EPPLER 376 AIRFOIL (e376-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 376 AIRFOIL (e376-il) Reynolds number: 200,000 Max Cl/Cd: 95.01 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e376-il-200000-n5.txt Download as CSV file: xf-e376-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.4264 0.16434 0.16074 0.0170 1.0000 0.0051
-13.500 -0.4177 0.16139 0.15780 0.0154 1.0000 0.0051
-13.250 -0.4092 0.15843 0.15485 0.0140 1.0000 0.0052
-13.000 -0.4004 0.15547 0.15190 0.0125 1.0000 0.0053
-12.750 -0.3918 0.15254 0.14899 0.0110 1.0000 0.0054
-12.500 -0.3833 0.14962 0.14608 0.0096 1.0000 0.0055
-12.250 -0.3744 0.14676 0.14323 0.0082 1.0000 0.0055
-12.000 -0.3657 0.14388 0.14037 0.0068 1.0000 0.0056
-11.750 -0.3570 0.14105 0.13756 0.0054 1.0000 0.0057
-11.500 -0.3482 0.13814 0.13467 0.0040 1.0000 0.0059
-11.250 -0.3394 0.13531 0.13182 0.0027 1.0000 0.0060
-11.000 -0.3305 0.13254 0.12908 0.0013 1.0000 0.0061
-10.750 -0.3216 0.12980 0.12635 0.0000 1.0000 0.0062
-10.500 -0.3126 0.12704 0.12361 -0.0013 1.0000 0.0064
-10.250 -0.3033 0.12436 0.12096 -0.0026 1.0000 0.0066
-10.000 -0.2941 0.12178 0.11841 -0.0039 1.0000 0.0067
-9.750 -0.2844 0.11932 0.11598 -0.0053 1.0000 0.0069
-9.250 -0.2653 0.11472 0.11144 -0.0079 1.0000 0.0070
-7.250 -0.1533 0.09476 0.09134 -0.0287 0.8271 0.0074
-7.000 -0.1433 0.09057 0.08707 -0.0289 0.8050 0.0076
-6.750 -0.1317 0.08754 0.08394 -0.0300 0.7838 0.0077
-6.500 -0.1185 0.08480 0.08112 -0.0315 0.7657 0.0078
-6.250 -0.1039 0.08231 0.07855 -0.0334 0.7489 0.0079
-6.000 -0.0878 0.07982 0.07599 -0.0355 0.7341 0.0081
-5.750 -0.0706 0.07731 0.07341 -0.0379 0.7204 0.0083
-5.500 -0.0520 0.07487 0.07089 -0.0404 0.7078 0.0086
-5.250 -0.0319 0.07239 0.06834 -0.0431 0.6958 0.0088
-5.000 -0.0105 0.06990 0.06577 -0.0460 0.6856 0.0092
-4.750 0.0124 0.06738 0.06319 -0.0491 0.6755 0.0096
-4.500 0.0370 0.06490 0.06061 -0.0524 0.6662 0.0103
-4.250 0.0698 0.06330 0.05889 -0.0569 0.6572 0.0118
-4.000 0.1099 0.06248 0.05796 -0.0630 0.6482 0.0122
-3.750 0.1429 0.06051 0.05587 -0.0674 0.6407 0.0123
-3.500 0.1749 0.05830 0.05356 -0.0714 0.6330 0.0123
-3.250 0.2058 0.05600 0.05115 -0.0748 0.6260 0.0124
-3.000 0.2372 0.05365 0.04871 -0.0782 0.6190 0.0124
-2.750 0.2687 0.05135 0.04628 -0.0813 0.6130 0.0124
-2.500 0.2929 0.04714 0.04206 -0.0836 0.6066 0.0127
-2.250 0.3154 0.04373 0.03855 -0.0852 0.6012 0.0132
-2.000 0.3445 0.04130 0.03606 -0.0878 0.5950 0.0138
-1.750 0.3763 0.03926 0.03392 -0.0905 0.5893 0.0145
-1.500 0.4094 0.03738 0.03192 -0.0932 0.5839 0.0157
-1.250 0.4441 0.03571 0.03014 -0.0959 0.5780 0.0193
-1.000 0.4849 0.03483 0.02907 -0.0988 0.5730 0.0210
-0.750 0.5237 0.03386 0.02793 -0.1014 0.5675 0.0212
-0.500 0.5591 0.03259 0.02651 -0.1034 0.5621 0.0213
-0.250 0.5923 0.03120 0.02495 -0.1049 0.5576 0.0214
0.000 0.6167 0.02814 0.02191 -0.1064 0.5525 0.0224
0.250 0.6467 0.02674 0.02040 -0.1077 0.5476 0.0236
