E186 (10.27%) (e186-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: E186 (10.27%) (e186-il) Reynolds number: 100,000 Max Cl/Cd: 46.03 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e186-il-100000.txt Download as CSV file: xf-e186-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: E186 (10.27%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.6224 0.11676 0.11247 0.0311 1.0000 0.1056
-9.750 -0.6434 0.11269 0.10852 0.0240 1.0000 0.1096
-9.500 -0.6732 0.10790 0.10386 0.0146 1.0000 0.1103
-9.250 -0.6230 0.10370 0.09956 0.0245 1.0000 0.1153
-9.000 -0.6238 0.09969 0.09559 0.0222 1.0000 0.1203
-8.750 -0.6597 0.09428 0.09031 0.0119 1.0000 0.1236
-8.500 -0.6591 0.08899 0.08507 0.0109 1.0000 0.1260
-8.250 -0.6353 0.08627 0.08235 0.0141 1.0000 0.1327
-8.000 -0.6634 0.08148 0.07758 0.0087 1.0000 0.1367
-7.750 -0.5701 0.06990 0.06640 0.0062 1.0000 0.1555
-7.500 -0.6663 0.07330 0.06934 0.0064 1.0000 0.1508
-7.250 -0.6528 0.06943 0.06554 0.0074 1.0000 0.1589
-6.500 -0.6564 0.04479 0.03895 0.0032 1.0000 0.0814
-6.250 -0.6414 0.03871 0.03214 0.0050 1.0000 0.0680
-6.000 -0.6212 0.03457 0.02768 0.0055 1.0000 0.0647
-5.750 -0.5984 0.03088 0.02344 0.0061 1.0000 0.0619
-5.500 -0.5729 0.02798 0.02003 0.0062 1.0000 0.0607
-5.250 -0.5488 0.02592 0.01768 0.0059 0.9929 0.0612
-5.000 -0.4996 0.02388 0.01531 0.0017 0.9681 0.0668
-4.750 -0.4547 0.02206 0.01317 -0.0010 0.9468 0.0698
-4.500 -0.4222 0.02023 0.01143 -0.0017 0.9257 0.0754
-4.250 -0.3989 0.01925 0.01037 -0.0003 0.9052 0.0839
-4.000 -0.3815 0.01825 0.00948 0.0021 0.8879 0.1051
-3.750 -0.3714 0.01612 0.00837 0.0055 0.8730 0.2527
-3.500 -0.3596 0.01485 0.00807 0.0086 0.8591 0.4505
-3.250 -0.3007 0.01382 0.00860 0.0059 0.8489 0.8257
-3.000 -0.2357 0.01485 0.00928 0.0019 0.8383 0.9059
-2.750 -0.1774 0.01570 0.00974 -0.0022 0.8276 0.9452
-2.500 -0.1085 0.01602 0.00965 -0.0094 0.8165 0.9758
-2.250 -0.0396 0.01567 0.00898 -0.0178 0.8047 1.0000
-2.000 -0.0205 0.01555 0.00868 -0.0171 0.7936 1.0000
-1.750 -0.0012 0.01549 0.00843 -0.0162 0.7835 1.0000
-1.500 0.0187 0.01546 0.00824 -0.0152 0.7741 1.0000
-1.250 0.0414 0.01548 0.00813 -0.0149 0.7640 1.0000
-1.000 0.0629 0.01553 0.00804 -0.0141 0.7555 1.0000
-0.750 0.0854 0.01559 0.00798 -0.0135 0.7467 1.0000
-0.500 0.1092 0.01570 0.00800 -0.0132 0.7380 1.0000
-0.250 0.1309 0.01580 0.00798 -0.0122 0.7306 1.0000
0.000 0.1563 0.01597 0.00810 -0.0123 0.7216 1.0000
0.250 0.1784 0.01611 0.00813 -0.0113 0.7148 1.0000
0.500 0.2042 0.01631 0.00831 -0.0114 0.7060 1.0000
0.750 0.2276 0.01650 0.00844 -0.0107 0.6990 1.0000
