EPPLER 376 AIRFOIL (e376-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: EPPLER 376 AIRFOIL (e376-il) Reynolds number: 100,000 Max Cl/Cd: 67.36 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e376-il-100000-n5.txt Download as CSV file: xf-e376-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2569 0.11952 0.11500 -0.0111 1.0000 0.0122
-8.750 -0.2490 0.11794 0.11349 -0.0125 1.0000 0.0123
-8.500 -0.2415 0.11644 0.11205 -0.0138 1.0000 0.0123
-8.250 -0.2313 0.11473 0.11041 -0.0159 1.0000 0.0123
-8.000 -0.2197 0.11280 0.10854 -0.0182 1.0000 0.0124
-7.750 -0.2075 0.11090 0.10671 -0.0207 1.0000 0.0124
-7.500 -0.1949 0.10883 0.10471 -0.0231 1.0000 0.0124
-7.250 -0.1730 0.10580 0.10175 -0.0278 0.9750 0.0124
-7.000 -0.1619 0.09633 0.09224 -0.0267 0.9544 0.0128
-6.750 -0.1393 0.09098 0.08685 -0.0303 0.9262 0.0132
-6.500 -0.1165 0.08709 0.08290 -0.0342 0.8977 0.0136
-6.250 -0.0967 0.08408 0.07980 -0.0373 0.8703 0.0139
-6.000 -0.0790 0.08141 0.07705 -0.0397 0.8454 0.0144
-5.750 -0.0617 0.07889 0.07444 -0.0418 0.8243 0.0153
-5.500 -0.0434 0.07651 0.07198 -0.0442 0.8053 0.0162
-5.250 -0.0237 0.07411 0.06949 -0.0467 0.7885 0.0171
-5.000 -0.0024 0.07170 0.06699 -0.0495 0.7738 0.0180
-4.750 0.0204 0.06929 0.06450 -0.0525 0.7602 0.0189
-4.500 0.0456 0.06699 0.06207 -0.0559 0.7475 0.0199
-4.250 0.0756 0.06508 0.06006 -0.0601 0.7355 0.0207
-4.000 0.1089 0.06351 0.05836 -0.0649 0.7245 0.0211
-3.750 0.1450 0.06212 0.05681 -0.0700 0.7144 0.0213
-3.500 0.1815 0.06059 0.05514 -0.0750 0.7041 0.0214
-3.250 0.2015 0.05677 0.05128 -0.0763 0.6958 0.0216
-3.000 0.2177 0.05287 0.04735 -0.0769 0.6877 0.0224
-2.750 0.2452 0.05041 0.04479 -0.0796 0.6794 0.0235
-2.500 0.2760 0.04829 0.04255 -0.0826 0.6718 0.0254
-2.250 0.3186 0.04743 0.04149 -0.0873 0.6634 0.0286
-2.000 0.3704 0.04798 0.04171 -0.0930 0.6560 0.0292
-1.750 0.3875 0.04332 0.03712 -0.0938 0.6489 0.0299
-1.500 0.4126 0.04058 0.03427 -0.0954 0.6430 0.0315
-1.250 0.4449 0.03875 0.03234 -0.0978 0.6357 0.0336
-1.000 0.4793 0.03727 0.03069 -0.1003 0.6296 0.0362
-0.750 0.5217 0.03717 0.03035 -0.1032 0.6226 0.0386
-0.500 0.5617 0.03703 0.02994 -0.1054 0.6165 0.0391
-0.250 0.5869 0.03379 0.02668 -0.1069 0.6107 0.0399
0.000 0.6144 0.03170 0.02452 -0.1082 0.6047 0.0416
0.250 0.6453 0.03041 0.02306 -0.1095 0.5997 0.0438
0.500 0.6781 0.02938 0.02191 -0.1108 0.5932 0.0469
0.750 0.7180 0.03020 0.02238 -0.1116 0.5878 0.0505
1.000 0.7413 0.02739 0.01961 -0.1128 0.5825 0.0564
1.250 0.7782 0.02796 0.01989 -0.1132 0.5766 0.0622
1.750 0.8362 0.02501 0.01675 -0.1147 0.5662 0.0643
2.000 0.8690 0.02376 0.01523 -0.1149 0.5613 0.0367
