E201 (11.88%) (e201-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: E201 (11.88%) (e201-il) Reynolds number: 100,000 Max Cl/Cd: 56.67 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e201-il-100000.txt Download as CSV file: xf-e201-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: E201 (11.88%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3619 0.10893 0.10390 -0.0359 1.0000 0.1124
-9.750 -0.3829 0.10669 0.10179 -0.0403 1.0000 0.1171
-9.500 -0.4125 0.10437 0.09966 -0.0455 1.0000 0.1178
-9.250 -0.3651 0.09908 0.09424 -0.0386 1.0000 0.1217
-9.000 -0.3608 0.09627 0.09147 -0.0384 1.0000 0.1258
-8.750 -0.3898 0.09397 0.08935 -0.0424 1.0000 0.1313
-8.500 -0.3999 0.09014 0.08564 -0.0429 1.0000 0.1331
-8.250 -0.3755 0.08707 0.08254 -0.0395 1.0000 0.1365
-8.000 -0.3774 0.08456 0.08010 -0.0387 1.0000 0.1403
-7.750 -0.4128 0.08278 0.07854 -0.0388 1.0000 0.1449
-7.500 -0.4875 0.08079 0.07669 -0.0434 1.0000 0.1466
-7.250 -0.4500 0.07759 0.07362 -0.0360 1.0000 0.1489
-7.000 -0.4569 0.07614 0.07225 -0.0319 1.0000 0.1508
-6.750 -0.4747 0.07487 0.07107 -0.0288 1.0000 0.1527
-6.500 -0.4946 0.07321 0.06948 -0.0270 1.0000 0.1555
-6.250 -0.4849 0.04594 0.04054 -0.0543 0.9856 0.0737
-6.000 -0.4544 0.03885 0.03218 -0.0580 0.9767 0.0630
-5.750 -0.4182 0.03442 0.02727 -0.0614 0.9708 0.0617
-5.500 -0.3845 0.03154 0.02383 -0.0633 0.9618 0.0621
-5.250 -0.3466 0.02890 0.02068 -0.0658 0.9553 0.0645
-5.000 -0.3109 0.02673 0.01832 -0.0676 0.9473 0.0667
-4.750 -0.2716 0.02502 0.01642 -0.0697 0.9407 0.0704
-4.500 -0.2345 0.02368 0.01483 -0.0711 0.9328 0.0763
-4.250 -0.1978 0.02215 0.01345 -0.0731 0.9262 0.0915
-4.000 -0.1651 0.02045 0.01209 -0.0742 0.9182 0.1375
-3.750 -0.1316 0.01894 0.01126 -0.0761 0.9113 0.2600
-3.500 -0.0998 0.01815 0.01113 -0.0772 0.9034 0.4035
-3.250 -0.0670 0.01788 0.01106 -0.0778 0.8961 0.4980
-3.000 -0.0350 0.01770 0.01094 -0.0781 0.8885 0.5659
-2.750 -0.0057 0.01758 0.01089 -0.0777 0.8808 0.6186
-2.500 0.0247 0.01742 0.01078 -0.0775 0.8735 0.6666
-2.250 0.0518 0.01732 0.01070 -0.0766 0.8658 0.7088
-2.000 0.0804 0.01717 0.01058 -0.0759 0.8586 0.7508
-1.750 0.1051 0.01711 0.01054 -0.0745 0.8507 0.7922
-1.500 0.1324 0.01699 0.01044 -0.0733 0.8437 0.8352
-1.250 0.1626 0.01695 0.01040 -0.0727 0.8369 0.8820
-1.000 0.2131 0.01690 0.01026 -0.0763 0.8307 0.9287
-0.750 0.2893 0.01664 0.00980 -0.0852 0.8272 0.9638
-0.500 0.3682 0.01641 0.00940 -0.0956 0.8215 0.9932
-0.250 0.3938 0.01636 0.00921 -0.0966 0.8130 1.0000
0.000 0.4021 0.01668 0.00942 -0.0941 0.8029 1.0000
0.250 0.4262 0.01675 0.00935 -0.0936 0.7965 1.0000
0.500 0.4403 0.01721 0.00973 -0.0917 0.7867 1.0000
0.750 0.4685 0.01729 0.00968 -0.0916 0.7811 1.0000
1.000 0.4843 0.01781 0.01016 -0.0900 0.7715 1.0000
1.250 0.5138 0.01790 0.01015 -0.0900 0.7662 1.0000
1.500 0.5304 0.01849 0.01072 -0.0886 0.7567 1.0000
1.750 0.5601 0.01859 0.01075 -0.0886 0.7515 1.0000
2.000 0.5773 0.01922 0.01139 -0.0873 0.7422 1.0000
