E207 (12.04%) (e207-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: E207 (12.04%) (e207-il) Reynolds number: 200,000 Max Cl/Cd: 72.11 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e207-il-200000-n5.txt Download as CSV file: xf-e207-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.5099 0.08119 0.07765 -0.0386 1.0000 0.0170
-10.500 -0.5423 0.06841 0.06487 -0.0465 1.0000 0.0167
-10.250 -0.5721 0.05786 0.05423 -0.0558 1.0000 0.0164
-10.000 -0.5977 0.05181 0.04803 -0.0605 1.0000 0.0163
-9.750 -0.6223 0.04827 0.04436 -0.0596 1.0000 0.0162
-9.500 -0.6426 0.04485 0.04073 -0.0572 1.0000 0.0162
-9.250 -0.6569 0.04134 0.03693 -0.0545 1.0000 0.0163
-9.000 -0.6647 0.03811 0.03336 -0.0517 1.0000 0.0164
-8.750 -0.6666 0.03528 0.03018 -0.0489 1.0000 0.0166
-8.500 -0.6641 0.03284 0.02738 -0.0462 1.0000 0.0168
-8.250 -0.6552 0.03072 0.02490 -0.0442 0.9992 0.0171
-8.000 -0.6285 0.02769 0.02148 -0.0460 0.9924 0.0177
-7.750 -0.5978 0.02612 0.01981 -0.0479 0.9854 0.0188
-7.500 -0.5673 0.02469 0.01815 -0.0493 0.9776 0.0198
-7.250 -0.5353 0.02301 0.01620 -0.0508 0.9702 0.0203
-7.000 -0.5066 0.02157 0.01456 -0.0514 0.9587 0.0210
-6.750 -0.4771 0.02030 0.01311 -0.0520 0.9465 0.0217
-6.500 -0.4463 0.01918 0.01184 -0.0529 0.9333 0.0224
-6.250 -0.4139 0.01826 0.01074 -0.0540 0.9187 0.0232
-6.000 -0.3827 0.01711 0.00953 -0.0551 0.9025 0.0249
-5.750 -0.3505 0.01635 0.00867 -0.0561 0.8846 0.0265
-5.500 -0.3210 0.01567 0.00786 -0.0565 0.8639 0.0278
-5.250 -0.2929 0.01510 0.00712 -0.0564 0.8430 0.0294
-5.000 -0.2665 0.01463 0.00647 -0.0561 0.8228 0.0312
-4.750 -0.2415 0.01414 0.00588 -0.0555 0.8031 0.0352
-4.500 -0.2163 0.01375 0.00539 -0.0549 0.7852 0.0428
-4.250 -0.1918 0.01332 0.00495 -0.0542 0.7686 0.0635
-4.000 -0.1674 0.01292 0.00458 -0.0536 0.7531 0.0933
-3.750 -0.1426 0.01259 0.00428 -0.0531 0.7387 0.1256
-3.500 -0.1182 0.01223 0.00402 -0.0526 0.7254 0.1711
-3.250 -0.0938 0.01185 0.00378 -0.0521 0.7129 0.2257
-3.000 -0.0708 0.01135 0.00359 -0.0514 0.7014 0.3157
-2.750 -0.0470 0.01102 0.00348 -0.0507 0.6908 0.3957
-2.500 -0.0220 0.01085 0.00338 -0.0501 0.6805 0.4487
-2.250 0.0032 0.01071 0.00330 -0.0495 0.6706 0.4944
-2.000 0.0285 0.01059 0.00322 -0.0489 0.6616 0.5355
-1.750 0.0542 0.01050 0.00315 -0.0483 0.6527 0.5696
-1.500 0.0800 0.01041 0.00310 -0.0478 0.6443 0.6021
-1.250 0.1055 0.01033 0.00304 -0.0472 0.6365 0.6349
-1.000 0.1311 0.01025 0.00302 -0.0465 0.6286 0.6690
-0.750 0.1566 0.01018 0.00300 -0.0458 0.6215 0.7053
-0.500 0.1821 0.01010 0.00301 -0.0451 0.6140 0.7437
-0.250 0.2079 0.01004 0.00302 -0.0443 0.6073 0.7858
0.000 0.2359 0.01000 0.00307 -0.0440 0.6002 0.8313
0.250 0.2696 0.01003 0.00312 -0.0448 0.5935 0.8751
0.500 0.3087 0.01010 0.00317 -0.0469 0.5865 0.9108
0.750 0.3481 0.01019 0.00320 -0.0492 0.5796 0.9364
1.000 0.3844 0.01028 0.00325 -0.0509 0.5731 0.9567
1.250 0.4211 0.01037 0.00328 -0.0528 0.5662 0.9718
1.500 0.4590 0.01047 0.00331 -0.0550 0.5600 0.9838
1.750 0.4982 0.01053 0.00335 -0.0575 0.5530 0.9933
