064
-5.750 -0.5973 0.01022 0.00392 -0.0157 1.0000 0.1146
-5.500 -0.5658 0.00998 0.00371 -0.0164 0.9964 0.1240
-5.250 -0.5315 0.00975 0.00351 -0.0177 0.9888 0.1341
-5.000 -0.4958 0.00952 0.00333 -0.0192 0.9811 0.1454
-4.750 -0.4602 0.00930 0.00317 -0.0207 0.9700 0.1575
-4.500 -0.4239 0.00913 0.00302 -0.0223 0.9545 0.1670
-4.250 -0.3864 0.00897 0.00287 -0.0241 0.9313 0.1765
-4.000 -0.3512 0.00885 0.00270 -0.0254 0.8937 0.1850
-3.750 -0.3236 0.00885 0.00256 -0.0248 0.8475 0.1924
-3.500 -0.2978 0.00886 0.00244 -0.0240 0.8079 0.1984
-3.250 -0.2716 0.00887 0.00233 -0.0233 0.7746 0.2060
-3.000 -0.2451 0.00886 0.00223 -0.0228 0.7446 0.2137
-2.750 -0.2185 0.00886 0.00213 -0.0222 0.7140 0.2222
-2.250 -0.1648 0.00888 0.00195 -0.0213 0.6526 0.2349
-2.000 -0.1375 0.00889 0.00187 -0.0209 0.6282 0.2411
-1.750 -0.1100 0.00887 0.00180 -0.0206 0.6059 0.2474
-1.500 -0.0826 0.00888 0.00174 -0.0203 0.5811 0.2547
-1.250 -0.0551 0.00889 0.00168 -0.0200 0.5578 0.2624
-1.000 -0.0277 0.00889 0.00163 -0.0197 0.5336 0.2718
-0.750 -0.0003 0.00891 0.00159 -0.0193 0.5064 0.2811
-0.500 0.0270 0.00895 0.00157 -0.0190 0.4789 0.2924
-0.250 0.0543 0.00895 0.00155 -0.0188 0.4535 0.3091
0.000 0.0814 0.00896 0.00154 -0.0185 0.4255 0.3303
0.250 0.1083 0.00899 0.00155 -0.0182 0.3920 0.3539
0.500 0.1351 0.00906 0.00157 -0.0179 0.3521 0.3805
0.750 0.1616 0.00914 0.00161 -0.0175 0.3131 0.4152
1.000 0.1883 0.00919 0.00167 -0.0172 0.2838 0.4527
1.250 0.2152 0.00924 0.00174 -0.0169 0.2631 0.4867
1.500 0.2422 0.00929 0.00183 -0.0166 0.2472 0.5189
1.750 0.2693 0.00932 0.00192 -0.0162 0.2346 0.5511
2.000 0.2963 0.00935 0.00202 -0.0159 0.2246 0.5852
2.500 0.3503 0.00942 0.00223 -0.0151 0.2085 0.6473
2.750 0.3773 0.00946 0.00234 -0.0147 0.2013 0.6755
3.000 0.4040 0.00952 0.00247 -0.0143 0.1940 0.7063
3.250 0.4306 0.00954 0.00260 -0.0137 0.1877 0.7376
3.500 0.4568 0.00960 0.00273 -0.0132 0.1811 0.7687
3.750 0.4825 0.00962 0.00287 -0.0124 0.1757 0.8060
4.000 0.5077 0.00963 0.00302 -0.0115 0.1704 0.8486
4.250 0.5336 0.00968 0.00316 -0.0108 0.1644 0.8987
4.500 0.5788 0.00977 0.00333 -0.0142 0.1580 0.9669
4.750 0.6133 0.00996 0.00349 -0.0155 0.1525 1.0000
5.000 0.6397 0.01016 0.00366 -0.0150 0.1474 1.0000
5.250 0.6664 0.01032 0.00383 -0.0146 0.1431 1.0000
5.500 0.6930 0.01052 0.00401 -0.0142 0.1390 1.0000
5.750 0.7194 0.01075 0.00421 -0.0138 0.1349 1.0000