0.500 0.6784 0.02560 0.01911 -0.1088 0.5432 0.0253
0.750 0.7125 0.02484 0.01822 -0.1098 0.5379 0.0282
1.000 0.7480 0.02455 0.01773 -0.1103 0.5333 0.0291
1.250 0.7791 0.02347 0.01647 -0.1109 0.5293 0.0292
1.750 0.8390 0.02020 0.01297 -0.1125 0.5196 0.0195
2.000 0.8688 0.01962 0.01224 -0.1127 0.5157 0.0271
2.250 0.9003 0.01851 0.01098 -0.1130 0.5108 0.0236
2.500 0.9319 0.01739 0.00962 -0.1129 0.5062 0.0211
2.750 0.9612 0.01650 0.00851 -0.1128 0.5023 0.0206
3.000 0.9908 0.01538 0.00717 -0.1127 0.4978 0.0203
3.250 1.0190 0.01443 0.00597 -0.1124 0.4931 0.0203
3.500 1.0461 0.01397 0.00533 -0.1121 0.4888 0.0212
3.750 1.0728 0.01380 0.00515 -0.1119 0.4842 0.0260
4.000 1.0999 0.01378 0.00519 -0.1117 0.4790 0.0535
4.250 1.1262 0.01402 0.00542 -0.1114 0.4744 0.0804
4.500 1.1527 0.01407 0.00549 -0.1112 0.4691 0.0906
4.750 1.1792 0.01413 0.00552 -0.1110 0.4634 0.0998
5.000 1.2055 0.01424 0.00560 -0.1107 0.4578 0.1121
5.250 1.2318 0.01435 0.00584 -0.1105 0.4505 0.1305
5.500 1.2578 0.01450 0.00598 -0.1102 0.4444 0.1520
5.750 1.2840 0.01464 0.00621 -0.1100 0.4370 0.1771
6.000 1.3098 0.01480 0.00639 -0.1098 0.4300 0.2067
6.250 1.3333 0.01433 0.00666 -0.1092 0.4213 0.8220
6.750 1.3883 0.01465 0.00719 -0.1094 0.4034 1.0000
7.000 1.4136 0.01488 0.00751 -0.1090 0.3928 1.0000
7.250 1.4384 0.01514 0.00783 -0.1086 0.3813 1.0000
7.500 1.4630 0.01543 0.00818 -0.1082 0.3683 1.0000
7.750 1.4871 0.01576 0.00856 -0.1078 0.3529 1.0000
8.000 1.5103 0.01618 0.00905 -0.1073 0.3290 1.0000
8.250 1.5293 0.01707 0.00966 -0.1065 0.2719 1.0000
8.500 1.5453 0.01844 0.01069 -0.1055 0.2127 1.0000
8.750 1.5577 0.02029 0.01214 -0.1044 0.1515 1.0000
9.000 1.5691 0.02214 0.01366 -0.1031 0.1031 1.0000
9.250 1.5782 0.02410 0.01533 -0.1015 0.0606 1.0000
9.500 1.5859 0.02601 0.01706 -0.0998 0.0318 1.0000
9.750 1.5892 0.02811 0.01912 -0.0975 0.0121 1.0000
10.000 1.5946 0.02980 0.02089 -0.0953 0.0084 1.0000
10.250 1.5971 0.03137 0.02262 -0.0928 0.0076 1.0000
10.500 1.5976 0.03320 0.02462 -0.0905 0.0071 1.0000
10.750 1.5976 0.03536 0.02695 -0.0889 0.0068 1.0000
11.000 1.5969 0.03784 0.02961 -0.0877 0.0065 1.0000
11.250 1.5950 0.04067 0.03262 -0.0868 0.0062 1.0000
11.500 1.5926 0.04374 0.03588 -0.0863 0.0061 1.0000
11.750 1.5889 0.04711 0.03943 -0.0859 0.0059 1.0000
12.000 1.5841 0.05077 0.04327 -0.0858 0.0058 1.0000
12.250 1.5782 0.05467 0.04733 -0.0859 0.0057 1.0000
12.500 1.5707 0.05887 0.05170 -0.0861 0.0056 1.0000
12.750 1.5616 0.06338 0.05637 -0.0865 0.0054 1.0000
13.000 1.5517 0.06812 0.06128 -0.0871 0.0052 1.0000
13.250 1.5402 0.07315 0.06645 -0.0877 0.0050 1.0000
13.500 1.5358 0.07732 0.07078 -0.0884 0.0049 1.0000
13.750 1.5317 0.08156 0.07518 -0.0891 0.0046 1.0000
14.000 1.5265 0.08607 0.07985 -0.0900 0.0045 1.0000
14.250 1.5210 0.09076 0.08470 -0.0910 0.0044 1.0000
14.500 1.5154 0.09554 0.08971 -0.0921 0.0043 1.0000
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