2.000 0.5343 0.01062 0.00337 -0.0594 0.5472 1.0000
2.250 0.5578 0.01071 0.00347 -0.0587 0.5407 1.0000
2.500 0.5814 0.01083 0.00355 -0.0579 0.5350 1.0000
2.750 0.6052 0.01095 0.00366 -0.0571 0.5288 1.0000
3.000 0.6291 0.01107 0.00377 -0.0564 0.5227 1.0000
3.250 0.6531 0.01121 0.00390 -0.0557 0.5169 1.0000
3.500 0.6771 0.01133 0.00405 -0.0550 0.5100 1.0000
3.750 0.7011 0.01148 0.00417 -0.0542 0.5037 1.0000
4.000 0.7251 0.01161 0.00433 -0.0535 0.4955 1.0000
4.250 0.7489 0.01176 0.00449 -0.0527 0.4882 1.0000
4.500 0.7727 0.01190 0.00466 -0.0519 0.4794 1.0000
4.750 0.7965 0.01205 0.00483 -0.0511 0.4705 1.0000
5.000 0.8200 0.01221 0.00499 -0.0503 0.4613 1.0000
5.250 0.8438 0.01236 0.00521 -0.0495 0.4509 1.0000
5.500 0.8674 0.01253 0.00541 -0.0487 0.4404 1.0000
5.750 0.8907 0.01271 0.00562 -0.0479 0.4295 1.0000
6.000 0.9138 0.01291 0.00584 -0.0470 0.4172 1.0000
6.250 0.9367 0.01312 0.00609 -0.0461 0.4033 1.0000
6.500 0.9593 0.01335 0.00635 -0.0452 0.3875 1.0000
6.750 0.9814 0.01361 0.00664 -0.0442 0.3693 1.0000
7.000 1.0024 0.01393 0.00694 -0.0431 0.3479 1.0000
7.250 1.0226 0.01431 0.00729 -0.0419 0.3221 1.0000
7.500 1.0409 0.01482 0.00772 -0.0404 0.2911 1.0000
7.750 1.0572 0.01546 0.00823 -0.0387 0.2543 1.0000
8.000 1.0717 0.01624 0.00885 -0.0367 0.2194 1.0000
8.250 1.0860 0.01705 0.00954 -0.0349 0.1886 1.0000
8.500 1.0996 0.01788 0.01028 -0.0329 0.1625 1.0000
9.000 1.1234 0.01967 0.01191 -0.0287 0.1154 1.0000
9.250 1.1327 0.02064 0.01279 -0.0262 0.0955 1.0000
9.500 1.1395 0.02160 0.01366 -0.0234 0.0778 1.0000
9.750 1.1449 0.02261 0.01461 -0.0205 0.0635 1.0000
10.000 1.1514 0.02363 0.01560 -0.0180 0.0531 1.0000
10.250 1.1581 0.02470 0.01669 -0.0157 0.0451 1.0000
10.500 1.1635 0.02592 0.01793 -0.0135 0.0391 1.0000
10.750 1.1696 0.02717 0.01924 -0.0116 0.0327 1.0000
11.000 1.1735 0.02868 0.02080 -0.0098 0.0274 1.0000
11.250 1.1750 0.03050 0.02267 -0.0082 0.0225 1.0000
11.500 1.1783 0.03230 0.02456 -0.0070 0.0194 1.0000
11.750 1.1777 0.03456 0.02683 -0.0058 0.0163 1.0000
12.000 1.1800 0.03668 0.02909 -0.0050 0.0148 1.0000
12.250 1.1822 0.03889 0.03141 -0.0045 0.0138 1.0000
12.500 1.1823 0.04141 0.03400 -0.0041 0.0127 1.0000
12.750 1.1808 0.04419 0.03687 -0.0038 0.0117 1.0000
13.000 1.1806 0.04692 0.03975 -0.0037 0.0113 1.0000
13.250 1.1796 0.04980 0.04275 -0.0037 0.0110 1.0000
13.500 1.1778 0.05286 0.04594 -0.0039 0.0104 1.0000
13.750 1.1757 0.05602 0.04923 -0.0043 0.0102 1.0000
14.000 1.1732 0.05931 0.05264 -0.0048 0.0099 1.0000
14.250 1.1699 0.06282 0.05628 -0.0054 0.0097 1.0000
14.500 1.1662 0.06650 0.06009 -0.0063 0.0094 1.0000
14.750 1.1625 0.07028 0.06399 -0.0072 0.0093 1.0000
15.000 1.1578 0.07435 0.06818 -0.0084 0.0091 1.0000
15.250 1.1520 0.07866 0.07259 -0.0098 0.0089 1.0000
15.500 1.1464 0.08304 0.07708 -0.0112 0.0088 1.0000
15.750 1.1409 0.08753 0.08168 -0.0127 0.0087 1.0000
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Polar data table (+)
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