6.000 0.7461 0.01093 0.00441 -0.0134 0.1314 1.0000
6.250 0.7726 0.01114 0.00461 -0.0130 0.1261 1.0000
6.500 0.7988 0.01139 0.00483 -0.0126 0.1203 1.0000
6.750 0.8254 0.01160 0.00505 -0.0122 0.1155 1.0000
7.000 0.8515 0.01186 0.00529 -0.0118 0.1100 1.0000
7.250 0.8777 0.01211 0.00555 -0.0114 0.1048 1.0000
7.500 0.9035 0.01240 0.00582 -0.0110 0.0977 1.0000
7.750 0.9292 0.01270 0.00610 -0.0105 0.0905 1.0000
8.000 0.9546 0.01305 0.00642 -0.0101 0.0828 1.0000
8.250 0.9796 0.01343 0.00678 -0.0096 0.0756 1.0000
8.500 1.0047 0.01380 0.00714 -0.0091 0.0696 1.0000
8.750 1.0292 0.01423 0.00755 -0.0085 0.0641 1.0000
9.000 1.0537 0.01466 0.00798 -0.0080 0.0596 1.0000
9.250 1.0780 0.01510 0.00843 -0.0074 0.0559 1.0000
9.500 1.1022 0.01552 0.00888 -0.0068 0.0527 1.0000
9.750 1.1257 0.01603 0.00940 -0.0062 0.0497 1.0000
10.000 1.1498 0.01644 0.00986 -0.0056 0.0471 1.0000
10.250 1.1726 0.01699 0.01041 -0.0049 0.0432 1.0000
10.500 1.1957 0.01748 0.01094 -0.0042 0.0388 1.0000
10.750 1.2179 0.01806 0.01153 -0.0035 0.0327 1.0000
11.000 1.2377 0.01889 0.01230 -0.0026 0.0238 1.0000
11.250 1.2569 0.01974 0.01314 -0.0016 0.0207 1.0000
11.500 1.2762 0.02053 0.01399 -0.0006 0.0192 1.0000
11.750 1.2953 0.02129 0.01482 0.0005 0.0183 1.0000
12.000 1.3129 0.02215 0.01574 0.0016 0.0174 1.0000
12.250 1.3287 0.02310 0.01678 0.0029 0.0167 1.0000
12.500 1.3440 0.02403 0.01778 0.0043 0.0162 1.0000
12.750 1.3584 0.02493 0.01878 0.0057 0.0158 1.0000
13.000 1.3707 0.02591 0.01986 0.0073 0.0154 1.0000
13.250 1.3775 0.02696 0.02101 0.0096 0.0151 1.0000
13.500 1.3814 0.02815 0.02230 0.0121 0.0148 1.0000
13.750 1.3827 0.02961 0.02385 0.0142 0.0146 1.0000
14.000 1.3814 0.03146 0.02581 0.0157 0.0144 1.0000
14.250 1.3780 0.03378 0.02825 0.0164 0.0142 1.0000
14.500 1.3728 0.03668 0.03127 0.0162 0.0141 1.0000
14.750 1.3651 0.04030 0.03503 0.0151 0.0140 1.0000
15.000 1.3510 0.04524 0.04012 0.0128 0.0138 1.0000
15.250 1.3334 0.05122 0.04627 0.0095 0.0137 1.0000
15.500 1.3148 0.05779 0.05301 0.0056 0.0137 1.0000
15.750 1.2887 0.06593 0.06133 0.0008 0.0137 1.0000
16.000 1.2610 0.07461 0.07019 -0.0041 0.0138 1.0000
16.250 1.2282 0.08430 0.08004 -0.0095 0.0139 1.0000
16.500 1.1999 0.09318 0.08908 -0.0144 0.0140 1.0000
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Polar data table (+)
Polar graphs
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