E169 (14.4%) (e169-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: E169 (14.4%) (e169-il) Reynolds number: 500,000 Max Cl/Cd: 71.54 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e169-il-500000-n5.txt Download as CSV file: xf-e169-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E169 (14.4%)
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
------ -------- --------- --------- -------- -------- --------
-17.500 -1.1041 0.09746 0.09319 -0.0021 1.0000 0.0098
-17.250 -1.1128 0.09223 0.08786 -0.0046 1.0000 0.0101
-17.000 -1.1222 0.08696 0.08250 -0.0071 1.0000 0.0102
-16.750 -1.1294 0.08218 0.07763 -0.0093 1.0000 0.0104
-16.500 -1.1385 0.07721 0.07255 -0.0116 1.0000 0.0105
-16.250 -1.1461 0.07258 0.06782 -0.0137 1.0000 0.0107
-16.000 -1.1531 0.06816 0.06329 -0.0156 1.0000 0.0109
-15.750 -1.1610 0.06374 0.05878 -0.0174 1.0000 0.0111
-15.500 -1.1731 0.05896 0.05390 -0.0194 1.0000 0.0113
-15.250 -1.1827 0.05461 0.04944 -0.0210 1.0000 0.0115
-15.000 -1.1897 0.05066 0.04541 -0.0225 1.0000 0.0117
-14.750 -1.1961 0.04686 0.04152 -0.0238 1.0000 0.0120
-14.500 -1.2000 0.04344 0.03801 -0.0249 1.0000 0.0123
-14.250 -1.2029 0.04018 0.03465 -0.0258 1.0000 0.0125
-14.000 -1.2040 0.03723 0.03161 -0.0266 1.0000 0.0128
-13.750 -1.2031 0.03457 0.02886 -0.0272 1.0000 0.0132
-13.500 -1.2014 0.03213 0.02632 -0.0275 1.0000 0.0136
-13.250 -1.1981 0.03000 0.02409 -0.0276 1.0000 0.0140
-13.000 -1.1964 0.02791 0.02192 -0.0273 1.0000 0.0145
-12.750 -1.1942 0.02612 0.02006 -0.0265 1.0000 0.0151
-12.500 -1.1904 0.02468 0.01856 -0.0252 1.0000 0.0158
-12.250 -1.1851 0.02353 0.01734 -0.0235 1.0000 0.0165
-12.000 -1.1778 0.02263 0.01636 -0.0214 1.0000 0.0174
-11.750 -1.1704 0.02181 0.01548 -0.0189 1.0000 0.0181
-11.500 -1.1615 0.02098 0.01462 -0.0166 1.0000 0.0192
-11.250 -1.1478 0.02024 0.01383 -0.0150 1.0000 0.0205
-11.000 -1.1317 0.01959 0.01313 -0.0136 1.0000 0.0219
-10.750 -1.1154 0.01890 0.01241 -0.0122 1.0000 0.0237
-10.500 -1.0981 0.01824 0.01173 -0.0109 1.0000 0.0264
-10.250 -1.0796 0.01764 0.01110 -0.0097 1.0000 0.0293
-10.000 -1.0608 0.01702 0.01049 -0.0085 1.0000 0.0338
-9.750 -1.0416 0.01641 0.00989 -0.0074 1.0000 0.0390
-9.500 -1.0215 0.01586 0.00934 -0.0064 1.0000 0.0447
-9.250 -1.0009 0.01533 0.00882 -0.0053 1.0000 0.0515
-9.000 -0.9805 0.01477 0.00829 -0.0043 1.0000 0.0600
-8.750 -0.9596 0.01425 0.00781 -0.0033 1.0000 0.0689
-8.500 -0.9383 0.01377 0.00735 -0.0023 1.0000 0.0784
-8.250 -0.9169 0.01329 0.00692 -0.0013 1.0000 0.0896
-8.000 -0.8958 0.01280 0.00649 -0.0003 1.0000 0.1034
