EPPLER 376 AIRFOIL (e376-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 376 AIRFOIL (e376-il) Reynolds number: 1,000,000 Max Cl/Cd: 141.71 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e376-il-1000000-n5.txt Download as CSV file: xf-e376-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 376 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.2088 0.10073 0.09795 -0.0177 0.6445 0.0022
-8.000 -0.2000 0.09848 0.09568 -0.0186 0.6347 0.0022
-7.750 -0.1920 0.09628 0.09345 -0.0193 0.6261 0.0022
-7.500 -0.1820 0.09408 0.09124 -0.0206 0.6183 0.0022
-7.250 -0.1696 0.09166 0.08878 -0.0224 0.6104 0.0022
-7.000 -0.1559 0.08916 0.08627 -0.0245 0.6033 0.0022
-6.750 -0.1413 0.08664 0.08371 -0.0267 0.5962 0.0022
-6.500 -0.1254 0.08405 0.08112 -0.0292 0.5902 0.0022
-6.250 -0.1084 0.08150 0.07853 -0.0317 0.5842 0.0022
-6.000 -0.0906 0.07893 0.07594 -0.0344 0.5789 0.0022
-5.750 -0.0611 0.05922 0.05641 -0.0288 0.5581 0.0025
-5.500 -0.0451 0.05639 0.05356 -0.0311 0.5529 0.0026
-5.250 -0.0275 0.05347 0.05063 -0.0337 0.5490 0.0028
-5.000 -0.0087 0.05053 0.04767 -0.0364 0.5439 0.0032
-4.750 0.0117 0.04750 0.04460 -0.0394 0.5400 0.0038
-4.500 0.0339 0.04447 0.04154 -0.0425 0.5358 0.0039
-4.250 0.0588 0.04150 0.03854 -0.0461 0.5316 0.0040
-4.000 0.0932 0.05809 0.05484 -0.0596 0.5373 0.0040
-3.750 0.1243 0.05575 0.05245 -0.0636 0.5322 0.0041
-3.500 0.1537 0.05327 0.04992 -0.0672 0.5275 0.0041
-3.250 0.1841 0.05083 0.04743 -0.0707 0.5237 0.0041
-3.000 0.2153 0.04841 0.04496 -0.0743 0.5196 0.0041
-2.750 0.2473 0.04605 0.04253 -0.0777 0.5150 0.0041
-2.500 0.2800 0.04374 0.04015 -0.0811 0.5109 0.0041
-2.250 0.3135 0.04145 0.03781 -0.0845 0.5071 0.0041
-2.000 0.3473 0.03924 0.03554 -0.0877 0.5032 0.0041
-1.750 0.3791 0.03658 0.03282 -0.0907 0.4992 0.0043
-1.500 0.4117 0.03460 0.03078 -0.0934 0.4954 0.0044
-1.250 0.4456 0.03273 0.02884 -0.0961 0.4913 0.0046
-1.000 0.4798 0.03093 0.02696 -0.0985 0.4871 0.0048
-0.750 0.5142 0.02918 0.02512 -0.1008 0.4835 0.0051
-0.500 0.5488 0.02746 0.02332 -0.1030 0.4799 0.0055
-0.250 0.5844 0.02582 0.02160 -0.1048 0.4757 0.0063
0.000 0.6199 0.02424 0.01991 -0.1066 0.4715 0.0064
0.250 0.6560 0.02203 0.01755 -0.1083 0.4680 0.0041
0.500 0.6909 0.02029 0.01569 -0.1097 0.4646 0.0041
0.750 0.7234 0.01899 0.01430 -0.1106 0.4603 0.0046
1.000 0.7555 0.01780 0.01299 -0.1114 0.4561 0.0057
1.250 0.7858 0.01693 0.01204 -0.1119 0.4524 0.0078
1.500 0.8177 0.01573 0.01072 -0.1123 0.4484 0.0080
1.750 0.8524 0.01372 0.00846 -0.1126 0.4443 0.0070
2.000 0.8888 0.00871 0.00260 -0.1129 0.4412 0.0070
2.250 0.9161 0.00843 0.00224 -0.1127 0.4374 0.0083
2.500 0.9432 0.00824 0.00197 -0.1125 0.4328 0.0108
2.750 0.9703 0.00825 0.00196 -0.1123 0.4280 0.0138
3.000 0.9973 0.00820 0.00187 -0.1121 0.4237 0.0151
3.250 1.0244 0.00814 0.00179 -0.1119 0.4178 0.0205
3.500 1.0513 0.00818 0.00178 -0.1117 0.4109 0.0251
3.750 1.0783 0.00822 0.00183 -0.1116 0.4038 0.0315
