EPPLER 420 AIRFOIL (e420-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 420 AIRFOIL (e420-il) Reynolds number: 200,000 Max Cl/Cd: 75.62 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e420-il-200000-n5.txt Download as CSV file: xf-e420-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 420 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 0.3718 0.09694 0.09118 -0.1587 0.6731 0.0300
-9.750 0.3775 0.09505 0.08923 -0.1593 0.6656 0.0302
-9.500 0.3843 0.09318 0.08735 -0.1597 0.6582 0.0302
-9.250 0.3890 0.09132 0.08547 -0.1603 0.6513 0.0303
-9.000 0.3981 0.08933 0.08343 -0.1603 0.6451 0.0304
-8.750 0.4095 0.08724 0.08134 -0.1600 0.6386 0.0307
-8.500 0.4183 0.08550 0.07957 -0.1600 0.6325 0.0310
-8.250 0.4264 0.08377 0.07779 -0.1600 0.6271 0.0313
-8.000 0.4342 0.08199 0.07601 -0.1601 0.6220 0.0316
-7.750 0.4417 0.08027 0.07430 -0.1601 0.6167 0.0319
-7.500 0.4483 0.07852 0.07253 -0.1600 0.6117 0.0325
-7.250 0.4545 0.07683 0.07080 -0.1598 0.6071 0.0328
-6.750 0.4655 0.07336 0.06737 -0.1593 0.5979 0.0331
-6.250 0.4605 0.06822 0.06222 -0.1579 0.5905 0.0227
-5.750 0.4664 0.06542 0.05944 -0.1554 0.5834 0.0218
-5.500 0.4695 0.06356 0.05762 -0.1551 0.5798 0.0214
-5.000 0.4728 0.05711 0.05118 -0.1581 0.5736 0.0196
-4.750 0.4837 0.05487 0.04892 -0.1596 0.5705 0.0195
-4.250 0.6077 0.02310 0.01564 -0.2181 0.5660 0.0202
-4.000 0.6400 0.02197 0.01429 -0.2203 0.5623 0.0216
-3.750 0.6736 0.02062 0.01252 -0.2226 0.5585 0.0230
-3.500 0.7029 0.02005 0.01184 -0.2234 0.5549 0.0238
-3.250 0.7329 0.01949 0.01108 -0.2242 0.5518 0.0250
-3.000 0.7635 0.01898 0.01032 -0.2250 0.5490 0.0265
-2.750 0.7930 0.01865 0.00990 -0.2256 0.5463 0.0284
-2.500 0.8218 0.01831 0.00947 -0.2259 0.5435 0.0312
-2.250 0.8502 0.01808 0.00917 -0.2262 0.5406 0.0360
-2.000 0.8785 0.01788 0.00888 -0.2264 0.5377 0.0431
-1.750 0.9066 0.01773 0.00868 -0.2266 0.5349 0.0525
-1.500 0.9347 0.01765 0.00852 -0.2267 0.5323 0.0635
-1.250 0.9630 0.01765 0.00842 -0.2269 0.5298 0.0763
-1.000 0.9902 0.01768 0.00844 -0.2268 0.5274 0.0885
-0.750 1.0166 0.01772 0.00847 -0.2266 0.5249 0.1003
-0.500 1.0430 0.01777 0.00852 -0.2263 0.5225 0.1118
-0.250 1.0695 0.01785 0.00858 -0.2261 0.5201 0.1229
0.000 1.0958 0.01793 0.00863 -0.2259 0.5178 0.1339
0.250 1.1223 0.01805 0.00869 -0.2256 0.5155 0.1451
0.500 1.1491 0.01817 0.00878 -0.2255 0.5133 0.1556
0.750 1.1767 0.01832 0.00884 -0.2255 0.5112 0.1669
1.000 1.2029 0.01848 0.00899 -0.2253 0.5091 0.1778
1.250 1.2276 0.01862 0.00916 -0.2247 0.5069 0.1878
1.500 1.2523 0.01878 0.00934 -0.2242 0.5048 0.1987
1.750 1.2772 0.01894 0.00952 -0.2238 0.5027 0.2085
2.000 1.3018 0.01911 0.00968 -0.2232 0.5005 0.2193
2.250 1.3264 0.01926 0.00986 -0.2228 0.4984 0.2293
