E205 (10.48%) (e205-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: E205 (10.48%) (e205-il) Reynolds number: 1,000,000 Max Cl/Cd: 128.32 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e205-il-1000000.txt Download as CSV file: xf-e205-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: E205 (10.48%)
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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3308 0.09256 0.09105 -0.0255 1.0000 0.0136
-10.000 -0.3340 0.08683 0.08533 -0.0278 1.0000 0.0146
-9.750 -0.4208 0.09294 0.09135 -0.0253 1.0000 0.0125
-9.500 -0.4198 0.08916 0.08758 -0.0270 1.0000 0.0131
-9.250 -0.4220 0.08437 0.08281 -0.0294 1.0000 0.0140
-7.750 -0.4689 0.04290 0.04097 -0.0554 0.9911 0.0149
-7.500 -0.4765 0.02980 0.02702 -0.0607 0.9764 0.0154
-7.250 -0.4541 0.02648 0.02345 -0.0621 0.9615 0.0159
-7.000 -0.4261 0.02536 0.02226 -0.0632 0.9367 0.0164
-6.750 -0.4205 0.01880 0.01478 -0.0598 0.8968 0.0132
-6.500 -0.4021 0.01698 0.01255 -0.0581 0.8630 0.0132
-6.250 -0.3810 0.01575 0.01100 -0.0568 0.8341 0.0134
-6.000 -0.3584 0.01476 0.00974 -0.0557 0.8087 0.0136
-5.750 -0.3349 0.01386 0.00861 -0.0548 0.7855 0.0137
-5.500 -0.3109 0.01310 0.00766 -0.0541 0.7652 0.0138
-5.250 -0.2863 0.01239 0.00678 -0.0533 0.7465 0.0140
-5.000 -0.2614 0.01179 0.00604 -0.0527 0.7292 0.0142
-4.750 -0.2359 0.01136 0.00548 -0.0522 0.7134 0.0145
-4.500 -0.2097 0.01107 0.00509 -0.0517 0.6992 0.0148
-4.250 -0.1851 0.01040 0.00429 -0.0510 0.6861 0.0152
-4.000 -0.1606 0.00973 0.00349 -0.0503 0.6742 0.0159
-3.750 -0.1347 0.00939 0.00305 -0.0499 0.6629 0.0166
-3.500 -0.1081 0.00914 0.00273 -0.0495 0.6522 0.0172
-3.250 -0.0813 0.00893 0.00245 -0.0493 0.6424 0.0180
-3.000 -0.0544 0.00876 0.00219 -0.0490 0.6333 0.0188
-2.750 -0.0271 0.00860 0.00198 -0.0487 0.6246 0.0199
-2.500 -0.0001 0.00841 0.00175 -0.0485 0.6165 0.0238
-2.250 0.0263 0.00811 0.00156 -0.0481 0.6085 0.0571
-2.000 0.0525 0.00782 0.00143 -0.0479 0.6015 0.1087
-1.750 0.0791 0.00758 0.00134 -0.0477 0.5941 0.1596
-1.500 0.1056 0.00737 0.00127 -0.0475 0.5874 0.2138
-1.250 0.1320 0.00711 0.00121 -0.0472 0.5808 0.2824
-1.000 0.1578 0.00685 0.00117 -0.0469 0.5746 0.3668
-0.750 0.1832 0.00650 0.00114 -0.0466 0.5683 0.4766
-0.500 0.2076 0.00616 0.00113 -0.0460 0.5622 0.5939
-0.250 0.2306 0.00576 0.00114 -0.0449 0.5568 0.7248
0.000 0.2509 0.00533 0.00118 -0.0430 0.5511 0.8737
0.250 0.2920 0.00536 0.00132 -0.0454 0.5448 0.9593
0.500 0.3285 0.00544 0.00136 -0.0471 0.5390 0.9748
0.750 0.3660 0.00555 0.00140 -0.0492 0.5327 0.9839
1.000 0.4122 0.00561 0.00142 -0.0532 0.5267 0.9882
1.250 0.4523 0.00568 0.00143 -0.0558 0.5204 0.9929
1.500 0.4940 0.00573 0.00144 -0.0589 0.5143 0.9963
1.750 0.5361 0.00576 0.00143 -0.0620 0.5075 0.9996
2.000 0.5640 0.00582 0.00145 -0.0621 0.5014 1.0000
2.250 0.5895 0.00585 0.00147 -0.0616 0.4949 1.0000
2.750 0.6400 0.00598 0.00155 -0.0605 0.4809 1.0000
3.250 0.6906 0.00612 0.00165 -0.0594 0.4664 1.0000
3.500 0.7155 0.00622 0.00172 -0.0589 0.4587 1.0000
3.750 0.7410 0.00628 0.00179 -0.0584 0.4511 1.0000
