E182 (8.47%) (e182-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: E182 (8.47%) (e182-il) Reynolds number: 500,000 Max Cl/Cd: 71.33 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e182-il-500000-n5.txt Download as CSV file: xf-e182-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E182 (8.47%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5267 0.08286 0.08086 0.0146 0.8757 0.0097
-8.750 -0.5332 0.07761 0.07557 0.0128 0.8592 0.0095
-8.500 -0.5409 0.07210 0.07002 0.0105 0.8446 0.0094
-8.250 -0.5510 0.06638 0.06427 0.0079 0.8309 0.0092
-7.750 -0.5867 0.05423 0.05204 -0.0005 0.8049 0.0089
-7.250 -0.6677 0.03319 0.02951 -0.0101 0.8209 0.0069
-7.000 -0.6532 0.02956 0.02538 -0.0093 0.8076 0.0068
-6.750 -0.6356 0.02675 0.02213 -0.0084 0.7956 0.0068
-6.500 -0.6164 0.02413 0.01908 -0.0076 0.7848 0.0068
-6.000 -0.5738 0.01962 0.01377 -0.0059 0.7650 0.0069
-5.750 -0.5504 0.01796 0.01182 -0.0053 0.7563 0.0070
-5.500 -0.5260 0.01672 0.01037 -0.0048 0.7476 0.0073
-5.250 -0.5008 0.01575 0.00921 -0.0043 0.7394 0.0075
-4.750 -0.4494 0.01416 0.00733 -0.0035 0.7242 0.0081
-4.250 -0.3974 0.01285 0.00579 -0.0027 0.7100 0.0087
-4.000 -0.3709 0.01240 0.00523 -0.0024 0.7034 0.0094
-3.750 -0.3442 0.01197 0.00473 -0.0022 0.6969 0.0099
-3.500 -0.3176 0.01151 0.00418 -0.0019 0.6906 0.0101
-3.250 -0.2908 0.01111 0.00370 -0.0016 0.6848 0.0103
-3.000 -0.2641 0.01064 0.00311 -0.0013 0.6786 0.0109
-2.750 -0.2370 0.01033 0.00271 -0.0010 0.6732 0.0119
-2.500 -0.2095 0.01008 0.00241 -0.0009 0.6675 0.0132
-2.250 -0.1819 0.00989 0.00215 -0.0007 0.6617 0.0149
-2.000 -0.1551 0.00953 0.00190 -0.0005 0.6565 0.0430
-1.750 -0.1284 0.00915 0.00172 -0.0004 0.6509 0.0953
-1.500 -0.1015 0.00887 0.00157 -0.0003 0.6457 0.1451
-1.250 -0.0749 0.00852 0.00145 -0.0002 0.6404 0.2144
-1.000 -0.0490 0.00806 0.00135 0.0000 0.6350 0.3203
-0.750 -0.0251 0.00741 0.00126 0.0005 0.6301 0.4874
-0.500 -0.0019 0.00683 0.00121 0.0013 0.6248 0.6363
-0.250 0.0216 0.00643 0.00116 0.0024 0.6194 0.7406
0.000 0.0454 0.00604 0.00117 0.0037 0.6146 0.8611
0.250 0.1001 0.00600 0.00126 -0.0018 0.6084 0.9470
0.500 0.1402 0.00607 0.00126 -0.0043 0.6026 0.9693
0.750 0.1747 0.00613 0.00128 -0.0057 0.5967 0.9830
1.000 0.2132 0.00617 0.00128 -0.0080 0.5892 0.9910
1.250 0.2521 0.00620 0.00127 -0.0104 0.5807 0.9973
1.500 0.2858 0.00624 0.00125 -0.0117 0.5719 1.0000
1.750 0.3123 0.00627 0.00126 -0.0114 0.5623 1.0000
2.000 0.3387 0.00632 0.00129 -0.0111 0.5524 1.0000
