E186 (10.27%) (e186-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: E186 (10.27%) (e186-il) Reynolds number: 500,000 Max Cl/Cd: 79.73 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e186-il-500000.txt Download as CSV file: xf-e186-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.6829 0.08369 0.08188 0.0173 1.0000 0.0210
-9.000 -0.7047 0.07479 0.07300 0.0086 1.0000 0.0203
-8.750 -0.7281 0.06827 0.06641 0.0061 1.0000 0.0202
-8.500 -0.7431 0.06288 0.06090 0.0058 1.0000 0.0204
-8.250 -0.7509 0.05758 0.05544 0.0058 1.0000 0.0209
-8.000 -0.7540 0.05240 0.05005 0.0064 1.0000 0.0216
-7.750 -0.7420 0.05022 0.04741 0.0081 1.0000 0.0242
-7.500 -0.7647 0.04176 0.03829 0.0120 0.8933 0.0250
-7.250 -0.7598 0.03837 0.03468 0.0144 0.8536 0.0260
-7.000 -0.7447 0.03676 0.03292 0.0157 0.8241 0.0269
-6.500 -0.7195 0.02842 0.02347 0.0214 0.7845 0.0226
-6.250 -0.7069 0.02256 0.01677 0.0247 0.7698 0.0195
-6.000 -0.6844 0.01997 0.01372 0.0263 0.7549 0.0187
-5.750 -0.6605 0.01842 0.01192 0.0273 0.7412 0.0188
-5.500 -0.6361 0.01716 0.01047 0.0281 0.7289 0.0191
-5.250 -0.6115 0.01611 0.00927 0.0289 0.7173 0.0194
-5.000 -0.5867 0.01525 0.00829 0.0296 0.7066 0.0200
-4.750 -0.5618 0.01459 0.00753 0.0302 0.6969 0.0209
-4.500 -0.5371 0.01390 0.00671 0.0310 0.6880 0.0216
-4.250 -0.5124 0.01322 0.00593 0.0318 0.6792 0.0222
-4.000 -0.4875 0.01268 0.00527 0.0325 0.6716 0.0230
-3.750 -0.4619 0.01222 0.00473 0.0331 0.6635 0.0239
-3.500 -0.4365 0.01179 0.00417 0.0338 0.6567 0.0249
-3.250 -0.4107 0.01133 0.00364 0.0343 0.6492 0.0277
-3.000 -0.3844 0.01106 0.00330 0.0348 0.6430 0.0328
-2.750 -0.3605 0.01033 0.00290 0.0355 0.6363 0.0984
-2.500 -0.3368 0.00974 0.00262 0.0362 0.6303 0.1873
-2.250 -0.3128 0.00920 0.00243 0.0368 0.6241 0.2779
-2.000 -0.2896 0.00865 0.00225 0.0375 0.6182 0.3834
-1.750 -0.2686 0.00802 0.00209 0.0388 0.6129 0.5129
-1.500 -0.2520 0.00724 0.00196 0.0412 0.6072 0.6731
-1.250 -0.2316 0.00665 0.00189 0.0432 0.6020 0.8116
-1.000 -0.1364 0.00690 0.00239 0.0295 0.5946 0.9338
-0.750 -0.1006 0.00716 0.00255 0.0282 0.5889 0.9489
-0.500 -0.0655 0.00739 0.00269 0.0270 0.5835 0.9599
-0.250 -0.0254 0.00760 0.00283 0.0246 0.5774 0.9684
0.000 0.0159 0.00779 0.00291 0.0219 0.5720 0.9744
0.250 0.0564 0.00790 0.00298 0.0193 0.5661 0.9805
0.500 0.0969 0.00797 0.00299 0.0166 0.5604 0.9853
0.750 0.1403 0.00799 0.00294 0.0133 0.5549 0.9896
1.000 0.1803 0.00800 0.00293 0.0107 0.5488 0.9943
1.250 0.2222 0.00791 0.00277 0.0076 0.5434 0.9978
1.500 0.2574 0.00783 0.00270 0.0060 0.5376 1.0000
1.750 0.2824 0.00781 0.00266 0.0064 0.5319 1.0000