2.250 0.8991 0.02294 0.01421 -0.1151 0.5568 0.0340
2.500 0.9294 0.02221 0.01333 -0.1152 0.5510 0.0323
2.750 0.9592 0.02146 0.01235 -0.1151 0.5462 0.0313
3.000 0.9882 0.02086 0.01157 -0.1150 0.5415 0.0322
3.250 1.0167 0.02032 0.01085 -0.1147 0.5359 0.0385
3.500 1.0459 0.01992 0.01026 -0.1148 0.5313 0.0439
3.750 1.0746 0.01940 0.00951 -0.1146 0.5261 0.0543
4.000 1.1006 0.01963 0.00981 -0.1144 0.5205 0.0929
4.250 1.1268 0.01958 0.00956 -0.1139 0.5161 0.1107
4.500 1.1526 0.01966 0.00967 -0.1136 0.5100 0.1205
4.750 1.1785 0.01977 0.00973 -0.1133 0.5046 0.1331
5.000 1.2044 0.01994 0.00989 -0.1130 0.4996 0.1534
5.250 1.2300 0.02016 0.01025 -0.1127 0.4930 0.1755
5.500 1.2560 0.02029 0.01036 -0.1123 0.4878 0.2083
5.750 1.2813 0.02051 0.01079 -0.1121 0.4801 0.2629
6.000 1.3077 0.02004 0.01092 -0.1119 0.4739 1.0000
6.250 1.3323 0.02039 0.01137 -0.1115 0.4656 1.0000
6.500 1.3575 0.02059 0.01154 -0.1109 0.4591 1.0000
6.750 1.3817 0.02093 0.01212 -0.1104 0.4496 1.0000
7.000 1.4060 0.02119 0.01248 -0.1099 0.4406 1.0000
7.250 1.4304 0.02138 0.01272 -0.1092 0.4315 1.0000
7.500 1.4539 0.02170 0.01323 -0.1086 0.4202 1.0000
7.750 1.4772 0.02200 0.01370 -0.1080 0.4083 1.0000
8.000 1.5004 0.02230 0.01426 -0.1073 0.3952 1.0000
8.250 1.5230 0.02261 0.01475 -0.1066 0.3801 1.0000
8.500 1.5448 0.02296 0.01524 -0.1057 0.3630 1.0000
8.750 1.5657 0.02344 0.01591 -0.1048 0.3421 1.0000
9.000 1.5834 0.02407 0.01654 -0.1036 0.3066 1.0000
9.250 1.5951 0.02534 0.01754 -0.1021 0.2497 1.0000
9.500 1.6037 0.02709 0.01906 -0.1004 0.2033 1.0000
9.750 1.6080 0.02920 0.02106 -0.0984 0.1628 1.0000
10.000 1.6049 0.03188 0.02343 -0.0961 0.1194 1.0000
10.250 1.5988 0.03454 0.02588 -0.0935 0.0878 1.0000
10.500 1.5872 0.03740 0.02858 -0.0907 0.0640 1.0000
10.750 1.5765 0.04065 0.03175 -0.0890 0.0454 1.0000
11.000 1.5656 0.04434 0.03540 -0.0880 0.0317 1.0000
11.250 1.5550 0.04834 0.03940 -0.0874 0.0228 1.0000
11.500 1.5479 0.05219 0.04339 -0.0871 0.0188 1.0000
11.750 1.5401 0.05627 0.04761 -0.0870 0.0165 1.0000
12.000 1.5310 0.06067 0.05214 -0.0871 0.0150 1.0000
12.250 1.5210 0.06534 0.05695 -0.0875 0.0140 1.0000
12.500 1.5137 0.06975 0.06159 -0.0879 0.0134 1.0000
12.750 1.5057 0.07436 0.06641 -0.0885 0.0128 1.0000
13.000 1.4975 0.07908 0.07134 -0.0892 0.0124 1.0000
13.250 1.4892 0.08393 0.07639 -0.0901 0.0121 1.0000
13.500 1.4813 0.08890 0.08156 -0.0911 0.0117 1.0000
13.750 1.4741 0.09389 0.08674 -0.0922 0.0114 1.0000
14.000 1.4674 0.09886 0.09190 -0.0934 0.0111 1.0000
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Polar data table (+)
Polar graphs
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