E186 (10.27%) (e186-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: E186 (10.27%) (e186-il) Reynolds number: 200,000 Max Cl/Cd: 58.14 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e186-il-200000-n5.txt Download as CSV file: xf-e186-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.7263 0.06803 0.06503 0.0029 1.0000 0.0150
-9.250 -0.7468 0.06279 0.05970 0.0009 1.0000 0.0147
-9.000 -0.7675 0.05793 0.05466 0.0017 1.0000 0.0148
-8.750 -0.7808 0.05303 0.04949 0.0027 1.0000 0.0149
-8.500 -0.7878 0.04831 0.04442 0.0042 1.0000 0.0150
-8.250 -0.7890 0.04396 0.03968 0.0058 1.0000 0.0151
-8.000 -0.7849 0.03999 0.03529 0.0076 1.0000 0.0151
-7.750 -0.7757 0.03662 0.03147 0.0093 1.0000 0.0152
-7.500 -0.7621 0.03326 0.02759 0.0105 0.9225 0.0154
-7.250 -0.7530 0.03021 0.02401 0.0133 0.8747 0.0157
-7.000 -0.7398 0.02777 0.02114 0.0157 0.8447 0.0161
-6.750 -0.7222 0.02594 0.01898 0.0175 0.8207 0.0165
-6.500 -0.7023 0.02476 0.01758 0.0188 0.8005 0.0174
-6.250 -0.6808 0.02369 0.01627 0.0199 0.7826 0.0184
-6.000 -0.6583 0.02240 0.01471 0.0210 0.7671 0.0190
-5.750 -0.6349 0.02109 0.01315 0.0221 0.7531 0.0193
-5.500 -0.6112 0.01993 0.01176 0.0230 0.7404 0.0197
-5.250 -0.5876 0.01893 0.01058 0.0239 0.7288 0.0202
-4.750 -0.5400 0.01728 0.00862 0.0257 0.7076 0.0214
-4.500 -0.5159 0.01662 0.00782 0.0265 0.6981 0.0221
-4.250 -0.4916 0.01604 0.00710 0.0273 0.6895 0.0228
-4.000 -0.4674 0.01540 0.00634 0.0280 0.6806 0.0255
-3.750 -0.4420 0.01499 0.00582 0.0286 0.6728 0.0283
-3.500 -0.4164 0.01460 0.00530 0.0291 0.6649 0.0310
-3.250 -0.3910 0.01415 0.00483 0.0297 0.6577 0.0399
-3.000 -0.3665 0.01360 0.00440 0.0304 0.6506 0.0760
-2.750 -0.3424 0.01304 0.00407 0.0309 0.6440 0.1381
-2.500 -0.3181 0.01254 0.00378 0.0315 0.6372 0.2028
-2.250 -0.2940 0.01209 0.00354 0.0321 0.6312 0.2724
-2.000 -0.2753 0.01117 0.00333 0.0336 0.6249 0.4340
-1.750 -0.2617 0.01010 0.00318 0.0366 0.6198 0.6404
-1.500 -0.2139 0.00951 0.00327 0.0333 0.6129 0.8280
-1.250 -0.1416 0.00973 0.00342 0.0246 0.6062 0.8908
-1.000 -0.0991 0.00994 0.00351 0.0220 0.5997 0.9177
-0.750 -0.0622 0.01014 0.00360 0.0204 0.5937 0.9356
-0.500 -0.0273 0.01031 0.00365 0.0192 0.5881 0.9500
-0.250 0.0088 0.01046 0.00371 0.0176 0.5819 0.9623
0.000 0.0459 0.01060 0.00373 0.0158 0.5767 0.9729
0.250 0.0841 0.01069 0.00377 0.0136 0.5704 0.9817
0.500 0.1254 0.01070 0.00369 0.0107 0.5647 0.9881
0.750 0.1653 0.01071 0.00364 0.0081 0.5589 0.9946
1.000 0.2061 0.01062 0.00352 0.0052 0.5528 0.9998
1.250 0.2315 0.01064 0.00347 0.0056 0.5480 1.0000
1.500 0.2569 0.01064 0.00348 0.0059 0.5420 1.0000
1.750 0.2822 0.01066 0.00348 0.0063 0.5367 1.0000
2.000 0.3076 0.01069 0.00351 0.0067 0.5314 1.0000
2.250 0.3333 0.01072 0.00355 0.0070 0.5253 1.0000
