E205 (10.48%) (e205-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: E205 (10.48%) (e205-il) Reynolds number: 1,000,000 Max Cl/Cd: 116.53 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e205-il-1000000-n5.txt Download as CSV file: xf-e205-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.7236 0.03925 0.03734 -0.0576 1.0000 0.0065
-10.250 -0.7391 0.03440 0.03219 -0.0565 1.0000 0.0066
-10.000 -0.7340 0.03199 0.02961 -0.0554 0.9993 0.0066
-9.750 -0.7140 0.02967 0.02709 -0.0568 0.9918 0.0067
-9.500 -0.6891 0.02762 0.02484 -0.0586 0.9850 0.0069
-9.250 -0.6653 0.02560 0.02260 -0.0598 0.9747 0.0071
-9.000 -0.6408 0.02334 0.02006 -0.0610 0.9575 0.0072
-8.750 -0.6165 0.02165 0.01808 -0.0615 0.9206 0.0074
-8.500 -0.5992 0.02045 0.01654 -0.0601 0.8771 0.0076
-8.250 -0.5808 0.01938 0.01517 -0.0587 0.8435 0.0078
-8.000 -0.5610 0.01839 0.01390 -0.0576 0.8138 0.0080
-7.750 -0.5400 0.01740 0.01266 -0.0566 0.7891 0.0081
-7.500 -0.5177 0.01661 0.01165 -0.0558 0.7675 0.0083
-7.250 -0.4945 0.01590 0.01075 -0.0551 0.7481 0.0085
-7.000 -0.4709 0.01523 0.00989 -0.0544 0.7296 0.0086
-6.750 -0.4469 0.01456 0.00904 -0.0538 0.7135 0.0087
-6.500 -0.4224 0.01398 0.00830 -0.0532 0.6987 0.0089
-6.250 -0.3975 0.01347 0.00766 -0.0528 0.6848 0.0090
-6.000 -0.3723 0.01297 0.00703 -0.0523 0.6726 0.0090
-5.750 -0.3467 0.01254 0.00649 -0.0519 0.6614 0.0091
-5.500 -0.3211 0.01212 0.00595 -0.0514 0.6505 0.0092
-5.000 -0.2713 0.01093 0.00455 -0.0504 0.6309 0.0098
-4.750 -0.2455 0.01051 0.00403 -0.0500 0.6221 0.0101
-4.500 -0.2193 0.01019 0.00364 -0.0496 0.6132 0.0105
-4.250 -0.1926 0.00992 0.00331 -0.0493 0.6057 0.0109
-4.000 -0.1659 0.00970 0.00301 -0.0491 0.5977 0.0112
-3.750 -0.1389 0.00949 0.00276 -0.0489 0.5906 0.0118
-3.500 -0.1118 0.00931 0.00252 -0.0486 0.5834 0.0122
-3.250 -0.0846 0.00915 0.00230 -0.0484 0.5770 0.0125
-3.000 -0.0573 0.00901 0.00210 -0.0483 0.5702 0.0129
-2.750 -0.0299 0.00888 0.00193 -0.0481 0.5643 0.0133
-2.500 -0.0024 0.00877 0.00178 -0.0480 0.5580 0.0135
-2.250 0.0250 0.00866 0.00162 -0.0478 0.5521 0.0145
-2.000 0.0526 0.00854 0.00148 -0.0477 0.5464 0.0167
-1.750 0.0799 0.00843 0.00136 -0.0475 0.5408 0.0232
-1.500 0.1068 0.00820 0.00126 -0.0473 0.5356 0.0581
-1.250 0.1339 0.00804 0.00118 -0.0472 0.5298 0.0878
-1.000 0.1609 0.00790 0.00112 -0.0470 0.5247 0.1213
-0.750 0.1881 0.00773 0.00107 -0.0469 0.5196 0.1636
-0.500 0.2147 0.00753 0.00103 -0.0468 0.5140 0.2232
-0.250 0.2407 0.00724 0.00101 -0.0465 0.5091 0.3165
0.000 0.2667 0.00694 0.00100 -0.0463 0.5041 0.4148
0.250 0.2925 0.00670 0.00100 -0.0459 0.4984 0.5046
0.500 0.3184 0.00649 0.00101 -0.0456 0.4938 0.5856
0.750 0.3438 0.00627 0.00103 -0.0451 0.4887 0.6689
1.000 0.3674 0.00601 0.00106 -0.0442 0.4833 0.7695
1.250 0.3900 0.00573 0.00111 -0.0428 0.4786 0.8740
1.500 0.4271 0.00572 0.00123 -0.0445 0.4725 0.9494
1.750 0.4603 0.00581 0.00129 -0.0456 0.4668 0.9688
2.000 0.4952 0.00588 0.00134 -0.0471 0.4605 0.9778
2.250 0.5283 0.00598 0.00139 -0.0483 0.4534 0.9841
2.500 0.5663 0.00605 0.00144 -0.0505 0.4451 0.9877
2.750 0.6014 0.00615 0.00150 -0.0522 0.4362 0.9916
3.000 0.6365 0.00626 0.00156 -0.0538 0.4263 0.9948
3.250 0.6745 0.00634 0.00160 -0.0561 0.4162 0.9975
