E169 (14.4%) (e169-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: E169 (14.4%) (e169-il) Reynolds number: 1,000,000 Max Cl/Cd: 92.56 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e169-il-1000000.txt Download as CSV file: xf-e169-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.750 -1.1771 0.08861 0.08485 -0.0073 1.0000 0.0088
-17.500 -1.1865 0.08355 0.07970 -0.0096 1.0000 0.0087
-17.250 -1.2055 0.07716 0.07322 -0.0126 1.0000 0.0090
-17.000 -1.2195 0.07167 0.06762 -0.0150 1.0000 0.0090
-16.750 -1.2299 0.06685 0.06273 -0.0171 1.0000 0.0092
-16.500 -1.2419 0.06193 0.05771 -0.0192 1.0000 0.0093
-16.250 -1.2530 0.05737 0.05307 -0.0209 1.0000 0.0095
-16.000 -1.2617 0.05320 0.04880 -0.0225 1.0000 0.0097
-15.750 -1.2687 0.04930 0.04482 -0.0239 1.0000 0.0098
-15.500 -1.2743 0.04561 0.04104 -0.0251 1.0000 0.0101
-15.250 -1.2789 0.04210 0.03744 -0.0262 1.0000 0.0103
-15.000 -1.2793 0.03913 0.03439 -0.0271 1.0000 0.0105
-14.750 -1.2811 0.03606 0.03122 -0.0280 1.0000 0.0108
-14.500 -1.2762 0.03381 0.02890 -0.0285 1.0000 0.0110
-14.250 -1.2815 0.03059 0.02556 -0.0291 1.0000 0.0113
-14.000 -1.2843 0.02788 0.02277 -0.0292 1.0000 0.0118
-13.750 -1.2829 0.02584 0.02067 -0.0288 1.0000 0.0123
-13.500 -1.2803 0.02416 0.01892 -0.0279 1.0000 0.0127
-13.250 -1.2743 0.02294 0.01763 -0.0266 1.0000 0.0132
-13.000 -1.2679 0.02191 0.01654 -0.0248 1.0000 0.0137
-12.750 -1.2586 0.02115 0.01572 -0.0228 1.0000 0.0141
-12.500 -1.2573 0.02013 0.01463 -0.0196 1.0000 0.0149
-12.250 -1.2499 0.01933 0.01380 -0.0169 1.0000 0.0157
-12.000 -1.2354 0.01868 0.01312 -0.0152 1.0000 0.0166
-11.750 -1.2186 0.01811 0.01250 -0.0138 1.0000 0.0174
-11.500 -1.2012 0.01753 0.01187 -0.0125 1.0000 0.0182
-11.250 -1.1851 0.01681 0.01113 -0.0110 1.0000 0.0197
-11.000 -1.1662 0.01626 0.01056 -0.0098 1.0000 0.0211
-10.750 -1.1455 0.01581 0.01007 -0.0088 1.0000 0.0223
-10.500 -1.1271 0.01516 0.00942 -0.0075 1.0000 0.0251
-10.250 -1.1062 0.01469 0.00893 -0.0065 1.0000 0.0277
-10.000 -1.0864 0.01410 0.00837 -0.0054 1.0000 0.0326
-9.750 -1.0660 0.01356 0.00786 -0.0043 1.0000 0.0387
-9.500 -1.0452 0.01305 0.00739 -0.0032 1.0000 0.0462
-9.250 -1.0239 0.01258 0.00695 -0.0022 1.0000 0.0543
-9.000 -1.0027 0.01211 0.00652 -0.0011 1.0000 0.0640
-8.750 -0.9817 0.01162 0.00611 0.0000 1.0000 0.0758
-8.500 -0.9606 0.01115 0.00571 0.0011 1.0000 0.0891
-8.250 -0.9394 0.01068 0.00533 0.0022 1.0000 0.1043
-8.000 -0.9178 0.01024 0.00497 0.0032 1.0000 0.1212
-7.750 -0.8956 0.00986 0.00466 0.0042 1.0000 0.1373
-7.500 -0.8730 0.00951 0.00439 0.0052 1.0000 0.1526
-7.250 -0.8504 0.00919 0.00413 0.0061 1.0000 0.1678
