E207 (12.04%) (e207-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: E207 (12.04%) (e207-il) Reynolds number: 50,000 Max Cl/Cd: 30.89 at α=9.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e207-il-50000.txt Download as CSV file: xf-e207-il-50000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4077 0.11327 0.10645 -0.0169 1.0000 0.2698
-9.250 -0.3787 0.10748 0.10062 -0.0157 1.0000 0.2793
-8.750 -0.3982 0.10369 0.09705 -0.0166 1.0000 0.2994
-8.500 -0.3691 0.09822 0.09154 -0.0155 1.0000 0.3093
-8.250 -0.3648 0.09508 0.08846 -0.0151 1.0000 0.3207
-8.000 -0.3629 0.09222 0.08567 -0.0146 1.0000 0.3339
-7.500 -0.3720 0.08739 0.08104 -0.0131 1.0000 0.3596
-7.250 -0.4655 0.07142 0.06538 -0.0359 1.0000 0.1743
-7.000 -0.4934 0.06345 0.05727 -0.0401 1.0000 0.1479
-6.750 -0.5095 0.05755 0.05108 -0.0408 1.0000 0.1355
-6.500 -0.5114 0.05326 0.04662 -0.0396 1.0000 0.1299
-6.250 -0.5187 0.04866 0.04133 -0.0381 1.0000 0.1229
-6.000 -0.5133 0.04551 0.03799 -0.0361 1.0000 0.1213
-5.750 -0.5078 0.04259 0.03471 -0.0340 1.0000 0.1206
-5.500 -0.5011 0.04004 0.03170 -0.0320 1.0000 0.1218
-5.250 -0.4917 0.03779 0.02895 -0.0300 1.0000 0.1234
-5.000 -0.4796 0.03556 0.02651 -0.0284 1.0000 0.1261
-4.750 -0.4652 0.03373 0.02452 -0.0269 1.0000 0.1293
-4.500 -0.4492 0.03203 0.02251 -0.0254 1.0000 0.1337
-4.250 -0.4320 0.03051 0.02069 -0.0242 1.0000 0.1411
-4.000 -0.4148 0.02933 0.01937 -0.0229 1.0000 0.1541
-3.750 -0.3971 0.02804 0.01813 -0.0217 1.0000 0.1712
-3.500 -0.3801 0.02684 0.01709 -0.0204 1.0000 0.2051
-3.250 -0.3630 0.02557 0.01619 -0.0193 1.0000 0.2710
-3.000 -0.3489 0.02431 0.01579 -0.0174 1.0000 0.3880
-2.750 -0.3285 0.02361 0.01619 -0.0150 0.9939 0.5820
-2.500 -0.3038 0.02367 0.01676 -0.0121 0.9827 0.7279
-2.250 -0.2718 0.02400 0.01733 -0.0097 0.9720 0.8540
-2.000 -0.0701 0.02565 0.01795 -0.0396 0.9710 1.0000
-1.750 -0.0493 0.02531 0.01734 -0.0429 0.9545 1.0000
-1.500 -0.0240 0.02535 0.01704 -0.0456 0.9398 1.0000
-1.250 0.0114 0.02566 0.01701 -0.0491 0.9274 1.0000
-1.000 0.0394 0.02604 0.01711 -0.0508 0.9148 1.0000
-0.750 0.0665 0.02651 0.01730 -0.0521 0.9025 1.0000
-0.500 0.0940 0.02704 0.01761 -0.0532 0.8912 1.0000
-0.250 0.1280 0.02758 0.01795 -0.0553 0.8807 1.0000
0.000 0.1610 0.02815 0.01832 -0.0571 0.8705 1.0000
0.250 0.1799 0.02882 0.01885 -0.0566 0.8593 1.0000
0.500 0.2064 0.02950 0.01938 -0.0573 0.8493 1.0000
0.750 0.2441 0.03009 0.01985 -0.0597 0.8403 1.0000
1.000 0.2554 0.03097 0.02062 -0.0579 0.8296 1.0000
1.250 0.2801 0.03177 0.02133 -0.0583 0.8206 1.0000
1.500 0.3103 0.03250 0.02198 -0.0594 0.8116 1.0000
1.750 0.3196 0.03356 0.02297 -0.0575 0.8017 1.0000