2.500 0.3587 0.01077 0.00356 0.0075 0.5202 1.0000
2.750 0.3846 0.01080 0.00365 0.0078 0.5131 1.0000
3.000 0.4102 0.01085 0.00370 0.0082 0.5067 1.0000
3.250 0.4362 0.01089 0.00379 0.0085 0.4982 1.0000
3.500 0.4619 0.01094 0.00384 0.0089 0.4904 1.0000
3.750 0.4878 0.01099 0.00394 0.0092 0.4809 1.0000
4.000 0.5137 0.01105 0.00404 0.0095 0.4708 1.0000
4.250 0.5395 0.01112 0.00417 0.0099 0.4604 1.0000
4.500 0.5653 0.01120 0.00427 0.0103 0.4489 1.0000
4.750 0.5911 0.01129 0.00441 0.0106 0.4354 1.0000
5.000 0.6170 0.01139 0.00457 0.0109 0.4206 1.0000
5.250 0.6427 0.01152 0.00475 0.0112 0.4025 1.0000
5.500 0.6683 0.01169 0.00496 0.0116 0.3800 1.0000
5.750 0.6936 0.01193 0.00518 0.0119 0.3482 1.0000
6.000 0.7181 0.01239 0.00547 0.0121 0.2957 1.0000
6.250 0.7409 0.01337 0.00604 0.0120 0.2142 1.0000
6.500 0.7628 0.01447 0.00680 0.0120 0.1471 1.0000
6.750 0.7846 0.01542 0.00757 0.0122 0.1021 1.0000
7.000 0.8057 0.01640 0.00836 0.0125 0.0663 1.0000
7.250 0.8260 0.01742 0.00924 0.0129 0.0365 1.0000
7.500 0.8454 0.01850 0.01024 0.0136 0.0200 1.0000
7.750 0.8645 0.01952 0.01131 0.0144 0.0153 1.0000
8.000 0.8835 0.02044 0.01235 0.0153 0.0136 1.0000
8.250 0.9010 0.02144 0.01346 0.0163 0.0124 1.0000
8.500 0.9155 0.02273 0.01490 0.0175 0.0115 1.0000
8.750 0.9284 0.02404 0.01634 0.0189 0.0111 1.0000
9.000 0.9405 0.02531 0.01774 0.0204 0.0107 1.0000
9.250 0.9515 0.02657 0.01913 0.0220 0.0101 1.0000
9.500 0.9608 0.02786 0.02053 0.0236 0.0096 1.0000
9.750 0.9682 0.02925 0.02203 0.0254 0.0093 1.0000
10.000 0.9721 0.03062 0.02350 0.0274 0.0086 1.0000
10.250 0.9712 0.03220 0.02518 0.0297 0.0084 1.0000
10.500 0.9726 0.03395 0.02704 0.0313 0.0083 1.0000
10.750 0.9741 0.03592 0.02911 0.0326 0.0080 1.0000
11.000 0.9763 0.03798 0.03129 0.0336 0.0078 1.0000
11.250 0.9789 0.04012 0.03356 0.0344 0.0078 1.0000
11.500 0.9801 0.04254 0.03615 0.0350 0.0076 1.0000
11.750 0.9802 0.04514 0.03889 0.0355 0.0075 1.0000
12.000 0.9796 0.04792 0.04183 0.0357 0.0075 1.0000
12.250 0.9764 0.05109 0.04516 0.0356 0.0074 1.0000
12.500 0.9718 0.05452 0.04878 0.0352 0.0073 1.0000
12.750 0.9651 0.05831 0.05274 0.0344 0.0072 1.0000
13.000 0.9579 0.06226 0.05687 0.0333 0.0072 1.0000
13.250 0.9489 0.06662 0.06141 0.0318 0.0072 1.0000
13.500 0.9371 0.07157 0.06654 0.0298 0.0072 1.0000
13.750 0.9244 0.07689 0.07204 0.0274 0.0072 1.0000
14.000 0.9109 0.08272 0.07804 0.0245 0.0072 1.0000
14.250 0.8973 0.08902 0.08450 0.0212 0.0072 1.0000
14.500 0.8802 0.09645 0.09211 0.0171 0.0073 1.0000
14.750 0.8652 0.10404 0.09985 0.0128 0.0074 1.0000
15.000 0.8425 0.11407 0.11007 0.0072 0.0075 1.0000
15.250 0.8059 0.12916 0.12535 -0.0008 0.0077 1.0000
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Polar data table (+)
Polar graphs
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