4.000 0.7660 0.00639 0.00187 -0.0578 0.4430 1.0000
4.250 0.7912 0.00648 0.00196 -0.0573 0.4343 1.0000
4.500 0.8162 0.00658 0.00205 -0.0567 0.4251 1.0000
4.750 0.8409 0.00672 0.00215 -0.0561 0.4154 1.0000
5.000 0.8660 0.00682 0.00226 -0.0555 0.4050 1.0000
5.250 0.8907 0.00696 0.00239 -0.0549 0.3939 1.0000
5.500 0.9149 0.00713 0.00252 -0.0543 0.3784 1.0000
5.750 0.9382 0.00737 0.00269 -0.0534 0.3559 1.0000
6.000 0.9606 0.00769 0.00288 -0.0525 0.3260 1.0000
6.250 0.9824 0.00807 0.00314 -0.0515 0.2933 1.0000
6.500 1.0028 0.00855 0.00345 -0.0503 0.2556 1.0000
6.750 1.0211 0.00921 0.00386 -0.0488 0.2080 1.0000
7.000 1.0391 0.00988 0.00431 -0.0472 0.1653 1.0000
7.250 1.0580 0.01046 0.00473 -0.0458 0.1340 1.0000
7.500 1.0766 0.01105 0.00517 -0.0444 0.1045 1.0000
7.750 1.0954 0.01163 0.00562 -0.0430 0.0803 1.0000
8.000 1.1138 0.01224 0.00611 -0.0415 0.0589 1.0000
8.250 1.1319 0.01287 0.00663 -0.0400 0.0399 1.0000
8.500 1.1455 0.01383 0.00741 -0.0379 0.0151 1.0000
8.750 1.1630 0.01449 0.00804 -0.0363 0.0097 1.0000
9.000 1.1815 0.01505 0.00865 -0.0349 0.0083 1.0000
9.250 1.2002 0.01556 0.00922 -0.0335 0.0078 1.0000
9.500 1.2180 0.01612 0.00983 -0.0321 0.0073 1.0000
9.750 1.2348 0.01670 0.01046 -0.0305 0.0069 1.0000
10.000 1.2445 0.01770 0.01156 -0.0278 0.0061 1.0000
10.250 1.2543 0.01848 0.01242 -0.0252 0.0060 1.0000
10.500 1.2635 0.01916 0.01316 -0.0224 0.0059 1.0000
10.750 1.2716 0.01993 0.01401 -0.0196 0.0058 1.0000
11.000 1.2780 0.02087 0.01502 -0.0169 0.0057 1.0000
11.250 1.2869 0.02173 0.01595 -0.0148 0.0056 1.0000
11.500 1.2911 0.02295 0.01726 -0.0124 0.0055 1.0000
11.750 1.2947 0.02435 0.01875 -0.0103 0.0055 1.0000
12.000 1.3001 0.02575 0.02023 -0.0088 0.0053 1.0000
12.250 1.3011 0.02763 0.02222 -0.0072 0.0052 1.0000
12.500 1.3032 0.02959 0.02426 -0.0061 0.0052 1.0000
12.750 1.3053 0.03166 0.02643 -0.0053 0.0051 1.0000
13.000 1.3099 0.03361 0.02845 -0.0047 0.0049 1.0000
13.250 1.3103 0.03605 0.03099 -0.0042 0.0049 1.0000
13.500 1.3122 0.03843 0.03344 -0.0040 0.0048 1.0000
13.750 1.3057 0.04175 0.03690 -0.0037 0.0049 1.0000
14.000 1.3085 0.04416 0.03937 -0.0038 0.0047 1.0000
14.250 1.3058 0.04722 0.04252 -0.0038 0.0047 1.0000
14.500 1.3029 0.05036 0.04576 -0.0041 0.0046 1.0000
14.750 1.2988 0.05374 0.04924 -0.0043 0.0047 1.0000
15.000 1.2932 0.05739 0.05296 -0.0050 0.0044 1.0000
15.250 1.2877 0.06117 0.05684 -0.0057 0.0044 1.0000
15.500 1.2775 0.06561 0.06138 -0.0065 0.0043 1.0000
15.750 1.2796 0.06874 0.06462 -0.0075 0.0044 1.0000
16.000 1.2666 0.07378 0.06978 -0.0087 0.0042 1.0000
16.250 1.2623 0.07793 0.07403 -0.0100 0.0043 1.0000
16.500 1.2601 0.08194 0.07814 -0.0116 0.0043 1.0000
16.750 1.2433 0.08800 0.08436 -0.0133 0.0042 1.0000
17.000 1.2367 0.09293 0.08940 -0.0154 0.0042 1.0000
17.250 1.2207 0.09942 0.09606 -0.0179 0.0041 1.0000
17.500 1.2031 0.10660 0.10342 -0.0210 0.0041 1.0000
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Polar data table (+)
Polar graphs
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