-7.000 -0.8137 0.00883 0.00387 0.0041 0.9959 0.1869
-6.750 -0.7764 0.00853 0.00363 0.0019 0.9880 0.2029
-6.500 -0.7390 0.00826 0.00342 -0.0002 0.9740 0.2192
-6.250 -0.6929 0.00798 0.00318 -0.0040 0.9385 0.2392
-6.000 -0.6626 0.00790 0.00297 -0.0044 0.8778 0.2532
-5.750 -0.6380 0.00784 0.00282 -0.0035 0.8349 0.2647
-5.500 -0.6124 0.00780 0.00267 -0.0029 0.8010 0.2749
-5.250 -0.5861 0.00774 0.00253 -0.0025 0.7724 0.2860
-5.000 -0.5595 0.00768 0.00241 -0.0021 0.7479 0.2976
-4.750 -0.5326 0.00760 0.00229 -0.0018 0.7250 0.3083
-4.500 -0.5054 0.00756 0.00218 -0.0016 0.7039 0.3186
-4.250 -0.4778 0.00752 0.00209 -0.0014 0.6845 0.3282
-4.000 -0.4504 0.00745 0.00200 -0.0012 0.6664 0.3378
-3.750 -0.4225 0.00742 0.00191 -0.0011 0.6487 0.3466
-3.500 -0.3948 0.00738 0.00184 -0.0010 0.6324 0.3555
-3.250 -0.3668 0.00735 0.00176 -0.0008 0.6168 0.3630
-3.000 -0.3389 0.00732 0.00169 -0.0007 0.6018 0.3712
-2.750 -0.3108 0.00730 0.00163 -0.0006 0.5877 0.3784
-2.500 -0.2827 0.00727 0.00158 -0.0006 0.5742 0.3860
-2.250 -0.2546 0.00727 0.00152 -0.0005 0.5611 0.3933
-2.000 -0.2264 0.00724 0.00148 -0.0004 0.5484 0.4011
-1.750 -0.1981 0.00723 0.00144 -0.0004 0.5363 0.4081
-1.500 -0.1699 0.00721 0.00141 -0.0003 0.5249 0.4162
-1.250 -0.1416 0.00721 0.00138 -0.0002 0.5139 0.4235
-1.000 -0.1133 0.00719 0.00136 -0.0002 0.5033 0.4318
-0.750 -0.0849 0.00719 0.00134 -0.0001 0.4932 0.4395
-0.500 -0.0568 0.00719 0.00132 -0.0001 0.4834 0.4480
-0.250 -0.0283 0.00718 0.00131 0.0000 0.4740 0.4563
0.000 0.0000 0.00718 0.00131 0.0000 0.4652 0.4652
0.250 0.0283 0.00717 0.00131 0.0001 0.4563 0.4740
0.500 0.0568 0.00719 0.00132 0.0001 0.4480 0.4834
0.750 0.0849 0.00719 0.00134 0.0001 0.4395 0.4932
1.000 0.1133 0.00719 0.00136 0.0002 0.4318 0.5032
1.250 0.1416 0.00721 0.00138 0.0002 0.4235 0.5139
1.500 0.1699 0.00721 0.00141 0.0003 0.4162 0.5249
1.750 0.1980 0.00723 0.00144 0.0004 0.4081 0.5363
2.000 0.2264 0.00724 0.00148 0.0004 0.4011 0.5483
2.250 0.2545 0.00727 0.00152 0.0005 0.3933 0.5610
2.500 0.2827 0.00727 0.00158 0.0006 0.3860 0.5743
2.750 0.3108 0.00730 0.00163 0.0007 0.3785 0.5878
3.000 0.3388 0.00732 0.00169 0.0007 0.3711 0.6018
3.250 0.3668 0.00735 0.00176 0.0008 0.3630 0.6168
3.500 0.3948 0.00738 0.00184 0.0010 0.3556 0.6323
3.750 0.4225 0.00742 0.00191 0.0011 0.3467 0.6486
4.000 0.4503 0.00745 0.00200 0.0012 0.3379 0.6663
4.250 0.4778 0.00752 0.00209 0.0014 0.3282 0.6845
4.500 0.5054 0.00756 0.00218 0.0016 0.3185 0.7039
4.750 0.5325 0.00760 0.00229 0.0019 0.3083 0.7250
5.000 0.5594 0.00768 0.00241 0.0022 0.2977 0.7479
5.250 0.5861 0.00774 0.00253 0.0025 0.2861 0.7722
5.500 0.6124 0.00780 0.00267 0.0029 0.2748 0.8010
