E207 (12.04%) (e207-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: E207 (12.04%) (e207-il) Reynolds number: 100,000 Max Cl/Cd: 53.29 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e207-il-100000-n5.txt Download as CSV file: xf-e207-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E207 (12.04%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4645 0.08896 0.08398 -0.0373 1.0000 0.0300
-10.000 -0.4733 0.08259 0.07767 -0.0407 1.0000 0.0300
-9.750 -0.4845 0.07549 0.07062 -0.0449 1.0000 0.0297
-9.500 -0.5037 0.06720 0.06236 -0.0512 1.0000 0.0291
-9.250 -0.5288 0.06109 0.05620 -0.0555 1.0000 0.0288
-9.000 -0.5529 0.05707 0.05214 -0.0551 1.0000 0.0285
-8.750 -0.5709 0.05308 0.04798 -0.0541 1.0000 0.0284
-8.500 -0.5840 0.04928 0.04394 -0.0523 1.0000 0.0284
-8.250 -0.5918 0.04570 0.04007 -0.0502 1.0000 0.0285
-8.000 -0.5955 0.04229 0.03633 -0.0478 1.0000 0.0286
-7.750 -0.5952 0.03917 0.03280 -0.0453 1.0000 0.0288
-7.500 -0.5912 0.03643 0.02970 -0.0428 1.0000 0.0290
-7.250 -0.5844 0.03403 0.02694 -0.0403 1.0000 0.0293
-7.000 -0.5666 0.03154 0.02401 -0.0397 0.9967 0.0299
-6.750 -0.5332 0.02908 0.02107 -0.0417 0.9877 0.0311
-6.500 -0.4999 0.02727 0.01917 -0.0440 0.9783 0.0333
-6.250 -0.4645 0.02567 0.01736 -0.0460 0.9690 0.0352
-6.000 -0.4310 0.02408 0.01553 -0.0474 0.9578 0.0366
-5.750 -0.3980 0.02268 0.01396 -0.0485 0.9457 0.0384
-5.500 -0.3653 0.02151 0.01260 -0.0495 0.9328 0.0403
-5.250 -0.3342 0.02032 0.01141 -0.0505 0.9190 0.0439
-5.000 -0.3015 0.01950 0.01044 -0.0516 0.9049 0.0505
-4.750 -0.2702 0.01851 0.00942 -0.0524 0.8904 0.0593
-4.500 -0.2395 0.01760 0.00849 -0.0530 0.8753 0.0778
-4.250 -0.2100 0.01679 0.00778 -0.0535 0.8598 0.1134
-4.000 -0.1822 0.01602 0.00725 -0.0537 0.8440 0.1769
-3.750 -0.1569 0.01522 0.00685 -0.0536 0.8284 0.2687
-3.500 -0.1317 0.01466 0.00656 -0.0531 0.8132 0.3535
-3.250 -0.1062 0.01433 0.00636 -0.0525 0.7987 0.4269
-3.000 -0.0808 0.01410 0.00617 -0.0517 0.7847 0.4882
-2.750 -0.0553 0.01392 0.00602 -0.0509 0.7713 0.5394
-2.500 -0.0297 0.01378 0.00589 -0.0501 0.7588 0.5835
-2.250 -0.0038 0.01366 0.00577 -0.0493 0.7472 0.6237
-2.000 0.0224 0.01356 0.00564 -0.0485 0.7364 0.6629
-1.750 0.0487 0.01347 0.00556 -0.0478 0.7255 0.7018
-1.500 0.0752 0.01341 0.00550 -0.0470 0.7151 0.7410
-1.250 0.1028 0.01336 0.00544 -0.0464 0.7057 0.7816
-1.000 0.1328 0.01336 0.00542 -0.0462 0.6963 0.8232
-0.750 0.1685 0.01339 0.00542 -0.0472 0.6869 0.8629
-0.500 0.2084 0.01346 0.00537 -0.0492 0.6785 0.8980
-0.250 0.2495 0.01355 0.00537 -0.0517 0.6691 0.9272
0.000 0.2908 0.01364 0.00532 -0.0543 0.6606 0.9516
0.250 0.3323 0.01372 0.00527 -0.0572 0.6522 0.9718
0.500 0.3757 0.01377 0.00522 -0.0606 0.6437 0.9885
0.750 0.4142 0.01382 0.00515 -0.0631 0.6361 1.0000
1.000 0.4356 0.01394 0.00521 -0.0622 0.6281 1.0000
1.250 0.4581 0.01408 0.00523 -0.0613 0.6215 1.0000
1.500 0.4803 0.01423 0.00536 -0.0604 0.6136 1.0000
1.750 0.5036 0.01439 0.00543 -0.0596 0.6073 1.0000
2.000 0.5264 0.01457 0.00560 -0.0588 0.5998 1.0000
2.250 0.5500 0.01475 0.00572 -0.0580 0.5933 1.0000
2.500 0.5732 0.01495 0.00592 -0.0572 0.5863 1.0000
2.750 0.5969 0.01515 0.00609 -0.0565 0.5797 1.0000