2.000 0.3545 0.03430 0.02367 -0.0592 0.7937 1.0000
2.250 0.3642 0.03543 0.02474 -0.0575 0.7838 1.0000
2.500 0.3799 0.03656 0.02583 -0.0566 0.7752 1.0000
2.750 0.4110 0.03741 0.02669 -0.0577 0.7667 1.0000
3.000 0.4133 0.03886 0.02810 -0.0553 0.7576 1.0000
3.250 0.4473 0.03974 0.02899 -0.0567 0.7494 1.0000
3.500 0.4501 0.04127 0.03050 -0.0545 0.7401 1.0000
3.750 0.4674 0.04257 0.03182 -0.0540 0.7315 1.0000
4.000 0.4939 0.04365 0.03295 -0.0544 0.7224 1.0000
4.250 0.4950 0.04541 0.03470 -0.0524 0.7134 1.0000
4.500 0.5229 0.04654 0.03589 -0.0529 0.7039 1.0000
4.750 0.5352 0.04806 0.03745 -0.0520 0.6941 1.0000
5.000 0.5428 0.04977 0.03919 -0.0507 0.6841 1.0000
5.250 0.5673 0.05104 0.04056 -0.0508 0.6735 1.0000
5.500 0.5989 0.05204 0.04167 -0.0512 0.6620 1.0000
5.750 0.5968 0.05413 0.04379 -0.0493 0.6506 1.0000
6.000 0.6081 0.05585 0.04558 -0.0484 0.6385 1.0000
6.250 0.6251 0.05737 0.04721 -0.0478 0.6256 1.0000
6.500 0.6438 0.05880 0.04876 -0.0471 0.6118 1.0000
6.750 0.6622 0.06023 0.05029 -0.0464 0.5974 1.0000
7.000 0.6795 0.06166 0.05184 -0.0456 0.5822 1.0000
7.250 0.6967 0.06308 0.05341 -0.0446 0.5663 1.0000
7.500 0.7174 0.06420 0.05468 -0.0436 0.5492 1.0000
7.750 0.7531 0.06420 0.05490 -0.0426 0.5311 1.0000
8.000 0.7849 0.06422 0.05513 -0.0412 0.5129 1.0000
8.250 0.7836 0.06664 0.05763 -0.0397 0.4946 1.0000
8.500 0.8125 0.06645 0.05770 -0.0379 0.4746 1.0000
8.750 0.8614 0.06381 0.05538 -0.0350 0.4532 1.0000
9.000 1.0655 0.04284 0.03535 -0.0307 0.4087 1.0000
9.250 1.1152 0.03829 0.03081 -0.0278 0.3641 1.0000
9.500 1.1364 0.03691 0.02920 -0.0242 0.3203 1.0000
9.750 1.1472 0.03714 0.02909 -0.0206 0.2799 1.0000
10.000 1.1521 0.03845 0.03011 -0.0171 0.2456 1.0000
10.250 1.1635 0.04023 0.03143 -0.0147 0.2130 1.0000
10.500 1.1654 0.04262 0.03390 -0.0118 0.1901 1.0000
10.750 1.1738 0.04512 0.03623 -0.0096 0.1675 1.0000
11.000 1.1786 0.04777 0.03891 -0.0073 0.1498 1.0000
11.250 1.1845 0.05050 0.04164 -0.0052 0.1346 1.0000
11.750 1.1893 0.05674 0.04807 -0.0012 0.1137 1.0000
12.000 1.2038 0.06025 0.05151 -0.0005 0.1033 1.0000
12.250 1.1846 0.06362 0.05529 0.0024 0.1018 1.0000
12.500 1.1655 0.06748 0.05949 0.0042 0.1005 1.0000
12.750 1.1453 0.07185 0.06417 0.0050 0.0999 1.0000
13.000 1.1214 0.07686 0.06944 0.0048 0.0997 1.0000
13.250 1.0977 0.08249 0.07530 0.0036 0.1006 1.0000
13.500 1.0698 0.08902 0.08202 0.0013 0.1014 1.0000
13.750 1.0438 0.09618 0.08931 -0.0017 0.1025 1.0000
14.000 1.0204 0.10381 0.09704 -0.0051 0.1035 1.0000
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Polar data table (+)
Polar graphs
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