E207 (12.04%) (e207-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: E207 (12.04%) (e207-il) Reynolds number: 1,000,000 Max Cl/Cd: 112.75 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e207-il-1000000-n5.txt Download as CSV file: xf-e207-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -0.8132 0.08875 0.08667 -0.0346 1.0000 0.0058
-15.000 -0.8905 0.07046 0.06821 -0.0452 1.0000 0.0057
-14.750 -0.9626 0.05283 0.05030 -0.0575 1.0000 0.0055
-14.500 -0.9861 0.04480 0.04208 -0.0639 1.0000 0.0056
-14.250 -0.9923 0.04021 0.03737 -0.0674 1.0000 0.0056
-14.000 -1.0130 0.03468 0.03163 -0.0711 1.0000 0.0056
-13.750 -1.0201 0.03190 0.02870 -0.0714 1.0000 0.0056
-13.500 -1.0246 0.02993 0.02662 -0.0701 1.0000 0.0056
-13.250 -1.0277 0.02850 0.02507 -0.0675 1.0000 0.0057
-13.000 -1.0286 0.02743 0.02391 -0.0642 1.0000 0.0057
-12.750 -1.0255 0.02616 0.02252 -0.0615 1.0000 0.0058
-12.500 -1.0237 0.02463 0.02084 -0.0587 1.0000 0.0059
-12.250 -1.0122 0.02379 0.01993 -0.0568 1.0000 0.0062
-12.000 -1.0010 0.02287 0.01892 -0.0547 1.0000 0.0062
-11.750 -0.9859 0.02228 0.01828 -0.0530 1.0000 0.0064
-11.500 -0.9707 0.02168 0.01763 -0.0513 1.0000 0.0065
-11.250 -0.9424 0.02108 0.01698 -0.0521 0.9983 0.0067
-11.000 -0.9129 0.02057 0.01643 -0.0532 0.9960 0.0070
-10.750 -0.8834 0.02002 0.01582 -0.0542 0.9936 0.0073
-10.500 -0.8570 0.01925 0.01494 -0.0546 0.9900 0.0075
-10.250 -0.8282 0.01856 0.01417 -0.0555 0.9866 0.0078
-10.000 -0.7978 0.01780 0.01331 -0.0567 0.9838 0.0080
-9.750 -0.7710 0.01715 0.01257 -0.0571 0.9781 0.0082
-9.250 -0.7127 0.01600 0.01125 -0.0585 0.9624 0.0085
-9.000 -0.6818 0.01551 0.01067 -0.0594 0.9478 0.0087
-8.750 -0.6567 0.01437 0.00936 -0.0595 0.9179 0.0091
-8.500 -0.6337 0.01395 0.00878 -0.0587 0.8806 0.0095
-8.250 -0.6111 0.01368 0.00835 -0.0577 0.8463 0.0097
-8.000 -0.5883 0.01336 0.00787 -0.0568 0.8173 0.0100
-7.750 -0.5647 0.01307 0.00745 -0.0561 0.7928 0.0104
-7.500 -0.5408 0.01275 0.00698 -0.0554 0.7699 0.0106
-7.250 -0.5166 0.01242 0.00653 -0.0548 0.7504 0.0109
-7.000 -0.4917 0.01215 0.00615 -0.0543 0.7327 0.0114
-6.750 -0.4664 0.01190 0.00580 -0.0539 0.7159 0.0117
-6.500 -0.4410 0.01165 0.00545 -0.0534 0.7006 0.0120
-6.250 -0.4155 0.01137 0.00507 -0.0530 0.6869 0.0122
-6.000 -0.3897 0.01113 0.00474 -0.0526 0.6741 0.0123
-5.750 -0.3639 0.01087 0.00440 -0.0523 0.6623 0.0125
-5.500 -0.3386 0.01050 0.00393 -0.0518 0.6513 0.0130
-5.250 -0.3127 0.01021 0.00356 -0.0515 0.6410 0.0136
-5.000 -0.2863 0.00999 0.00327 -0.0512 0.6313 0.0142
-4.750 -0.2597 0.00980 0.00303 -0.0509 0.6220 0.0148