2.250 0.6071 0.01934 0.01146 -0.0873 0.7369 1.0000
2.500 0.6245 0.02000 0.01215 -0.0860 0.7277 1.0000
2.750 0.6544 0.02012 0.01224 -0.0861 0.7223 1.0000
3.000 0.6722 0.02081 0.01297 -0.0848 0.7130 1.0000
3.250 0.7025 0.02089 0.01306 -0.0848 0.7075 1.0000
3.500 0.7204 0.02158 0.01381 -0.0836 0.6979 1.0000
3.750 0.7520 0.02157 0.01379 -0.0837 0.6923 1.0000
4.000 0.7697 0.02225 0.01455 -0.0823 0.6821 1.0000
4.250 0.8020 0.02217 0.01449 -0.0824 0.6762 1.0000
4.500 0.8209 0.02274 0.01516 -0.0811 0.6657 1.0000
4.750 0.8445 0.02307 0.01556 -0.0803 0.6567 1.0000
5.000 0.8753 0.02292 0.01546 -0.0800 0.6485 1.0000
5.250 0.8965 0.02326 0.01591 -0.0788 0.6373 1.0000
5.500 0.9227 0.02329 0.01602 -0.0780 0.6271 1.0000
5.750 0.9557 0.02288 0.01563 -0.0778 0.6177 1.0000
6.000 0.9782 0.02298 0.01587 -0.0765 0.6050 1.0000
6.250 1.0028 0.02291 0.01590 -0.0753 0.5921 1.0000
6.500 1.0286 0.02269 0.01578 -0.0742 0.5785 1.0000
6.750 1.0546 0.02238 0.01556 -0.0731 0.5638 1.0000
7.000 1.0808 0.02199 0.01528 -0.0719 0.5479 1.0000
7.250 1.1071 0.02151 0.01486 -0.0706 0.5304 1.0000
7.500 1.1277 0.02124 0.01472 -0.0687 0.5092 1.0000
7.750 1.1497 0.02083 0.01436 -0.0668 0.4854 1.0000
8.000 1.1660 0.02069 0.01433 -0.0642 0.4562 1.0000
8.250 1.1781 0.02079 0.01451 -0.0611 0.4180 1.0000
8.500 1.1848 0.02118 0.01473 -0.0573 0.3652 1.0000
8.750 1.1831 0.02225 0.01538 -0.0527 0.3003 1.0000
9.000 1.1752 0.02385 0.01652 -0.0477 0.2428 1.0000
9.250 1.1655 0.02561 0.01792 -0.0428 0.1992 1.0000
9.500 1.1581 0.02752 0.01958 -0.0387 0.1637 1.0000
9.750 1.1500 0.02971 0.02154 -0.0351 0.1332 1.0000
10.000 1.1412 0.03221 0.02385 -0.0319 0.1064 1.0000
10.250 1.1327 0.03499 0.02642 -0.0291 0.0854 1.0000
10.500 1.1287 0.03772 0.02904 -0.0267 0.0700 1.0000
10.750 1.1325 0.04012 0.03136 -0.0246 0.0610 1.0000
11.000 1.1409 0.04224 0.03337 -0.0232 0.0543 1.0000
11.250 1.1576 0.04412 0.03537 -0.0218 0.0496 1.0000
11.500 1.1750 0.04605 0.03734 -0.0207 0.0457 1.0000
11.750 1.2198 0.04904 0.04027 -0.0209 0.0427 1.0000
12.000 1.2354 0.05176 0.04337 -0.0198 0.0417 1.0000
12.250 1.2459 0.05495 0.04691 -0.0186 0.0411 1.0000
12.500 1.2487 0.05837 0.05068 -0.0172 0.0408 1.0000
12.750 1.2453 0.06188 0.05452 -0.0158 0.0405 1.0000
13.000 1.2375 0.06560 0.05855 -0.0146 0.0404 1.0000
13.250 1.2262 0.06960 0.06285 -0.0138 0.0403 1.0000
13.500 1.2109 0.07392 0.06746 -0.0135 0.0401 1.0000
13.750 1.1944 0.07871 0.07252 -0.0138 0.0403 1.0000
14.000 1.1762 0.08389 0.07795 -0.0147 0.0405 1.0000
14.250 1.1557 0.08959 0.08389 -0.0163 0.0407 1.0000
14.500 1.1341 0.09581 0.09033 -0.0186 0.0411 1.0000
14.750 1.1126 0.10247 0.09717 -0.0215 0.0415 1.0000
15.000 1.0900 0.10978 0.10465 -0.0252 0.0419 1.0000
15.250 1.0701 0.11742 0.11242 -0.0291 0.0424 1.0000
15.500 0.9556 0.15174 0.14708 -0.0539 0.0496 1.0000
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Polar data table (+)
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