1.000 0.2527 0.01672 0.00866 -0.0106 0.6908 1.0000
1.250 0.2768 0.01697 0.00888 -0.0101 0.6837 1.0000
1.500 0.3013 0.01722 0.00913 -0.0098 0.6759 1.0000
1.750 0.3259 0.01753 0.00943 -0.0094 0.6686 1.0000
2.000 0.3501 0.01779 0.00972 -0.0089 0.6610 1.0000
2.250 0.3749 0.01814 0.01011 -0.0087 0.6531 1.0000
2.500 0.3984 0.01839 0.01036 -0.0079 0.6458 1.0000
2.750 0.4235 0.01880 0.01083 -0.0078 0.6371 1.0000
3.000 0.4460 0.01898 0.01102 -0.0065 0.6302 1.0000
3.250 0.4711 0.01939 0.01154 -0.0064 0.6201 1.0000
3.500 0.4941 0.01962 0.01180 -0.0053 0.6121 1.0000
3.750 0.5174 0.01983 0.01206 -0.0044 0.6027 1.0000
4.000 0.5414 0.02016 0.01252 -0.0038 0.5920 1.0000
4.250 0.5641 0.02027 0.01268 -0.0024 0.5826 1.0000
4.500 0.5868 0.02027 0.01271 -0.0009 0.5726 1.0000
4.750 0.6102 0.02038 0.01293 0.0001 0.5601 1.0000
5.000 0.6333 0.02039 0.01304 0.0014 0.5475 1.0000
5.250 0.6564 0.02029 0.01305 0.0029 0.5343 1.0000
5.500 0.6795 0.02007 0.01292 0.0045 0.5202 1.0000
5.750 0.7027 0.01975 0.01268 0.0061 0.5049 1.0000
6.000 0.7261 0.01930 0.01229 0.0079 0.4881 1.0000
6.250 0.7495 0.01886 0.01197 0.0095 0.4679 1.0000
6.500 0.7730 0.01832 0.01150 0.0113 0.4435 1.0000
6.750 0.7962 0.01795 0.01130 0.0126 0.4085 1.0000
7.000 0.8185 0.01778 0.01115 0.0139 0.3539 1.0000
7.250 0.8345 0.01885 0.01161 0.0149 0.2419 1.0000
7.500 0.8434 0.02143 0.01344 0.0157 0.1455 1.0000
7.750 0.8493 0.02423 0.01575 0.0174 0.0887 1.0000
8.000 0.8566 0.02658 0.01788 0.0196 0.0661 1.0000
8.250 0.8674 0.02874 0.01984 0.0219 0.0569 1.0000
8.500 0.8844 0.03038 0.02163 0.0237 0.0509 1.0000
8.750 0.9006 0.03283 0.02392 0.0251 0.0457 1.0000
9.000 0.9185 0.03466 0.02602 0.0267 0.0432 1.0000
9.250 0.9368 0.03711 0.02872 0.0282 0.0419 1.0000
9.500 0.9519 0.03992 0.03188 0.0297 0.0410 1.0000
9.750 0.9625 0.04301 0.03533 0.0313 0.0407 1.0000
10.000 0.9679 0.04632 0.03902 0.0331 0.0409 1.0000
10.250 0.9674 0.04988 0.04296 0.0349 0.0412 1.0000
10.500 0.9623 0.05343 0.04684 0.0366 0.0417 1.0000
10.750 0.9511 0.05702 0.05069 0.0384 0.0422 1.0000
11.000 0.9349 0.06021 0.05407 0.0401 0.0427 1.0000
11.250 0.9170 0.06399 0.05803 0.0405 0.0431 1.0000
11.500 0.8992 0.06821 0.06241 0.0398 0.0435 1.0000
11.750 0.8802 0.07305 0.06739 0.0382 0.0439 1.0000
12.000 0.8612 0.07841 0.07288 0.0359 0.0444 1.0000
12.250 0.8433 0.08421 0.07876 0.0332 0.0449 1.0000
12.500 0.7263 0.08215 0.07702 0.0351 0.0449 1.0000
12.750 0.7058 0.08912 0.08401 0.0325 0.0454 1.0000
|
Polar data table (+)
Polar graphs
<< Back to E186 (10.27%) (e186-il)