-4.500 -0.2328 0.00963 0.00281 -0.0507 0.6138 0.0156
-4.250 -0.2059 0.00949 0.00261 -0.0505 0.6055 0.0164
-4.000 -0.1786 0.00935 0.00242 -0.0504 0.5978 0.0170
-3.750 -0.1515 0.00923 0.00224 -0.0502 0.5908 0.0180
-3.500 -0.1242 0.00908 0.00208 -0.0500 0.5837 0.0208
-3.250 -0.0974 0.00891 0.00192 -0.0498 0.5770 0.0304
-3.000 -0.0706 0.00868 0.00176 -0.0497 0.5709 0.0539
-2.750 -0.0437 0.00850 0.00164 -0.0495 0.5646 0.0747
-2.500 -0.0168 0.00832 0.00153 -0.0494 0.5587 0.1009
-2.250 0.0101 0.00812 0.00142 -0.0492 0.5526 0.1348
-2.000 0.0368 0.00792 0.00133 -0.0491 0.5471 0.1755
-1.750 0.0639 0.00774 0.00125 -0.0490 0.5414 0.2118
-1.500 0.0909 0.00759 0.00119 -0.0489 0.5357 0.2475
-1.250 0.1176 0.00738 0.00113 -0.0487 0.5306 0.2996
-1.000 0.1436 0.00707 0.00108 -0.0485 0.5250 0.3841
-0.750 0.1700 0.00689 0.00107 -0.0483 0.5196 0.4469
-0.500 0.1977 0.00682 0.00106 -0.0482 0.5148 0.4739
-0.250 0.2254 0.00678 0.00106 -0.0482 0.5093 0.4963
0.000 0.2528 0.00675 0.00106 -0.0481 0.5039 0.5204
0.250 0.2805 0.00669 0.00107 -0.0480 0.4990 0.5446
0.500 0.3080 0.00666 0.00108 -0.0479 0.4935 0.5693
0.750 0.3353 0.00663 0.00110 -0.0478 0.4884 0.5948
1.000 0.3628 0.00658 0.00113 -0.0477 0.4832 0.6226
1.250 0.3898 0.00654 0.00116 -0.0475 0.4778 0.6546
1.500 0.4167 0.00648 0.00120 -0.0473 0.4727 0.6904
1.750 0.4433 0.00642 0.00125 -0.0471 0.4671 0.7288
2.000 0.4693 0.00636 0.00130 -0.0466 0.4615 0.7717
2.250 0.4951 0.00628 0.00136 -0.0461 0.4553 0.8167
2.500 0.5201 0.00623 0.00144 -0.0454 0.4480 0.8625
2.750 0.5458 0.00620 0.00153 -0.0447 0.4406 0.9089
3.000 0.5766 0.00628 0.00163 -0.0453 0.4321 0.9443
3.250 0.6099 0.00637 0.00171 -0.0464 0.4230 0.9621
3.500 0.6418 0.00648 0.00180 -0.0474 0.4133 0.9725
3.750 0.6737 0.00662 0.00189 -0.0483 0.4027 0.9802
4.000 0.7064 0.00674 0.00198 -0.0494 0.3919 0.9850
4.250 0.7403 0.00687 0.00209 -0.0509 0.3799 0.9886
4.500 0.7721 0.00703 0.00221 -0.0518 0.3670 0.9924
4.750 0.8042 0.00722 0.00234 -0.0529 0.3500 0.9954
5.000 0.8366 0.00742 0.00249 -0.0541 0.3336 0.9981
5.250 0.8666 0.00769 0.00266 -0.0548 0.3099 1.0000
5.500 0.8885 0.00798 0.00286 -0.0538 0.2872 1.0000
5.750 0.9097 0.00833 0.00309 -0.0526 0.2603 1.0000
6.000 0.9280 0.00889 0.00343 -0.0510 0.2167 1.0000
6.250 0.9482 0.00932 0.00374 -0.0497 0.1893 1.0000
6.500 0.9669 0.00985 0.00410 -0.0482 0.1555 1.0000
6.750 0.9859 0.01037 0.00447 -0.0467 0.1266 1.0000
7.000 1.0056 0.01085 0.00483 -0.0454 0.1029 1.0000
7.250 1.0261 0.01129 0.00519 -0.0442 0.0860 1.0000
7.500 1.0469 0.01171 0.00554 -0.0431 0.0719 1.0000
