E207 (12.04%) (e207-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: E207 (12.04%) (e207-il) Reynolds number: 50,000 Max Cl/Cd: 32.88 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e207-il-50000-n5.txt Download as CSV file: xf-e207-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4523 0.09475 0.08776 -0.0376 1.0000 0.0511
-9.750 -0.4575 0.08944 0.08252 -0.0404 1.0000 0.0511
-9.500 -0.4649 0.08357 0.07673 -0.0438 1.0000 0.0509
-9.250 -0.4751 0.07780 0.07101 -0.0475 1.0000 0.0506
-9.000 -0.4911 0.07262 0.06589 -0.0506 1.0000 0.0503
-8.750 -0.5085 0.06851 0.06179 -0.0512 1.0000 0.0500
-8.500 -0.5238 0.06433 0.05754 -0.0515 1.0000 0.0499
-8.250 -0.5360 0.06040 0.05348 -0.0510 1.0000 0.0498
-8.000 -0.5455 0.05656 0.04944 -0.0500 1.0000 0.0500
-7.750 -0.5515 0.05287 0.04548 -0.0485 1.0000 0.0503
-7.500 -0.5526 0.04944 0.04173 -0.0467 1.0000 0.0505
-7.250 -0.5505 0.04622 0.03816 -0.0448 1.0000 0.0507
-7.000 -0.5456 0.04321 0.03475 -0.0428 1.0000 0.0511
-6.750 -0.5379 0.04049 0.03161 -0.0407 1.0000 0.0516
-6.500 -0.5279 0.03806 0.02894 -0.0387 1.0000 0.0524
-6.250 -0.5164 0.03609 0.02681 -0.0368 1.0000 0.0536
-6.000 -0.5045 0.03448 0.02502 -0.0349 1.0000 0.0553
-5.750 -0.4925 0.03317 0.02354 -0.0329 1.0000 0.0584
-5.500 -0.4687 0.03158 0.02158 -0.0329 0.9956 0.0627
-5.250 -0.4302 0.02968 0.01951 -0.0354 0.9849 0.0673
-5.000 -0.3926 0.02814 0.01779 -0.0375 0.9732 0.0736
-4.750 -0.3565 0.02673 0.01626 -0.0394 0.9608 0.0842
-4.500 -0.3209 0.02545 0.01492 -0.0413 0.9479 0.1057
-4.250 -0.2861 0.02409 0.01378 -0.0434 0.9352 0.1495
-4.000 -0.2509 0.02268 0.01283 -0.0459 0.9231 0.2339
-3.750 -0.2181 0.02154 0.01224 -0.0474 0.9113 0.3430
-3.500 -0.1867 0.02093 0.01195 -0.0479 0.8992 0.4553
-3.250 -0.1579 0.02059 0.01174 -0.0475 0.8860 0.5393
-3.000 -0.1293 0.02033 0.01155 -0.0468 0.8731 0.6057
-2.750 -0.1006 0.02012 0.01135 -0.0460 0.8608 0.6639
-2.500 -0.0708 0.01996 0.01117 -0.0453 0.8491 0.7178
-2.250 -0.0370 0.01982 0.01099 -0.0451 0.8389 0.7691
-2.000 -0.0001 0.01976 0.01084 -0.0456 0.8278 0.8176
-1.750 0.0447 0.01976 0.01066 -0.0479 0.8170 0.8630
-1.500 0.0983 0.01975 0.01041 -0.0521 0.8073 0.9024
-1.250 0.1542 0.01970 0.01007 -0.0572 0.7974 0.9359
-1.000 0.2082 0.01964 0.00977 -0.0625 0.7861 0.9656
-0.750 0.2627 0.01950 0.00939 -0.0682 0.7752 0.9922
-0.500 0.2919 0.01948 0.00917 -0.0692 0.7642 1.0000
-0.250 0.3103 0.01958 0.00910 -0.0680 0.7534 1.0000
0.000 0.3280 0.01977 0.00915 -0.0667 0.7421 1.0000
0.250 0.3476 0.01998 0.00922 -0.0656 0.7320 1.0000
0.500 0.3708 0.02014 0.00923 -0.0648 0.7233 1.0000
0.750 0.3905 0.02045 0.00946 -0.0638 0.7129 1.0000
1.000 0.4123 0.02073 0.00963 -0.0629 0.7039 1.0000
1.250 0.4354 0.02099 0.00979 -0.0621 0.6955 1.0000
1.500 0.4561 0.02136 0.01011 -0.0611 0.6861 1.0000
1.750 0.4809 0.02160 0.01027 -0.0605 0.6789 1.0000
2.000 0.5009 0.02203 0.01069 -0.0594 0.6694 1.0000
2.250 0.5240 0.02237 0.01099 -0.0587 0.6617 1.0000
2.500 0.5461 0.02277 0.01139 -0.0578 0.6533 1.0000