5.750 0.6380 0.00784 0.00281 0.0035 0.2647 0.8348
6.000 0.6625 0.00790 0.00297 0.0044 0.2532 0.8777
6.250 0.6930 0.00798 0.00318 0.0040 0.2398 0.9388
6.500 0.7390 0.00826 0.00342 0.0001 0.2192 0.9741
6.750 0.7763 0.00853 0.00363 -0.0019 0.2030 0.9880
7.000 0.8135 0.00883 0.00387 -0.0040 0.1866 0.9958
7.250 0.8506 0.00919 0.00413 -0.0062 0.1678 1.0000
7.500 0.8732 0.00952 0.00439 -0.0052 0.1525 1.0000
7.750 0.8957 0.00986 0.00466 -0.0042 0.1372 1.0000
8.000 0.9179 0.01024 0.00498 -0.0032 0.1210 1.0000
8.250 0.9395 0.01068 0.00533 -0.0022 0.1042 1.0000
8.500 0.9607 0.01114 0.00571 -0.0011 0.0893 1.0000
8.750 0.9818 0.01162 0.00611 0.0000 0.0758 1.0000
9.000 1.0028 0.01210 0.00652 0.0011 0.0640 1.0000
9.250 1.0240 0.01258 0.00695 0.0022 0.0543 1.0000
9.500 1.0451 0.01305 0.00739 0.0032 0.0461 1.0000
9.750 1.0660 0.01355 0.00786 0.0043 0.0389 1.0000
10.000 1.0864 0.01409 0.00837 0.0054 0.0327 1.0000
10.250 1.1060 0.01468 0.00893 0.0065 0.0277 1.0000
10.500 1.1269 0.01516 0.00942 0.0075 0.0252 1.0000
10.750 1.1452 0.01582 0.01007 0.0088 0.0223 1.0000
11.000 1.1660 0.01626 0.01055 0.0098 0.0211 1.0000
11.250 1.1850 0.01680 0.01112 0.0110 0.0198 1.0000
11.500 1.2010 0.01753 0.01186 0.0125 0.0182 1.0000
11.750 1.2184 0.01810 0.01249 0.0139 0.0174 1.0000
12.000 1.2354 0.01866 0.01310 0.0152 0.0166 1.0000
12.250 1.2499 0.01932 0.01379 0.0169 0.0157 1.0000
12.500 1.2573 0.02011 0.01461 0.0196 0.0149 1.0000
12.750 1.2592 0.02111 0.01568 0.0228 0.0141 1.0000
13.000 1.2671 0.02194 0.01657 0.0249 0.0137 1.0000
13.250 1.2738 0.02296 0.01766 0.0266 0.0133 1.0000
13.500 1.2808 0.02412 0.01887 0.0279 0.0127 1.0000
13.750 1.2847 0.02569 0.02050 0.0288 0.0122 1.0000
14.000 1.2854 0.02778 0.02265 0.0292 0.0117 1.0000
14.250 1.2804 0.03070 0.02568 0.0291 0.0112 1.0000
14.500 1.2793 0.03348 0.02856 0.0286 0.0110 1.0000
14.750 1.2829 0.03587 0.03103 0.0280 0.0107 1.0000
15.000 1.2821 0.03883 0.03408 0.0272 0.0105 1.0000
15.250 1.2814 0.04183 0.03716 0.0263 0.0101 1.0000
15.500 1.2781 0.04519 0.04060 0.0252 0.0098 1.0000
15.750 1.2716 0.04899 0.04449 0.0239 0.0097 1.0000
16.000 1.2604 0.05342 0.04903 0.0223 0.0097 1.0000
16.250 1.2544 0.05725 0.05294 0.0209 0.0094 1.0000
16.500 1.2436 0.06179 0.05756 0.0191 0.0093 1.0000
16.750 1.2324 0.06657 0.06245 0.0171 0.0093 1.0000
17.000 1.2186 0.07190 0.06785 0.0148 0.0089 1.0000
17.250 1.2072 0.07701 0.07306 0.0125 0.0090 1.0000
17.500 1.1964 0.08215 0.07830 0.0102 0.0089 1.0000
17.750 1.1763 0.08884 0.08508 0.0070 0.0087 1.0000
18.000 1.1606 0.09504 0.09139 0.0041 0.0086 1.0000
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