E186 (10.27%) (e186-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: E186 (10.27%) (e186-il) Reynolds number: 1,000,000 Max Cl/Cd: 90.72 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e186-il-1000000.txt Download as CSV file: xf-e186-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.8005 0.05984 0.05843 0.0041 1.0000 0.0079
-9.750 -0.8348 0.05363 0.05206 0.0031 1.0000 0.0078
-9.500 -0.8677 0.04862 0.04685 0.0064 1.0000 0.0077
-9.250 -0.8931 0.04187 0.03971 0.0094 1.0000 0.0077
-9.000 -0.9013 0.03678 0.03422 0.0122 1.0000 0.0078
-8.750 -0.8981 0.03336 0.03034 0.0147 1.0000 0.0083
-8.500 -0.9060 0.02870 0.02509 0.0192 0.8892 0.0087
-8.250 -0.8909 0.02761 0.02379 0.0209 0.8491 0.0090
-8.000 -0.8737 0.02628 0.02221 0.0223 0.8188 0.0092
-7.750 -0.8529 0.02553 0.02132 0.0232 0.7933 0.0096
-7.500 -0.8338 0.02404 0.01955 0.0245 0.7723 0.0099
-7.250 -0.8146 0.02221 0.01742 0.0259 0.7541 0.0102
-7.000 -0.7937 0.02063 0.01556 0.0271 0.7376 0.0104
-6.750 -0.7715 0.01926 0.01395 0.0282 0.7227 0.0107
-6.500 -0.7481 0.01814 0.01262 0.0290 0.7094 0.0110
-6.250 -0.7236 0.01732 0.01163 0.0297 0.6972 0.0114
-6.000 -0.6971 0.01734 0.01154 0.0301 0.6856 0.0119
-5.750 -0.6758 0.01514 0.00907 0.0313 0.6756 0.0125
-5.500 -0.6526 0.01396 0.00777 0.0323 0.6665 0.0129
-5.250 -0.6284 0.01319 0.00690 0.0330 0.6578 0.0132
-5.000 -0.6036 0.01256 0.00621 0.0337 0.6492 0.0137
-4.750 -0.5786 0.01202 0.00558 0.0343 0.6417 0.0140
-4.500 -0.5533 0.01153 0.00500 0.0349 0.6343 0.0144
-4.250 -0.5274 0.01116 0.00456 0.0353 0.6276 0.0152
-4.000 -0.5015 0.01076 0.00409 0.0359 0.6207 0.0158
-3.750 -0.4753 0.01043 0.00367 0.0363 0.6146 0.0165
-3.500 -0.4487 0.01014 0.00333 0.0367 0.6085 0.0170
-3.250 -0.4221 0.00988 0.00299 0.0370 0.6025 0.0174
-3.000 -0.3955 0.00957 0.00261 0.0374 0.5970 0.0186
-2.750 -0.3685 0.00935 0.00233 0.0378 0.5913 0.0206
-2.250 -0.3172 0.00855 0.00184 0.0387 0.5808 0.0996
-2.000 -0.2920 0.00814 0.00167 0.0391 0.5756 0.1660
-1.750 -0.2668 0.00777 0.00153 0.0396 0.5707 0.2351
-1.500 -0.2421 0.00732 0.00139 0.0401 0.5658 0.3235
-1.250 -0.2182 0.00686 0.00127 0.0408 0.5607 0.4257
-1.000 -0.1947 0.00644 0.00118 0.0416 0.5561 0.5271
-0.750 -0.1737 0.00589 0.00109 0.0430 0.5515 0.6510
-0.500 -0.1575 0.00525 0.00100 0.0457 0.5468 0.8012
-0.250 -0.0810 0.00510 0.00125 0.0354 0.5408 0.9344
0.000 -0.0443 0.00526 0.00139 0.0337 0.5356 0.9481
0.250 -0.0153 0.00543 0.00149 0.0337 0.5306 0.9595
0.500 0.0220 0.00559 0.00161 0.0318 0.5256 0.9652
0.750 0.0524 0.00572 0.00172 0.0314 0.5205 0.9719
1.000 0.0919 0.00585 0.00178 0.0290 0.5151 0.9743
1.250 0.1298 0.00595 0.00187 0.0268 0.5098 0.9776
1.500 0.1624 0.00610 0.00198 0.0259 0.5040 0.9825
1.750 0.2007 0.00617 0.00202 0.0237 0.4976 0.9846
