E207 (12.04%) (e207-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: E207 (12.04%) (e207-il) Reynolds number: 500,000 Max Cl/Cd: 102.68 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e207-il-500000.txt Download as CSV file: xf-e207-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.3508 0.10042 0.09827 -0.0327 1.0000 0.0267
-11.000 -0.3558 0.09468 0.09255 -0.0350 1.0000 0.0268
-10.750 -0.3748 0.08637 0.08427 -0.0373 1.0000 0.0275
-10.500 -0.3691 0.08416 0.08207 -0.0371 1.0000 0.0281
-10.250 -0.3682 0.08063 0.07855 -0.0379 1.0000 0.0286
-10.000 -0.3688 0.07682 0.07476 -0.0388 1.0000 0.0292
-9.750 -0.3751 0.07172 0.06968 -0.0405 1.0000 0.0296
-9.500 -0.3853 0.06587 0.06386 -0.0428 1.0000 0.0300
-9.250 -0.4103 0.05656 0.05459 -0.0476 1.0000 0.0299
-8.500 -0.6506 0.03770 0.03424 -0.0466 1.0000 0.0207
-8.250 -0.6496 0.03145 0.02773 -0.0456 0.9980 0.0181
-8.000 -0.6268 0.02593 0.02153 -0.0475 0.9930 0.0176
-7.750 -0.5973 0.02317 0.01840 -0.0491 0.9879 0.0179
-7.500 -0.5616 0.02179 0.01680 -0.0514 0.9843 0.0191
-7.250 -0.5299 0.02007 0.01481 -0.0526 0.9784 0.0196
-7.000 -0.4951 0.01865 0.01317 -0.0543 0.9732 0.0200
-6.750 -0.4609 0.01762 0.01196 -0.0558 0.9667 0.0203
-6.500 -0.4319 0.01533 0.00951 -0.0565 0.9574 0.0210
-6.250 -0.4026 0.01422 0.00835 -0.0571 0.9438 0.0223
-6.000 -0.3707 0.01350 0.00756 -0.0580 0.9277 0.0235
-5.750 -0.3415 0.01280 0.00675 -0.0582 0.9051 0.0244
-5.500 -0.3149 0.01225 0.00605 -0.0578 0.8790 0.0253
-5.250 -0.2904 0.01184 0.00547 -0.0569 0.8520 0.0262
-5.000 -0.2666 0.01146 0.00493 -0.0560 0.8269 0.0270
-4.750 -0.2435 0.01095 0.00427 -0.0550 0.8041 0.0300
-4.500 -0.2187 0.01070 0.00391 -0.0542 0.7833 0.0330
-4.250 -0.1939 0.01040 0.00349 -0.0535 0.7650 0.0388
-4.000 -0.1700 0.00991 0.00310 -0.0528 0.7481 0.0732
-3.750 -0.1455 0.00954 0.00285 -0.0522 0.7325 0.1202
-3.500 -0.1206 0.00924 0.00265 -0.0517 0.7186 0.1672
-3.250 -0.0958 0.00891 0.00247 -0.0513 0.7059 0.2247
-3.000 -0.0708 0.00857 0.00230 -0.0509 0.6937 0.2885
-2.750 -0.0462 0.00822 0.00219 -0.0504 0.6827 0.3700
-2.500 -0.0209 0.00801 0.00213 -0.0499 0.6727 0.4349
-2.250 0.0048 0.00787 0.00208 -0.0495 0.6631 0.4869
-2.000 0.0310 0.00774 0.00203 -0.0491 0.6537 0.5283
-1.750 0.0574 0.00768 0.00199 -0.0488 0.6456 0.5602
-1.500 0.0838 0.00759 0.00196 -0.0484 0.6370 0.5953
-1.250 0.1098 0.00751 0.00193 -0.0479 0.6295 0.6318
-1.000 0.1362 0.00743 0.00192 -0.0475 0.6217 0.6642
-0.750 0.1622 0.00737 0.00191 -0.0471 0.6148 0.6991
-0.500 0.1880 0.00727 0.00191 -0.0465 0.6074 0.7377
-0.250 0.2133 0.00719 0.00193 -0.0457 0.6011 0.7812
0.000 0.2384 0.00708 0.00197 -0.0449 0.5942 0.8290
0.250 0.2643 0.00706 0.00202 -0.0441 0.5881 0.8794
0.500 0.2976 0.00707 0.00212 -0.0449 0.5813 0.9229
0.750 0.3359 0.00719 0.00218 -0.0469 0.5748 0.9506
1.000 0.3722 0.00730 0.00226 -0.0486 0.5683 0.9695
1.250 0.4160 0.00739 0.00230 -0.0520 0.5616 0.9782
1.500 0.4579 0.00749 0.00234 -0.0550 0.5552 0.9859
1.750 0.5000 0.00755 0.00237 -0.0581 0.5484 0.9922
2.000 0.5420 0.00762 0.00238 -0.0612 0.5421 0.9974
2.250 0.5761 0.00765 0.00241 -0.0627 0.5354 1.0000
2.500 0.5994 0.00775 0.00245 -0.0618 0.5297 1.0000
2.750 0.6232 0.00779 0.00251 -0.0611 0.5230 1.0000
3.000 0.6468 0.00788 0.00256 -0.0603 0.5164 1.0000
3.250 0.6708 0.00796 0.00264 -0.0595 0.5095 1.0000
3.500 0.6947 0.00804 0.00271 -0.0587 0.5023 1.0000
