EPPLER 379 AIRFOIL (e379-il) Xfoil prediction polar at RE=1,000,000 Ncrit=0
| Details | Polar file |
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Airfoil: EPPLER 379 AIRFOIL (e379-il) Reynolds number: 1,000,000 Max Cl/Cd: 135.65 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e379-il-1000000.txt Download as CSV file: xf-e379-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 379 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.4024 0.13806 0.13653 0.0199 1.0000 0.0022
-11.000 -0.3934 0.13515 0.13363 0.0184 1.0000 0.0022
-10.750 -0.3842 0.13227 0.13076 0.0170 1.0000 0.0022
-10.500 -0.3751 0.12943 0.12792 0.0155 1.0000 0.0022
-10.250 -0.3659 0.12661 0.12511 0.0141 1.0000 0.0022
-10.000 -0.3567 0.12383 0.12235 0.0126 1.0000 0.0022
-9.750 -0.3474 0.12108 0.11962 0.0112 1.0000 0.0022
-9.500 -0.3382 0.11838 0.11691 0.0098 1.0000 0.0022
-9.250 -0.3289 0.11569 0.11423 0.0085 1.0000 0.0022
-9.000 -0.3157 0.11273 0.11126 0.0060 0.9604 0.0022
-8.750 -0.2970 0.10955 0.10776 0.0021 0.8584 0.0022
-8.500 -0.2906 0.10742 0.10544 0.0018 0.8093 0.0022
-8.250 -0.2831 0.10519 0.10308 0.0012 0.7760 0.0022
-2.000 0.2546 0.03844 0.03497 -0.0672 0.5329 0.0030
-1.750 0.2867 0.03637 0.03286 -0.0697 0.5285 0.0037
-1.500 0.3205 0.03440 0.03081 -0.0722 0.5238 0.0057
-1.250 0.3579 0.03349 0.02976 -0.0740 0.5191 0.0070
0.000 0.5251 0.02506 0.02087 -0.0817 0.4977 0.0072
0.250 0.5572 0.02352 0.01921 -0.0826 0.4936 0.0073
0.500 0.5890 0.02197 0.01757 -0.0834 0.4898 0.0073
2.250 0.8025 0.01130 0.00579 -0.0843 0.4617 0.0077
2.500 0.8311 0.01003 0.00428 -0.0840 0.4575 0.0064
2.750 0.8590 0.00886 0.00279 -0.0835 0.4533 0.0059
3.000 0.8857 0.00809 0.00183 -0.0831 0.4492 0.0059
3.250 0.9128 0.00793 0.00164 -0.0828 0.4443 0.0069
3.500 0.9400 0.00810 0.00177 -0.0827 0.4387 0.0139
3.750 0.9670 0.00810 0.00188 -0.0827 0.4330 0.0300
4.000 0.9939 0.00812 0.00186 -0.0826 0.4270 0.0283
4.250 1.0209 0.00809 0.00181 -0.0824 0.4216 0.0274
4.500 1.0479 0.00811 0.00182 -0.0823 0.4157 0.0264
4.750 1.0748 0.00818 0.00187 -0.0821 0.4097 0.0257
5.000 1.1018 0.00824 0.00193 -0.0820 0.4033 0.0256
5.250 1.1286 0.00832 0.00205 -0.0819 0.3922 0.0504
5.500 1.1529 0.00888 0.00231 -0.0818 0.3162 0.1557
5.750 1.1847 0.00882 0.00299 -0.0841 0.2306 1.0000
6.000 1.2037 0.01084 0.00416 -0.0838 0.0887 1.0000
6.250 1.2245 0.01233 0.00519 -0.0834 0.0019 1.0000
6.500 1.2499 0.01261 0.00545 -0.0832 0.0017 1.0000
6.750 1.2752 0.01292 0.00579 -0.0829 0.0017 1.0000
7.000 1.3002 0.01330 0.00623 -0.0825 0.0018 1.0000
7.250 1.3248 0.01374 0.00693 -0.0821 0.0020 1.0000
7.500 1.3488 0.01431 0.00764 -0.0816 0.0023 1.0000
7.750 1.3720 0.01499 0.00845 -0.0810 0.0027 1.0000
8.000 1.3944 0.01583 0.00945 -0.0803 0.0037 1.0000
9.500 1.4010 0.01394 0.00884 -0.0633 0.0058 1.0000
9.750 1.4003 0.01548 0.01051 -0.0608 0.0054 1.0000
10.000 1.3997 0.01755 0.01270 -0.0587 0.0050 1.0000
10.250 1.4002 0.02007 0.01535 -0.0569 0.0046 1.0000
10.500 1.4010 0.02284 0.01825 -0.0554 0.0042 1.0000
10.750 1.4008 0.02600 0.02155 -0.0539 0.0039 1.0000
11.000 1.3992 0.02947 0.02516 -0.0526 0.0037 1.0000
11.250 1.3963 0.03340 0.02931 -0.0517 0.0035 1.0000
11.500 1.3911 0.03770 0.03376 -0.0510 0.0033 1.0000
11.750 1.3837 0.04248 0.03871 -0.0506 0.0032 1.0000
12.000 1.3741 0.04776 0.04415 -0.0506 0.0031 1.0000
12.250 1.3621 0.05339 0.04994 -0.0508 0.0030 1.0000
12.500 1.3493 0.05942 0.05613 -0.0513 0.0030 1.0000
12.750 1.3347 0.06578 0.06265 -0.0522 0.0030 1.0000
13.000 1.3187 0.07229 0.06932 -0.0535 0.0029 1.0000
13.250 1.3029 0.07895 0.07613 -0.0552 0.0029 1.0000
13.500 1.2861 0.08576 0.08309 -0.0573 0.0029 1.0000
13.750 1.2683 0.09261 0.09009 -0.0597 0.0029 1.0000
14.000 1.2498 0.09961 0.09724 -0.0624 0.0029 1.0000
14.250 1.2297 0.10651 0.10429 -0.0655 0.0029 1.0000
14.500 1.2023 0.11302 0.11096 -0.0687 0.0030 1.0000
14.750 1.1836 0.11911 0.11717 -0.0721 0.0029 1.0000
15.000 1.1625 0.12625 0.12445 -0.0762 0.0030 1.0000
15.250 1.1472 0.13270 0.13102 -0.0802 0.0030 1.0000
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Polar data table (+)
Polar graphs
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