2.500 1.3515 0.01944 0.01000 -0.2223 0.4963 0.2403
2.750 1.3776 0.01962 0.01018 -0.2222 0.4943 0.2512
3.000 1.4050 0.01983 0.01035 -0.2223 0.4926 0.2631
3.250 1.4301 0.02006 0.01061 -0.2220 0.4909 0.2756
3.500 1.4520 0.02029 0.01092 -0.2210 0.4890 0.2877
3.750 1.4737 0.02052 0.01122 -0.2201 0.4869 0.3016
4.000 1.4953 0.02075 0.01151 -0.2191 0.4846 0.3175
4.250 1.5171 0.02097 0.01179 -0.2182 0.4824 0.3363
4.500 1.5393 0.02118 0.01207 -0.2174 0.4804 0.3615
4.750 1.5623 0.02138 0.01236 -0.2168 0.4786 0.4014
5.000 1.5822 0.02098 0.01266 -0.2154 0.4770 1.0000
5.250 1.6078 0.02129 0.01289 -0.2153 0.4753 1.0000
5.500 1.6348 0.02162 0.01315 -0.2154 0.4735 1.0000
5.750 1.6489 0.02202 0.01362 -0.2131 0.4714 1.0000
6.000 1.6648 0.02243 0.01408 -0.2112 0.4692 1.0000
6.250 1.6822 0.02285 0.01453 -0.2097 0.4672 1.0000
6.500 1.7001 0.02326 0.01498 -0.2082 0.4651 1.0000
6.750 1.7185 0.02365 0.01539 -0.2069 0.4629 1.0000
7.000 1.7377 0.02402 0.01576 -0.2056 0.4608 1.0000
7.250 1.7586 0.02438 0.01611 -0.2048 0.4590 1.0000
7.500 1.7827 0.02473 0.01644 -0.2045 0.4573 1.0000
7.750 1.8048 0.02514 0.01685 -0.2039 0.4554 1.0000
8.000 1.8111 0.02583 0.01767 -0.2007 0.4530 1.0000
8.250 1.8201 0.02650 0.01844 -0.1980 0.4504 1.0000
8.500 1.8314 0.02714 0.01917 -0.1957 0.4478 1.0000
8.750 1.8448 0.02771 0.01979 -0.1938 0.4453 1.0000
9.000 1.8603 0.02823 0.02034 -0.1923 0.4429 1.0000
9.250 1.8795 0.02864 0.02075 -0.1914 0.4408 1.0000
9.500 1.9051 0.02891 0.02099 -0.1914 0.4387 1.0000
9.750 1.8993 0.03023 0.02250 -0.1870 0.4356 1.0000
10.000 1.8986 0.03148 0.02389 -0.1835 0.4322 1.0000
10.250 1.9037 0.03254 0.02504 -0.1809 0.4290 1.0000
10.500 1.9138 0.03337 0.02593 -0.1791 0.4261 1.0000
10.750 1.9313 0.03387 0.02644 -0.1781 0.4235 1.0000
11.000 1.9407 0.03484 0.02747 -0.1763 0.4205 1.0000
11.250 1.9235 0.03743 0.03027 -0.1719 0.4161 1.0000
11.500 1.9194 0.03940 0.03235 -0.1691 0.4120 1.0000
11.750 1.9270 0.04062 0.03363 -0.1675 0.4087 1.0000
12.000 1.9484 0.04088 0.03387 -0.1671 0.4059 1.0000
12.250 1.9171 0.04534 0.03858 -0.1628 0.4004 1.0000
12.500 1.9023 0.04881 0.04219 -0.1602 0.3951 1.0000
12.750 1.9145 0.04987 0.04326 -0.1593 0.3915 1.0000
13.000 1.9034 0.05330 0.04681 -0.1574 0.3865 1.0000
13.250 1.8650 0.05993 0.05363 -0.1548 0.3787 1.0000
13.500 1.8848 0.06025 0.05395 -0.1544 0.3753 1.0000
13.750 1.8222 0.07054 0.06448 -0.1521 0.3645 1.0000
14.000 1.8396 0.07114 0.06509 -0.1517 0.3605 1.0000
14.500 1.8089 0.08102 0.07516 -0.1503 0.3454 1.0000
15.000 1.7919 0.08945 0.08373 -0.1496 0.3304 1.0000
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Polar data table (+)
Polar graphs
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