-7.750 -0.8744 0.01233 0.00610 0.0007 1.0000 0.1187
-7.500 -0.8526 0.01192 0.00574 0.0017 1.0000 0.1336
-7.250 -0.8185 0.01148 0.00537 0.0001 0.9896 0.1523
-7.000 -0.7839 0.01099 0.00499 -0.0016 0.9646 0.1761
-6.750 -0.7369 0.01056 0.00462 -0.0059 0.9176 0.2006
-6.500 -0.7059 0.01039 0.00434 -0.0064 0.8635 0.2146
-6.250 -0.6814 0.01030 0.00411 -0.0056 0.8230 0.2258
-6.000 -0.6566 0.01018 0.00390 -0.0049 0.7912 0.2374
-5.750 -0.6314 0.01004 0.00370 -0.0043 0.7644 0.2501
-5.500 -0.6057 0.00992 0.00351 -0.0039 0.7404 0.2619
-5.250 -0.5796 0.00981 0.00333 -0.0034 0.7184 0.2734
-5.000 -0.5530 0.00972 0.00317 -0.0031 0.6987 0.2847
-4.750 -0.5264 0.00961 0.00302 -0.0028 0.6802 0.2959
-4.500 -0.4996 0.00952 0.00288 -0.0025 0.6623 0.3065
-4.250 -0.4724 0.00945 0.00276 -0.0023 0.6459 0.3164
-4.000 -0.4452 0.00938 0.00264 -0.0020 0.6307 0.3258
-3.750 -0.4178 0.00932 0.00252 -0.0018 0.6157 0.3340
-3.500 -0.3902 0.00927 0.00242 -0.0017 0.6013 0.3427
-3.250 -0.3627 0.00921 0.00233 -0.0015 0.5881 0.3502
-3.000 -0.3350 0.00918 0.00224 -0.0013 0.5751 0.3584
-2.500 -0.2795 0.00910 0.00209 -0.0011 0.5505 0.3736
-2.250 -0.2517 0.00906 0.00202 -0.0009 0.5391 0.3811
-2.000 -0.2238 0.00904 0.00196 -0.0008 0.5281 0.3888
-1.750 -0.1960 0.00901 0.00191 -0.0007 0.5173 0.3962
-1.500 -0.1679 0.00899 0.00187 -0.0006 0.5069 0.4040
-1.250 -0.1401 0.00897 0.00183 -0.0005 0.4970 0.4114
-1.000 -0.1120 0.00896 0.00180 -0.0004 0.4869 0.4194
-0.750 -0.0841 0.00894 0.00178 -0.0003 0.4777 0.4268
-0.250 -0.0280 0.00893 0.00175 -0.0001 0.4598 0.4428
0.000 0.0000 0.00894 0.00174 0.0000 0.4514 0.4513
0.250 0.0280 0.00893 0.00175 0.0001 0.4429 0.4597
0.750 0.0841 0.00894 0.00178 0.0003 0.4268 0.4777
1.000 0.1120 0.00896 0.00180 0.0004 0.4194 0.4869
1.250 0.1401 0.00897 0.00183 0.0005 0.4114 0.4971
1.500 0.1679 0.00899 0.00187 0.0006 0.4040 0.5069
1.750 0.1960 0.00901 0.00191 0.0007 0.3962 0.5172
2.000 0.2238 0.00904 0.00196 0.0008 0.3888 0.5282
2.250 0.2517 0.00906 0.00202 0.0009 0.3812 0.5391
2.500 0.2794 0.00910 0.00209 0.0011 0.3736 0.5506
3.000 0.3350 0.00918 0.00224 0.0014 0.3585 0.5752
3.250 0.3627 0.00921 0.00233 0.0015 0.3502 0.5881
3.500 0.3902 0.00927 0.00242 0.0017 0.3427 0.6013
3.750 0.4178 0.00932 0.00252 0.0018 0.3340 0.6158
4.000 0.4451 0.00938 0.00264 0.0021 0.3258 0.6306
4.250 0.4723 0.00945 0.00276 0.0023 0.3163 0.6460
4.500 0.4995 0.00952 0.00288 0.0025 0.3066 0.6623
4.750 0.5263 0.00961 0.00302 0.0028 0.2959 0.6804
5.000 0.5529 0.00972 0.00317 0.0031 0.2847 0.6987
5.250 0.5795 0.00981 0.00333 0.0034 0.2733 0.7184
5.500 0.6056 0.00992 0.00351 0.0039 0.2619 0.7403