2.000 0.3076 0.00783 0.00264 0.0069 0.5263 1.0000
2.250 0.3330 0.00780 0.00263 0.0073 0.5195 1.0000
2.500 0.3583 0.00783 0.00261 0.0077 0.5131 1.0000
2.750 0.3840 0.00780 0.00262 0.0081 0.5058 1.0000
3.000 0.4096 0.00784 0.00262 0.0085 0.4991 1.0000
3.250 0.4355 0.00783 0.00265 0.0089 0.4908 1.0000
3.500 0.4614 0.00786 0.00268 0.0092 0.4833 1.0000
3.750 0.4874 0.00787 0.00271 0.0096 0.4746 1.0000
4.000 0.5135 0.00791 0.00278 0.0099 0.4657 1.0000
4.250 0.5395 0.00796 0.00282 0.0102 0.4563 1.0000
4.500 0.5657 0.00800 0.00290 0.0105 0.4455 1.0000
4.750 0.5919 0.00805 0.00298 0.0108 0.4332 1.0000
5.000 0.6181 0.00813 0.00307 0.0110 0.4170 1.0000
5.250 0.6444 0.00824 0.00317 0.0112 0.3986 1.0000
5.500 0.6705 0.00841 0.00329 0.0114 0.3689 1.0000
5.750 0.6965 0.00876 0.00348 0.0115 0.3200 1.0000
6.000 0.7220 0.00940 0.00384 0.0113 0.2511 1.0000
6.250 0.7465 0.01038 0.00442 0.0109 0.1698 1.0000
6.500 0.7707 0.01117 0.00496 0.0109 0.1173 1.0000
6.750 0.7946 0.01195 0.00553 0.0109 0.0753 1.0000
7.000 0.8164 0.01322 0.00646 0.0110 0.0236 1.0000
7.250 0.8393 0.01404 0.00731 0.0115 0.0158 1.0000
7.500 0.8615 0.01488 0.00822 0.0121 0.0135 1.0000
7.750 0.8829 0.01572 0.00917 0.0127 0.0124 1.0000
8.000 0.9045 0.01640 0.00992 0.0133 0.0115 1.0000
8.250 0.9245 0.01725 0.01085 0.0141 0.0109 1.0000
8.500 0.9432 0.01820 0.01188 0.0151 0.0104 1.0000
8.750 0.9602 0.01924 0.01300 0.0161 0.0099 1.0000
9.000 0.9746 0.02051 0.01437 0.0175 0.0096 1.0000
9.250 0.9854 0.02207 0.01602 0.0192 0.0093 1.0000
9.500 0.9916 0.02412 0.01819 0.0215 0.0090 1.0000
9.750 1.0001 0.02598 0.02018 0.0237 0.0088 1.0000
10.000 1.0103 0.02755 0.02187 0.0256 0.0088 1.0000
10.250 1.0194 0.02925 0.02370 0.0275 0.0088 1.0000
10.500 1.0265 0.03137 0.02597 0.0295 0.0088 1.0000
10.750 1.0285 0.03355 0.02833 0.0320 0.0088 1.0000
11.000 1.0287 0.03607 0.03101 0.0345 0.0089 1.0000
11.250 1.0283 0.03753 0.03257 0.0366 0.0090 1.0000
11.500 1.0275 0.03942 0.03460 0.0380 0.0091 1.0000
11.750 1.0253 0.04174 0.03711 0.0390 0.0091 1.0000
12.000 1.0240 0.04391 0.03944 0.0394 0.0093 1.0000
12.250 0.9826 0.05241 0.04864 0.0393 0.0111 1.0000
12.500 0.9639 0.05756 0.05400 0.0381 0.0116 1.0000
12.750 0.9414 0.06351 0.06015 0.0360 0.0120 1.0000
13.000 0.9171 0.07008 0.06688 0.0332 0.0123 1.0000
14.250 0.7397 0.09111 0.08851 0.0259 0.0113 1.0000
14.500 0.7146 0.09975 0.09726 0.0217 0.0113 1.0000
14.750 0.5563 0.13931 0.13705 0.0047 0.0235 1.0000
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Polar data table (+)
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