3.500 0.7123 0.00644 0.00167 -0.0584 0.4052 1.0000
3.750 0.7371 0.00656 0.00176 -0.0578 0.3950 1.0000
4.000 0.7618 0.00669 0.00185 -0.0572 0.3839 1.0000
4.250 0.7865 0.00682 0.00195 -0.0566 0.3715 1.0000
4.500 0.8109 0.00698 0.00208 -0.0559 0.3578 1.0000
4.750 0.8349 0.00718 0.00221 -0.0552 0.3417 1.0000
5.000 0.8588 0.00737 0.00236 -0.0545 0.3257 1.0000
5.250 0.8818 0.00765 0.00254 -0.0537 0.3010 1.0000
5.500 0.9019 0.00819 0.00285 -0.0524 0.2529 1.0000
5.750 0.9195 0.00892 0.00327 -0.0508 0.1932 1.0000
6.000 0.9383 0.00953 0.00366 -0.0493 0.1503 1.0000
6.250 0.9586 0.01002 0.00401 -0.0481 0.1221 1.0000
6.500 0.9797 0.01042 0.00432 -0.0470 0.1018 1.0000
7.000 1.0209 0.01129 0.00503 -0.0446 0.0655 1.0000
7.250 1.0399 0.01185 0.00546 -0.0432 0.0444 1.0000
7.500 1.0587 0.01242 0.00593 -0.0418 0.0277 1.0000
7.750 1.0782 0.01294 0.00638 -0.0405 0.0160 1.0000
8.000 1.0964 0.01356 0.00694 -0.0390 0.0067 1.0000
8.250 1.1175 0.01393 0.00736 -0.0380 0.0059 1.0000
8.500 1.1380 0.01436 0.00781 -0.0369 0.0052 1.0000
8.750 1.1582 0.01479 0.00828 -0.0357 0.0048 1.0000
9.000 1.1775 0.01527 0.00882 -0.0345 0.0044 1.0000
9.250 1.1967 0.01574 0.00933 -0.0332 0.0042 1.0000
9.500 1.2157 0.01619 0.00982 -0.0320 0.0041 1.0000
9.750 1.2337 0.01669 0.01038 -0.0306 0.0039 1.0000
10.000 1.2508 0.01720 0.01094 -0.0291 0.0037 1.0000
10.250 1.2657 0.01781 0.01160 -0.0273 0.0035 1.0000
10.500 1.2786 0.01835 0.01219 -0.0250 0.0034 1.0000
10.750 1.2882 0.01900 0.01290 -0.0223 0.0032 1.0000
11.000 1.2978 0.01969 0.01365 -0.0198 0.0032 1.0000
11.250 1.3062 0.02051 0.01454 -0.0174 0.0031 1.0000
11.500 1.3137 0.02143 0.01552 -0.0151 0.0030 1.0000
11.750 1.3204 0.02248 0.01666 -0.0129 0.0029 1.0000
12.000 1.3257 0.02372 0.01798 -0.0110 0.0028 1.0000
12.250 1.3300 0.02515 0.01949 -0.0092 0.0028 1.0000
12.500 1.3339 0.02673 0.02116 -0.0078 0.0027 1.0000
12.750 1.3337 0.02882 0.02335 -0.0064 0.0026 1.0000
13.000 1.3334 0.03106 0.02570 -0.0055 0.0026 1.0000
13.250 1.3309 0.03368 0.02844 -0.0047 0.0025 1.0000
13.500 1.3296 0.03630 0.03117 -0.0043 0.0025 1.0000
13.750 1.3331 0.03851 0.03346 -0.0041 0.0025 1.0000
14.000 1.3342 0.04104 0.03608 -0.0040 0.0025 1.0000
14.250 1.3347 0.04370 0.03883 -0.0041 0.0025 1.0000
14.500 1.3329 0.04669 0.04192 -0.0042 0.0025 1.0000
14.750 1.3317 0.04966 0.04498 -0.0045 0.0024 1.0000
15.000 1.3287 0.05292 0.04834 -0.0050 0.0024 1.0000
15.250 1.3268 0.05617 0.05169 -0.0056 0.0024 1.0000
15.500 1.3261 0.05935 0.05497 -0.0063 0.0023 1.0000
15.750 1.3170 0.06379 0.05952 -0.0074 0.0024 1.0000
16.000 1.3126 0.06772 0.06356 -0.0085 0.0023 1.0000
16.250 1.3099 0.07152 0.06744 -0.0098 0.0023 1.0000
16.500 1.2997 0.07655 0.07260 -0.0115 0.0023 1.0000
16.750 1.2920 0.08138 0.07754 -0.0133 0.0023 1.0000
17.000 1.2863 0.08600 0.08226 -0.0151 0.0022 1.0000
17.250 1.2740 0.09181 0.08819 -0.0175 0.0023 1.0000
17.500 1.2699 0.09647 0.09295 -0.0196 0.0022 1.0000
17.750 1.2599 0.10220 0.09879 -0.0222 0.0022 1.0000
18.000 1.2505 0.10800 0.10470 -0.0249 0.0022 1.0000
18.250 1.2399 0.11416 0.11097 -0.0279 0.0022 1.0000
18.500 1.2276 0.12078 0.11770 -0.0313 0.0022 1.0000
18.750 1.2161 0.12739 0.12442 -0.0347 0.0022 1.0000
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