5.750 0.6313 0.01004 0.00370 0.0043 0.2502 0.7646
6.000 0.6565 0.01018 0.00390 0.0049 0.2376 0.7909
6.250 0.6813 0.01030 0.00411 0.0056 0.2258 0.8229
6.500 0.7058 0.01039 0.00434 0.0064 0.2145 0.8636
6.750 0.7369 0.01056 0.00463 0.0059 0.2005 0.9181
7.000 0.7840 0.01099 0.00500 0.0016 0.1760 0.9648
7.250 0.8185 0.01148 0.00537 -0.0001 0.1521 0.9897
7.500 0.8527 0.01192 0.00574 -0.0018 0.1336 1.0000
7.750 0.8744 0.01234 0.00610 -0.0008 0.1184 1.0000
8.000 0.8958 0.01281 0.00649 0.0003 0.1030 1.0000
8.250 0.9170 0.01328 0.00692 0.0013 0.0898 1.0000
8.500 0.9383 0.01376 0.00735 0.0023 0.0784 1.0000
8.750 0.9596 0.01425 0.00781 0.0033 0.0688 1.0000
9.000 0.9805 0.01477 0.00829 0.0043 0.0601 1.0000
9.500 1.0215 0.01585 0.00934 0.0064 0.0448 1.0000
9.750 1.0415 0.01641 0.00989 0.0074 0.0391 1.0000
10.000 1.0606 0.01702 0.01049 0.0086 0.0337 1.0000
10.250 1.0795 0.01763 0.01110 0.0097 0.0295 1.0000
10.500 1.0979 0.01824 0.01173 0.0109 0.0263 1.0000
10.750 1.1152 0.01890 0.01241 0.0122 0.0237 1.0000
11.000 1.1315 0.01959 0.01313 0.0136 0.0219 1.0000
11.250 1.1476 0.02023 0.01383 0.0150 0.0205 1.0000
11.500 1.1613 0.02098 0.01461 0.0167 0.0192 1.0000
11.750 1.1702 0.02180 0.01547 0.0190 0.0181 1.0000
12.000 1.1778 0.02261 0.01635 0.0214 0.0173 1.0000
12.250 1.1850 0.02353 0.01733 0.0235 0.0166 1.0000
12.500 1.1905 0.02467 0.01855 0.0252 0.0157 1.0000
12.750 1.1944 0.02610 0.02004 0.0265 0.0151 1.0000
13.000 1.1967 0.02788 0.02189 0.0273 0.0146 1.0000
13.250 1.1980 0.03000 0.02409 0.0276 0.0141 1.0000
13.500 1.2018 0.03209 0.02628 0.0275 0.0137 1.0000
13.750 1.2041 0.03447 0.02876 0.0272 0.0132 1.0000
14.000 1.2051 0.03711 0.03149 0.0266 0.0128 1.0000
14.250 1.2035 0.04013 0.03460 0.0258 0.0125 1.0000
14.500 1.2014 0.04329 0.03785 0.0249 0.0122 1.0000
14.750 1.1968 0.04680 0.04145 0.0237 0.0118 1.0000
15.000 1.1911 0.05052 0.04526 0.0225 0.0117 1.0000
15.250 1.1830 0.05461 0.04944 0.0209 0.0113 1.0000
15.500 1.1723 0.05912 0.05404 0.0192 0.0111 1.0000
15.750 1.1633 0.06348 0.05852 0.0175 0.0110 1.0000
16.000 1.1549 0.06796 0.06309 0.0156 0.0109 1.0000
16.250 1.1480 0.07236 0.06760 0.0137 0.0107 1.0000
16.500 1.1399 0.07708 0.07242 0.0116 0.0105 1.0000
16.750 1.1306 0.08207 0.07751 0.0093 0.0105 1.0000
17.000 1.1230 0.08691 0.08245 0.0070 0.0101 1.0000
17.250 1.1143 0.09207 0.08770 0.0046 0.0100 1.0000
17.500 1.1058 0.09726 0.09299 0.0021 0.0099 1.0000
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Polar data table (+)
Polar graphs
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