4.000 1.1051 0.00829 0.00189 -0.1114 0.3978 0.0397
4.250 1.1320 0.00835 0.00194 -0.1113 0.3919 0.0468
4.500 1.1586 0.00846 0.00203 -0.1111 0.3838 0.0557
4.750 1.1853 0.00855 0.00212 -0.1110 0.3749 0.0637
5.000 1.2119 0.00867 0.00227 -0.1108 0.3671 0.0733
5.250 1.2384 0.00881 0.00240 -0.1107 0.3579 0.0852
5.500 1.2648 0.00894 0.00254 -0.1105 0.3488 0.0983
5.750 1.2910 0.00911 0.00270 -0.1103 0.3379 0.1110
6.000 1.3170 0.00931 0.00288 -0.1102 0.3251 0.1231
6.250 1.3427 0.00954 0.00309 -0.1100 0.3102 0.1365
6.500 1.3682 0.00982 0.00338 -0.1098 0.2922 0.1527
6.750 1.3931 0.01021 0.00369 -0.1096 0.2682 0.1665
7.000 1.4172 0.01071 0.00408 -0.1093 0.2385 0.1856
7.250 1.4409 0.01127 0.00453 -0.1090 0.2082 0.2169
7.500 1.4639 0.01102 0.00510 -0.1087 0.1805 1.0000
7.750 1.4870 0.01161 0.00559 -0.1083 0.1560 1.0000
8.000 1.5095 0.01227 0.00612 -0.1079 0.1301 1.0000
8.250 1.5320 0.01289 0.00665 -0.1074 0.1100 1.0000
8.500 1.5541 0.01353 0.00720 -0.1069 0.0904 1.0000
8.750 1.5761 0.01416 0.00777 -0.1063 0.0753 1.0000
9.000 1.5968 0.01493 0.00846 -0.1057 0.0562 1.0000
9.250 1.6160 0.01585 0.00926 -0.1049 0.0371 1.0000
9.500 1.6340 0.01685 0.01015 -0.1039 0.0209 1.0000
9.750 1.6530 0.01765 0.01094 -0.1030 0.0133 1.0000
10.000 1.6712 0.01849 0.01177 -0.1021 0.0080 1.0000
10.250 1.6880 0.01940 0.01271 -0.1009 0.0039 1.0000
10.500 1.7032 0.02041 0.01377 -0.0996 0.0016 1.0000
10.750 1.7181 0.02135 0.01479 -0.0982 0.0009 1.0000
11.000 1.7303 0.02243 0.01598 -0.0965 0.0006 1.0000
11.250 1.7382 0.02373 0.01742 -0.0942 0.0004 1.0000
11.500 1.7418 0.02487 0.01867 -0.0913 0.0004 1.0000
11.750 1.7425 0.02627 0.02017 -0.0885 0.0004 1.0000
12.000 1.7422 0.02804 0.02207 -0.0863 0.0004 1.0000
12.250 1.7412 0.03018 0.02433 -0.0846 0.0004 1.0000
12.500 1.7409 0.03252 0.02679 -0.0835 0.0004 1.0000
12.750 1.7412 0.03500 0.02940 -0.0828 0.0003 1.0000
13.000 1.7380 0.03808 0.03263 -0.0822 0.0003 1.0000
13.250 1.7376 0.04095 0.03561 -0.0820 0.0003 1.0000
13.500 1.7359 0.04404 0.03881 -0.0818 0.0003 1.0000
13.750 1.7361 0.04696 0.04183 -0.0818 0.0002 1.0000
14.000 1.7337 0.05028 0.04526 -0.0819 0.0002 1.0000
14.250 1.7269 0.05431 0.04941 -0.0822 0.0002 1.0000
14.500 1.7213 0.05821 0.05344 -0.0826 0.0002 1.0000
14.750 1.7140 0.06245 0.05780 -0.0832 0.0002 1.0000
15.000 1.7039 0.06730 0.06279 -0.0840 0.0002 1.0000
15.250 1.6953 0.07211 0.06773 -0.0851 0.0002 1.0000
15.500 1.6863 0.07715 0.07290 -0.0863 0.0002 1.0000
15.750 1.6779 0.08222 0.07810 -0.0877 0.0002 1.0000
16.000 1.6675 0.08782 0.08383 -0.0894 0.0002 1.0000
16.250 1.6577 0.09348 0.08962 -0.0913 0.0001 1.0000
16.500 1.6465 0.09949 0.09577 -0.0934 0.0001 1.0000
16.750 1.6374 0.10527 0.10168 -0.0955 0.0001 1.0000
17.000 1.6270 0.11146 0.10799 -0.0980 0.0001 1.0000
17.250 1.6156 0.11793 0.11459 -0.1007 0.0001 1.0000
17.500 1.6044 0.12452 0.12132 -0.1036 0.0001 1.0000
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