E201 (11.88%) (e201-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: E201 (11.88%) (e201-il) Reynolds number: 500,000 Max Cl/Cd: 111.97 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e201-il-500000.txt Download as CSV file: xf-e201-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3968 0.08782 0.08560 -0.0438 1.0000 0.0270
-9.500 -0.3982 0.08438 0.08219 -0.0449 1.0000 0.0279
-7.750 -0.4629 0.02489 0.02028 -0.0828 0.9692 0.0189
-7.500 -0.4337 0.02326 0.01841 -0.0838 0.9615 0.0187
-7.250 -0.4068 0.02059 0.01547 -0.0846 0.9530 0.0184
-7.000 -0.3765 0.01893 0.01357 -0.0855 0.9438 0.0185
-6.750 -0.3482 0.01751 0.01195 -0.0859 0.9309 0.0186
-6.500 -0.3210 0.01565 0.00989 -0.0861 0.9161 0.0189
-6.250 -0.2956 0.01420 0.00829 -0.0859 0.8987 0.0196
-6.000 -0.2706 0.01340 0.00737 -0.0854 0.8794 0.0202
-5.750 -0.2461 0.01275 0.00659 -0.0848 0.8608 0.0207
-5.500 -0.2217 0.01221 0.00592 -0.0841 0.8433 0.0213
-5.250 -0.1971 0.01176 0.00532 -0.0834 0.8271 0.0222
-5.000 -0.1720 0.01136 0.00480 -0.0828 0.8122 0.0231
-4.750 -0.1465 0.01104 0.00434 -0.0824 0.7985 0.0241
-4.500 -0.1213 0.01058 0.00378 -0.0818 0.7857 0.0265
-4.250 -0.0951 0.01032 0.00344 -0.0815 0.7741 0.0305
-4.000 -0.0700 0.00980 0.00302 -0.0810 0.7637 0.0613
-3.750 -0.0447 0.00936 0.00275 -0.0807 0.7533 0.1175
-3.500 -0.0187 0.00904 0.00257 -0.0805 0.7437 0.1644
-3.250 0.0073 0.00877 0.00240 -0.0803 0.7352 0.2168
-3.000 0.0332 0.00842 0.00227 -0.0801 0.7264 0.2847
-2.750 0.0590 0.00812 0.00218 -0.0799 0.7186 0.3607
-2.500 0.0854 0.00794 0.00213 -0.0797 0.7107 0.4220
-2.250 0.1123 0.00784 0.00209 -0.0795 0.7037 0.4652
-2.000 0.1394 0.00776 0.00206 -0.0794 0.6963 0.4979
-1.750 0.1665 0.00771 0.00203 -0.0792 0.6898 0.5300
-1.500 0.1937 0.00763 0.00201 -0.0790 0.6829 0.5601
-1.250 0.2209 0.00762 0.00199 -0.0789 0.6769 0.5852
-1.000 0.2482 0.00755 0.00198 -0.0787 0.6703 0.6118
-0.750 0.2752 0.00751 0.00198 -0.0785 0.6644 0.6402
-0.500 0.3022 0.00747 0.00199 -0.0783 0.6586 0.6710
-0.250 0.3288 0.00739 0.00201 -0.0779 0.6524 0.7047
0.000 0.3550 0.00736 0.00203 -0.0775 0.6472 0.7435
0.250 0.3806 0.00725 0.00208 -0.0769 0.6414 0.7875
0.500 0.4054 0.00717 0.00213 -0.0760 0.6358 0.8370
0.750 0.4296 0.00712 0.00219 -0.0749 0.6307 0.8915
1.000 0.4614 0.00710 0.00224 -0.0754 0.6249 0.9434
1.250 0.5038 0.00715 0.00226 -0.0785 0.6193 0.9752
1.500 0.5481 0.00721 0.00229 -0.0821 0.6136 0.9923
1.750 0.5850 0.00726 0.00231 -0.0842 0.6077 1.0000
2.250 0.6342 0.00743 0.00242 -0.0829 0.5963 1.0000
2.500 0.6590 0.00752 0.00247 -0.0824 0.5901 1.0000
2.750 0.6842 0.00760 0.00254 -0.0818 0.5836 1.0000
3.000 0.7095 0.00768 0.00262 -0.0813 0.5767 1.0000
3.250 0.7351 0.00778 0.00270 -0.0809 0.5702 1.0000
3.500 0.7607 0.00785 0.00277 -0.0804 0.5624 1.0000
3.750 0.7864 0.00795 0.00286 -0.0800 0.5549 1.0000
4.000 0.8122 0.00804 0.00296 -0.0796 0.5470 1.0000
4.250 0.8381 0.00814 0.00306 -0.0793 0.5390 1.0000
4.500 0.8638 0.00824 0.00316 -0.0788 0.5304 1.0000
4.750 0.8896 0.00833 0.00329 -0.0785 0.5208 1.0000