3.000 0.6205 0.01536 0.00631 -0.0557 0.5730 1.0000
3.250 0.6441 0.01558 0.00654 -0.0549 0.5661 1.0000
3.500 0.6681 0.01580 0.00676 -0.0542 0.5597 1.0000
3.750 0.6915 0.01603 0.00704 -0.0535 0.5525 1.0000
4.000 0.7159 0.01626 0.00726 -0.0528 0.5461 1.0000
4.250 0.7391 0.01650 0.00760 -0.0520 0.5381 1.0000
4.500 0.7633 0.01672 0.00783 -0.0513 0.5311 1.0000
4.750 0.7867 0.01695 0.00813 -0.0505 0.5225 1.0000
5.000 0.8102 0.01718 0.00842 -0.0497 0.5140 1.0000
5.250 0.8342 0.01737 0.00867 -0.0489 0.5054 1.0000
5.500 0.8568 0.01760 0.00901 -0.0479 0.4951 1.0000
5.750 0.8799 0.01780 0.00928 -0.0470 0.4850 1.0000
6.000 0.9033 0.01797 0.00949 -0.0461 0.4746 1.0000
6.250 0.9256 0.01817 0.00980 -0.0451 0.4626 1.0000
6.500 0.9475 0.01839 0.01015 -0.0440 0.4498 1.0000
6.750 0.9693 0.01860 0.01046 -0.0429 0.4360 1.0000
7.000 0.9905 0.01882 0.01077 -0.0417 0.4209 1.0000
7.250 1.0112 0.01906 0.01107 -0.0404 0.4042 1.0000
7.500 1.0307 0.01935 0.01147 -0.0390 0.3845 1.0000
7.750 1.0492 0.01969 0.01188 -0.0374 0.3624 1.0000
8.000 1.0664 0.02012 0.01235 -0.0357 0.3359 1.0000
8.250 1.0814 0.02068 0.01286 -0.0338 0.3053 1.0000
8.500 1.0941 0.02140 0.01351 -0.0316 0.2708 1.0000
8.750 1.1032 0.02237 0.01432 -0.0291 0.2354 1.0000
9.000 1.1101 0.02348 0.01530 -0.0264 0.2038 1.0000
9.250 1.1154 0.02469 0.01644 -0.0236 0.1774 1.0000
9.500 1.1186 0.02591 0.01759 -0.0205 0.1551 1.0000
9.750 1.1192 0.02724 0.01887 -0.0173 0.1378 1.0000
10.000 1.1205 0.02866 0.02027 -0.0146 0.1221 1.0000
10.250 1.1210 0.03024 0.02184 -0.0121 0.1083 1.0000
10.500 1.1206 0.03202 0.02361 -0.0100 0.0968 1.0000
10.750 1.1200 0.03397 0.02556 -0.0083 0.0855 1.0000
11.000 1.1201 0.03603 0.02764 -0.0070 0.0742 1.0000
11.250 1.1202 0.03824 0.02987 -0.0060 0.0637 1.0000
11.500 1.1200 0.04059 0.03226 -0.0052 0.0557 1.0000
11.750 1.1170 0.04335 0.03500 -0.0047 0.0487 1.0000
12.000 1.1171 0.04592 0.03773 -0.0043 0.0426 1.0000
12.250 1.1123 0.04908 0.04090 -0.0041 0.0392 1.0000
12.500 1.1122 0.05186 0.04383 -0.0040 0.0342 1.0000
12.750 1.1079 0.05521 0.04722 -0.0042 0.0309 1.0000
13.000 1.1040 0.05857 0.05067 -0.0044 0.0284 1.0000
13.250 1.1021 0.06177 0.05403 -0.0046 0.0263 1.0000
13.500 1.0989 0.06525 0.05762 -0.0050 0.0245 1.0000
13.750 1.0954 0.06883 0.06129 -0.0057 0.0234 1.0000
14.000 1.0907 0.07265 0.06518 -0.0064 0.0225 1.0000
14.250 1.0889 0.07618 0.06884 -0.0069 0.0215 1.0000
14.500 1.0883 0.07968 0.07252 -0.0074 0.0206 1.0000
14.750 1.0874 0.08331 0.07632 -0.0081 0.0200 1.0000
15.000 1.0851 0.08730 0.08048 -0.0092 0.0193 1.0000
15.250 1.0816 0.09156 0.08489 -0.0106 0.0187 1.0000
15.500 1.0773 0.09607 0.08955 -0.0123 0.0182 1.0000
15.750 1.0719 0.10090 0.09451 -0.0144 0.0176 1.0000
16.000 1.0659 0.10591 0.09962 -0.0166 0.0171 1.0000
16.500 1.0535 0.11645 0.11048 -0.0216 0.0167 1.0000
16.750 1.0430 0.12289 0.11705 -0.0250 0.0162 1.0000
17.000 1.0332 0.12950 0.12383 -0.0286 0.0162 1.0000
17.250 1.0165 0.13819 0.13275 -0.0338 0.0159 1.0000
17.500 1.0066 0.14531 0.14000 -0.0378 0.0162 1.0000
17.750 0.9911 0.15439 0.14919 -0.0432 0.0163 1.0000
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Polar data table (+)
Polar graphs
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