2.250 0.3651 0.00638 0.00132 -0.0108 0.5418 1.0000
2.500 0.3916 0.00645 0.00135 -0.0105 0.5303 1.0000
2.750 0.4182 0.00652 0.00141 -0.0102 0.5176 1.0000
3.000 0.4447 0.00661 0.00148 -0.0100 0.5030 1.0000
3.250 0.4711 0.00673 0.00155 -0.0097 0.4815 1.0000
3.500 0.4972 0.00697 0.00163 -0.0095 0.4387 1.0000
4.000 0.5473 0.00818 0.00213 -0.0093 0.2690 1.0000
4.250 0.5714 0.00906 0.00256 -0.0093 0.1698 1.0000
4.500 0.5955 0.00981 0.00296 -0.0091 0.0979 1.0000
4.750 0.6200 0.01039 0.00335 -0.0089 0.0544 1.0000
5.000 0.6439 0.01110 0.00384 -0.0085 0.0144 1.0000
5.250 0.6689 0.01147 0.00422 -0.0081 0.0115 1.0000
5.500 0.6939 0.01186 0.00465 -0.0077 0.0099 1.0000
5.750 0.7188 0.01221 0.00507 -0.0073 0.0092 1.0000
6.000 0.7433 0.01262 0.00556 -0.0068 0.0086 1.0000
6.250 0.7675 0.01309 0.00608 -0.0063 0.0082 1.0000
6.500 0.7912 0.01362 0.00668 -0.0058 0.0078 1.0000
6.750 0.8143 0.01422 0.00735 -0.0052 0.0075 1.0000
7.000 0.8367 0.01492 0.00813 -0.0046 0.0072 1.0000
7.250 0.8577 0.01580 0.00909 -0.0038 0.0069 1.0000
7.500 0.8772 0.01688 0.01026 -0.0028 0.0066 1.0000
7.750 0.8952 0.01817 0.01163 -0.0017 0.0064 1.0000
8.000 0.9130 0.01949 0.01304 -0.0006 0.0064 1.0000
8.250 0.9332 0.02040 0.01404 0.0003 0.0063 1.0000
8.500 0.9536 0.02123 0.01498 0.0011 0.0062 1.0000
8.750 0.9733 0.02215 0.01602 0.0020 0.0060 1.0000
9.000 0.9923 0.02316 0.01716 0.0029 0.0058 1.0000
9.250 1.0098 0.02442 0.01856 0.0039 0.0057 1.0000
9.500 1.0264 0.02577 0.02007 0.0050 0.0055 1.0000
9.750 1.0412 0.02737 0.02185 0.0062 0.0055 1.0000
10.000 1.0546 0.02898 0.02365 0.0075 0.0053 1.0000
10.250 1.0656 0.03076 0.02563 0.0088 0.0052 1.0000
10.500 1.0733 0.03276 0.02787 0.0104 0.0052 1.0000
10.750 1.0760 0.03467 0.02998 0.0124 0.0050 1.0000
11.000 1.0730 0.03690 0.03241 0.0144 0.0050 1.0000
11.250 1.0687 0.03947 0.03519 0.0157 0.0050 1.0000
11.500 1.0636 0.04227 0.03819 0.0164 0.0049 1.0000
11.750 1.0546 0.04577 0.04190 0.0164 0.0049 1.0000
12.000 1.0442 0.04968 0.04602 0.0157 0.0049 1.0000
12.250 1.0334 0.05387 0.05039 0.0144 0.0048 1.0000
12.500 1.0180 0.05909 0.05580 0.0123 0.0049 1.0000
12.750 0.9995 0.06524 0.06215 0.0092 0.0049 1.0000
13.000 0.9832 0.07157 0.06864 0.0056 0.0049 1.0000
13.250 0.9634 0.07924 0.07647 0.0007 0.0048 1.0000
13.500 0.9416 0.08834 0.08573 -0.0051 0.0049 1.0000
13.750 0.9154 0.10002 0.09756 -0.0126 0.0050 1.0000
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Polar data table (+)
Polar graphs
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