7.750 1.0672 0.01216 0.00593 -0.0420 0.0574 1.0000
8.000 1.0870 0.01264 0.00634 -0.0408 0.0444 1.0000
8.250 1.1070 0.01310 0.00675 -0.0396 0.0351 1.0000
8.500 1.1266 0.01357 0.00718 -0.0384 0.0271 1.0000
8.750 1.1460 0.01404 0.00763 -0.0371 0.0211 1.0000
9.000 1.1641 0.01457 0.00813 -0.0357 0.0146 1.0000
9.250 1.1803 0.01519 0.00872 -0.0340 0.0084 1.0000
9.500 1.1978 0.01571 0.00924 -0.0325 0.0065 1.0000
9.750 1.2151 0.01619 0.00976 -0.0309 0.0055 1.0000
10.000 1.2311 0.01669 0.01029 -0.0292 0.0050 1.0000
10.250 1.2435 0.01722 0.01086 -0.0268 0.0045 1.0000
10.500 1.2551 0.01778 0.01147 -0.0243 0.0041 1.0000
10.750 1.2654 0.01843 0.01218 -0.0218 0.0039 1.0000
11.000 1.2775 0.01903 0.01283 -0.0197 0.0037 1.0000
11.250 1.2885 0.01973 0.01358 -0.0176 0.0035 1.0000
11.500 1.2989 0.02049 0.01440 -0.0156 0.0035 1.0000
11.750 1.3077 0.02140 0.01537 -0.0136 0.0033 1.0000
12.000 1.3165 0.02236 0.01639 -0.0117 0.0032 1.0000
12.250 1.3256 0.02336 0.01745 -0.0102 0.0031 1.0000
12.500 1.3324 0.02461 0.01879 -0.0086 0.0031 1.0000
12.750 1.3381 0.02604 0.02029 -0.0072 0.0029 1.0000
13.000 1.3444 0.02752 0.02185 -0.0061 0.0029 1.0000
13.250 1.3507 0.02908 0.02347 -0.0052 0.0028 1.0000
13.500 1.3533 0.03107 0.02554 -0.0043 0.0027 1.0000
13.750 1.3574 0.03301 0.02756 -0.0036 0.0026 1.0000
14.000 1.3593 0.03524 0.02988 -0.0031 0.0026 1.0000
14.250 1.3607 0.03761 0.03233 -0.0028 0.0026 1.0000
14.500 1.3596 0.04030 0.03512 -0.0026 0.0025 1.0000
14.750 1.3599 0.04291 0.03781 -0.0025 0.0025 1.0000
15.000 1.3560 0.04608 0.04109 -0.0026 0.0024 1.0000
15.250 1.3472 0.04988 0.04501 -0.0030 0.0023 1.0000
15.500 1.3455 0.05299 0.04821 -0.0034 0.0023 1.0000
15.750 1.3399 0.05670 0.05203 -0.0041 0.0023 1.0000
16.000 1.3415 0.05956 0.05498 -0.0047 0.0022 1.0000
16.250 1.3319 0.06405 0.05958 -0.0059 0.0023 1.0000
16.500 1.3310 0.06745 0.06307 -0.0068 0.0022 1.0000
16.750 1.3221 0.07211 0.06785 -0.0083 0.0022 1.0000
17.000 1.3195 0.07597 0.07179 -0.0096 0.0022 1.0000
17.250 1.3097 0.08106 0.07699 -0.0115 0.0022 1.0000
17.500 1.3055 0.08535 0.08138 -0.0132 0.0022 1.0000
17.750 1.3025 0.08954 0.08566 -0.0149 0.0021 1.0000
18.000 1.2883 0.09576 0.09201 -0.0176 0.0022 1.0000
18.250 1.2790 0.10127 0.09763 -0.0201 0.0022 1.0000
18.500 1.2646 0.10783 0.10431 -0.0232 0.0022 1.0000
18.750 1.2622 0.11233 0.10890 -0.0253 0.0021 1.0000
19.000 1.2438 0.11999 0.11669 -0.0292 0.0021 1.0000
19.250 1.2354 0.12581 0.12261 -0.0323 0.0021 1.0000
|
Polar data table (+)
Polar graphs
<< Back to E207 (12.04%) (e207-il)