2.000 0.2403 0.00620 0.00203 0.0212 0.4903 0.9865
2.250 0.2787 0.00625 0.00204 0.0189 0.4833 0.9888
2.500 0.3159 0.00628 0.00206 0.0168 0.4757 0.9916
2.750 0.3511 0.00635 0.00211 0.0152 0.4679 0.9943
3.000 0.3897 0.00630 0.00205 0.0129 0.4592 0.9960
3.250 0.4271 0.00627 0.00202 0.0107 0.4504 0.9980
3.500 0.4637 0.00626 0.00199 0.0088 0.4405 0.9998
3.750 0.4908 0.00629 0.00201 0.0088 0.4311 1.0000
4.000 0.5168 0.00633 0.00206 0.0092 0.4214 1.0000
4.250 0.5429 0.00639 0.00211 0.0094 0.4096 1.0000
4.500 0.5690 0.00648 0.00216 0.0097 0.3924 1.0000
4.750 0.5951 0.00664 0.00224 0.0099 0.3651 1.0000
5.000 0.6214 0.00685 0.00236 0.0100 0.3347 1.0000
5.250 0.6475 0.00734 0.00258 0.0099 0.2709 1.0000
5.500 0.6734 0.00798 0.00291 0.0097 0.2027 1.0000
5.750 0.6993 0.00852 0.00324 0.0095 0.1538 1.0000
6.000 0.7250 0.00908 0.00360 0.0094 0.1099 1.0000
6.250 0.7504 0.00964 0.00398 0.0094 0.0725 1.0000
6.500 0.7754 0.01024 0.00441 0.0094 0.0404 1.0000
6.750 0.7996 0.01111 0.00508 0.0095 0.0111 1.0000
7.000 0.8243 0.01160 0.00561 0.0098 0.0088 1.0000
7.250 0.8488 0.01200 0.00607 0.0102 0.0081 1.0000
7.500 0.8730 0.01246 0.00658 0.0106 0.0076 1.0000
7.750 0.8967 0.01296 0.00714 0.0110 0.0072 1.0000
8.000 0.9197 0.01354 0.00777 0.0115 0.0068 1.0000
8.250 0.9415 0.01431 0.00862 0.0120 0.0064 1.0000
8.500 0.9597 0.01563 0.01009 0.0129 0.0060 1.0000
8.750 0.9803 0.01636 0.01090 0.0137 0.0059 1.0000
9.000 0.9998 0.01715 0.01177 0.0145 0.0057 1.0000
9.250 1.0184 0.01798 0.01268 0.0155 0.0055 1.0000
9.500 1.0346 0.01903 0.01382 0.0167 0.0054 1.0000
9.750 1.0493 0.02013 0.01502 0.0181 0.0052 1.0000
10.000 1.0619 0.02135 0.01633 0.0197 0.0052 1.0000
10.250 1.0720 0.02272 0.01781 0.0216 0.0051 1.0000
10.500 1.0802 0.02414 0.01934 0.0236 0.0051 1.0000
10.750 1.0854 0.02575 0.02109 0.0258 0.0051 1.0000
11.000 1.0822 0.02727 0.02272 0.0291 0.0051 1.0000
11.250 1.0770 0.02908 0.02465 0.0319 0.0052 1.0000
11.500 1.0757 0.03109 0.02679 0.0336 0.0052 1.0000
11.750 1.0732 0.03350 0.02936 0.0350 0.0052 1.0000
12.000 1.0741 0.03558 0.03154 0.0357 0.0051 1.0000
12.250 1.0719 0.03817 0.03428 0.0362 0.0051 1.0000
12.500 1.0717 0.04058 0.03679 0.0362 0.0050 1.0000
12.750 1.0678 0.04356 0.03990 0.0361 0.0049 1.0000
13.000 1.0541 0.04797 0.04454 0.0357 0.0050 1.0000
13.250 1.0444 0.05195 0.04867 0.0348 0.0051 1.0000
13.500 1.0323 0.05641 0.05329 0.0335 0.0051 1.0000
13.750 1.0149 0.06182 0.05888 0.0316 0.0053 1.0000
14.000 1.0014 0.06691 0.06410 0.0294 0.0053 1.0000
14.250 0.9862 0.07261 0.06994 0.0268 0.0053 1.0000
14.500 0.9629 0.08020 0.07770 0.0230 0.0054 1.0000
14.750 0.9409 0.08816 0.08581 0.0187 0.0055 1.0000
15.000 0.9228 0.09584 0.09360 0.0145 0.0055 1.0000
|
Polar data table (+)
Polar graphs
<< Back to E186 (10.27%) (e186-il)