3.750 0.7188 0.00813 0.00280 -0.0580 0.4951 1.0000
4.000 0.7427 0.00823 0.00288 -0.0572 0.4874 1.0000
4.250 0.7669 0.00832 0.00299 -0.0565 0.4793 1.0000
4.500 0.7908 0.00844 0.00308 -0.0557 0.4717 1.0000
4.750 0.8152 0.00852 0.00321 -0.0550 0.4633 1.0000
5.000 0.8390 0.00866 0.00333 -0.0542 0.4548 1.0000
5.250 0.8632 0.00876 0.00346 -0.0535 0.4451 1.0000
5.500 0.8873 0.00889 0.00360 -0.0528 0.4353 1.0000
5.750 0.9109 0.00904 0.00374 -0.0519 0.4246 1.0000
6.000 0.9344 0.00921 0.00391 -0.0511 0.4128 1.0000
6.250 0.9580 0.00936 0.00408 -0.0503 0.3995 1.0000
6.500 0.9811 0.00956 0.00427 -0.0494 0.3840 1.0000
6.750 1.0042 0.00978 0.00448 -0.0486 0.3667 1.0000
7.000 1.0266 0.01005 0.00472 -0.0477 0.3451 1.0000
7.250 1.0481 0.01040 0.00500 -0.0466 0.3197 1.0000
7.500 1.0669 0.01093 0.00537 -0.0452 0.2816 1.0000
7.750 1.0826 0.01172 0.00589 -0.0434 0.2306 1.0000
8.250 1.1127 0.01339 0.00713 -0.0397 0.1484 1.0000
8.500 1.1288 0.01413 0.00772 -0.0380 0.1212 1.0000
8.750 1.1451 0.01482 0.00832 -0.0363 0.1004 1.0000
9.000 1.1610 0.01550 0.00892 -0.0346 0.0823 1.0000
9.250 1.1754 0.01624 0.00958 -0.0327 0.0667 1.0000
9.500 1.1897 0.01694 0.01023 -0.0308 0.0543 1.0000
9.750 1.2024 0.01767 0.01093 -0.0287 0.0433 1.0000
10.000 1.2109 0.01844 0.01167 -0.0258 0.0334 1.0000
10.250 1.2131 0.01952 0.01269 -0.0221 0.0219 1.0000
10.500 1.2173 0.02059 0.01377 -0.0190 0.0170 1.0000
10.750 1.2187 0.02190 0.01512 -0.0158 0.0145 1.0000
11.000 1.2259 0.02294 0.01625 -0.0136 0.0134 1.0000
11.250 1.2315 0.02417 0.01756 -0.0115 0.0127 1.0000
11.500 1.2345 0.02568 0.01914 -0.0095 0.0118 1.0000
11.750 1.2333 0.02765 0.02120 -0.0076 0.0113 1.0000
12.000 1.2302 0.02997 0.02364 -0.0061 0.0108 1.0000
12.250 1.2336 0.03190 0.02568 -0.0051 0.0105 1.0000
12.500 1.2366 0.03397 0.02785 -0.0044 0.0101 1.0000
12.750 1.2399 0.03608 0.03004 -0.0039 0.0098 1.0000
13.000 1.2376 0.03884 0.03291 -0.0034 0.0095 1.0000
13.250 1.2391 0.04129 0.03545 -0.0031 0.0094 1.0000
13.500 1.2391 0.04396 0.03820 -0.0030 0.0090 1.0000
13.750 1.2387 0.04673 0.04105 -0.0030 0.0087 1.0000
14.000 1.2371 0.04969 0.04409 -0.0031 0.0085 1.0000
14.250 1.2339 0.05288 0.04738 -0.0033 0.0084 1.0000
14.500 1.2296 0.05628 0.05087 -0.0036 0.0083 1.0000
14.750 1.2224 0.06010 0.05478 -0.0039 0.0081 1.0000
15.000 1.2183 0.06364 0.05843 -0.0043 0.0080 1.0000
15.250 1.2133 0.06733 0.06223 -0.0046 0.0079 1.0000
15.500 1.2139 0.07062 0.06565 -0.0055 0.0078 1.0000
15.750 1.2118 0.07425 0.06939 -0.0063 0.0078 1.0000
16.000 1.2094 0.07809 0.07338 -0.0075 0.0077 1.0000
16.250 1.2065 0.08204 0.07745 -0.0086 0.0077 1.0000
16.500 1.2032 0.08623 0.08176 -0.0101 0.0076 1.0000
16.750 1.1985 0.09067 0.08634 -0.0117 0.0076 1.0000
17.000 1.1933 0.09537 0.09118 -0.0136 0.0076 1.0000
17.250 1.1858 0.10066 0.09663 -0.0160 0.0074 1.0000
17.500 1.1787 0.10590 0.10200 -0.0183 0.0075 1.0000
17.750 1.1697 0.11169 0.10795 -0.0211 0.0074 1.0000
18.000 1.1600 0.11775 0.11416 -0.0242 0.0074 1.0000
18.250 1.1493 0.12421 0.12077 -0.0277 0.0074 1.0000
18.500 1.1382 0.13097 0.12768 -0.0315 0.0074 1.0000
18.750 1.1245 0.13850 0.13537 -0.0359 0.0073 1.0000
19.000 1.1109 0.14611 0.14313 -0.0404 0.0075 1.0000
19.250 1.0960 0.15444 0.15160 -0.0454 0.0075 1.0000
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Polar data table (+)
Polar graphs
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