5.000 0.9152 0.00846 0.00341 -0.0780 0.5112 1.0000
5.250 0.9406 0.00859 0.00354 -0.0776 0.5006 1.0000
5.500 0.9660 0.00871 0.00369 -0.0771 0.4885 1.0000
5.750 0.9903 0.00887 0.00384 -0.0765 0.4716 1.0000
6.000 1.0144 0.00906 0.00401 -0.0758 0.4505 1.0000
6.250 1.0370 0.00933 0.00420 -0.0749 0.4224 1.0000
6.500 1.0590 0.00968 0.00445 -0.0739 0.3911 1.0000
6.750 1.0772 0.01027 0.00482 -0.0724 0.3413 1.0000
7.000 1.0917 0.01117 0.00537 -0.0704 0.2754 1.0000
7.250 1.1065 0.01205 0.00598 -0.0684 0.2229 1.0000
7.500 1.1210 0.01294 0.00661 -0.0665 0.1744 1.0000
7.750 1.1357 0.01378 0.00724 -0.0646 0.1357 1.0000
8.000 1.1507 0.01456 0.00786 -0.0627 0.1056 1.0000
8.250 1.1641 0.01539 0.00853 -0.0606 0.0780 1.0000
8.500 1.1745 0.01635 0.00931 -0.0580 0.0489 1.0000
8.750 1.1770 0.01753 0.01029 -0.0541 0.0235 1.0000
9.000 1.1852 0.01840 0.01115 -0.0510 0.0174 1.0000
9.250 1.1928 0.01935 0.01213 -0.0481 0.0148 1.0000
9.500 1.2047 0.02009 0.01295 -0.0459 0.0140 1.0000
9.750 1.2146 0.02097 0.01390 -0.0436 0.0133 1.0000
10.000 1.2236 0.02193 0.01493 -0.0413 0.0125 1.0000
10.250 1.2305 0.02307 0.01615 -0.0390 0.0121 1.0000
10.500 1.2340 0.02451 0.01766 -0.0365 0.0116 1.0000
10.750 1.2320 0.02645 0.01971 -0.0339 0.0112 1.0000
11.000 1.2357 0.02811 0.02145 -0.0320 0.0110 1.0000
11.250 1.2418 0.02966 0.02310 -0.0306 0.0109 1.0000
11.500 1.2461 0.03146 0.02500 -0.0291 0.0106 1.0000
11.750 1.2503 0.03333 0.02696 -0.0279 0.0105 1.0000
12.000 1.2538 0.03535 0.02907 -0.0267 0.0103 1.0000
12.250 1.2567 0.03749 0.03132 -0.0256 0.0101 1.0000
12.500 1.2596 0.03971 0.03363 -0.0247 0.0099 1.0000
12.750 1.2630 0.04194 0.03595 -0.0238 0.0098 1.0000
13.000 1.2666 0.04419 0.03830 -0.0230 0.0097 1.0000
13.250 1.2703 0.04650 0.04071 -0.0223 0.0097 1.0000
13.500 1.2741 0.04883 0.04314 -0.0218 0.0094 1.0000
13.750 1.2778 0.05125 0.04566 -0.0213 0.0093 1.0000
14.000 1.2811 0.05376 0.04829 -0.0210 0.0092 1.0000
14.250 1.2836 0.05638 0.05098 -0.0210 0.0090 1.0000
14.500 1.2856 0.05924 0.05399 -0.0206 0.0090 1.0000
14.750 1.2872 0.06209 0.05692 -0.0209 0.0088 1.0000
15.000 1.2873 0.06532 0.06028 -0.0209 0.0087 1.0000
15.250 1.2866 0.06872 0.06381 -0.0213 0.0087 1.0000
15.500 1.2850 0.07232 0.06755 -0.0218 0.0086 1.0000
15.750 1.2812 0.07637 0.07176 -0.0226 0.0086 1.0000
16.000 1.2756 0.08079 0.07636 -0.0237 0.0086 1.0000
16.250 1.2684 0.08558 0.08132 -0.0252 0.0086 1.0000
16.500 1.2596 0.09082 0.08673 -0.0271 0.0086 1.0000
16.750 1.2477 0.09681 0.09295 -0.0295 0.0088 1.0000
17.000 1.2349 0.10315 0.09949 -0.0324 0.0088 1.0000
17.250 1.2191 0.11036 0.10692 -0.0359 0.0089 1.0000
17.500 1.1994 0.11872 0.11551 -0.0404 0.0090 1.0000
17.750 1.1661 0.13070 0.12782 -0.0476 0.0093 1.0000
18.000 1.1452 0.14042 0.13773 -0.0537 0.0094 1.0000
18.250 1.1154 0.15327 0.15081 -0.0619 0.0095 1.0000
18.500 1.0733 0.17108 0.16886 -0.0733 0.0101 1.0000
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Polar data table (+)
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