2.750 0.5681 0.02320 0.01182 -0.0569 0.6453 1.0000
3.000 0.5917 0.02356 0.01217 -0.0562 0.6376 1.0000
3.250 0.6125 0.02408 0.01273 -0.0552 0.6292 1.0000
3.500 0.6373 0.02441 0.01309 -0.0546 0.6221 1.0000
3.750 0.6569 0.02501 0.01376 -0.0536 0.6133 1.0000
4.000 0.6829 0.02531 0.01407 -0.0530 0.6067 1.0000
4.250 0.7012 0.02599 0.01486 -0.0519 0.5973 1.0000
4.500 0.7266 0.02633 0.01527 -0.0513 0.5904 1.0000
4.750 0.7459 0.02697 0.01602 -0.0501 0.5809 1.0000
5.000 0.7673 0.02750 0.01664 -0.0492 0.5723 1.0000
5.250 0.7917 0.02784 0.01708 -0.0484 0.5640 1.0000
5.500 0.8099 0.02851 0.01792 -0.0471 0.5537 1.0000
5.750 0.8332 0.02888 0.01839 -0.0462 0.5447 1.0000
6.000 0.8565 0.02919 0.01883 -0.0452 0.5348 1.0000
6.250 0.8745 0.02978 0.01958 -0.0438 0.5233 1.0000
6.500 0.8948 0.03019 0.02014 -0.0425 0.5118 1.0000
6.750 0.9171 0.03042 0.02054 -0.0412 0.5002 1.0000
7.000 0.9401 0.03052 0.02079 -0.0400 0.4878 1.0000
7.250 0.9616 0.03065 0.02105 -0.0385 0.4744 1.0000
7.500 0.9802 0.03087 0.02145 -0.0368 0.4594 1.0000
7.750 0.9968 0.03116 0.02192 -0.0348 0.4432 1.0000
8.000 1.0125 0.03141 0.02239 -0.0328 0.4256 1.0000
8.250 1.0295 0.03147 0.02260 -0.0307 0.4067 1.0000
8.500 1.0430 0.03174 0.02300 -0.0283 0.3860 1.0000
8.750 1.0544 0.03207 0.02344 -0.0257 0.3629 1.0000
9.000 1.0620 0.03268 0.02414 -0.0229 0.3375 1.0000
9.250 1.0680 0.03340 0.02487 -0.0201 0.3104 1.0000
9.500 1.0696 0.03434 0.02576 -0.0168 0.2835 1.0000
9.750 1.0691 0.03564 0.02700 -0.0138 0.2571 1.0000
10.000 1.0668 0.03730 0.02851 -0.0112 0.2326 1.0000
10.250 1.0634 0.03936 0.03049 -0.0091 0.2104 1.0000
10.500 1.0594 0.04167 0.03266 -0.0074 0.1913 1.0000
10.750 1.0558 0.04422 0.03518 -0.0062 0.1732 1.0000
11.000 1.0529 0.04688 0.03780 -0.0052 0.1575 1.0000
11.250 1.0503 0.04966 0.04055 -0.0044 0.1434 1.0000
11.500 1.0485 0.05247 0.04334 -0.0039 0.1308 1.0000
11.750 1.0473 0.05534 0.04621 -0.0034 0.1194 1.0000
12.000 1.0461 0.05824 0.04907 -0.0030 0.1093 1.0000
12.250 1.0455 0.06124 0.05213 -0.0029 0.0996 1.0000
12.500 1.0450 0.06438 0.05538 -0.0028 0.0906 1.0000
12.750 1.0435 0.06758 0.05857 -0.0029 0.0828 1.0000
13.000 1.0423 0.07095 0.06212 -0.0031 0.0755 1.0000
13.250 1.0401 0.07450 0.06576 -0.0035 0.0692 1.0000
13.500 1.0375 0.07820 0.06958 -0.0041 0.0636 1.0000
13.750 1.0364 0.08176 0.07317 -0.0046 0.0590 1.0000
14.000 1.0313 0.08628 0.07799 -0.0058 0.0550 1.0000
14.250 1.0280 0.09031 0.08210 -0.0070 0.0515 1.0000
14.500 1.0263 0.09422 0.08602 -0.0079 0.0486 1.0000
14.750 1.0158 0.10019 0.09233 -0.0103 0.0470 1.0000
15.000 1.0042 0.10659 0.09900 -0.0131 0.0458 1.0000
15.250 0.9896 0.11379 0.10644 -0.0167 0.0448 1.0000
15.500 0.9718 0.12219 0.11506 -0.0212 0.0446 1.0000
15.750 0.9483 0.13274 0.12580 -0.0271 0.0454 1.0000
16.000 0.9222 0.14504 0.13818 -0.0341 0.0464 1.0000
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Polar data table (+)
Polar graphs
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