E387 (e387-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: E387 (e387-il) Reynolds number: 100,000 Max Cl/Cd: 60.66 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e387-il-100000.txt Download as CSV file: xf-e387-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: E387
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3494 0.10359 0.09882 -0.0293 1.0000 0.0775
-8.500 -0.3569 0.10207 0.09741 -0.0331 1.0000 0.0784
-8.250 -0.3669 0.10046 0.09593 -0.0366 1.0000 0.0787
-8.000 -0.3345 0.09342 0.08882 -0.0310 1.0000 0.0830
-7.750 -0.3300 0.09063 0.08610 -0.0313 1.0000 0.0860
-7.500 -0.3321 0.08819 0.08376 -0.0324 1.0000 0.0892
-7.250 -0.3464 0.08667 0.08240 -0.0355 1.0000 0.0917
-7.000 -0.3592 0.08488 0.08072 -0.0431 1.0000 0.0926
-6.750 -0.3585 0.08082 0.07679 -0.0390 1.0000 0.0939
-6.500 -0.3577 0.07863 0.07469 -0.0333 1.0000 0.0959
-6.250 -0.3751 0.07784 0.07402 -0.0295 1.0000 0.0967
-6.000 -0.3934 0.07714 0.07342 -0.0263 1.0000 0.0975
-5.750 -0.3539 0.07033 0.06637 -0.0462 0.9884 0.1078
-5.500 -0.3280 0.06660 0.06271 -0.0448 0.9829 0.1121
-5.250 -0.2881 0.06071 0.05663 -0.0566 0.9728 0.1239
-5.000 -0.2518 0.05602 0.05174 -0.0647 0.9623 0.1374
-4.750 -0.2147 0.05183 0.04740 -0.0707 0.9543 0.1520
-4.500 -0.1794 0.04800 0.04347 -0.0751 0.9461 0.1674
-4.250 -0.1185 0.03620 0.03002 -0.0860 0.9381 0.0780
-4.000 -0.0767 0.03078 0.02389 -0.0892 0.9317 0.0639
-3.750 -0.0393 0.02783 0.02038 -0.0913 0.9237 0.0637
-3.500 0.0001 0.02508 0.01712 -0.0933 0.9167 0.0631
-3.250 0.0351 0.02305 0.01466 -0.0942 0.9081 0.0635
-3.000 0.0731 0.02113 0.01244 -0.0954 0.9013 0.0665
-2.750 0.1030 0.02003 0.01130 -0.0956 0.8916 0.0766
-2.500 0.1373 0.01851 0.00989 -0.0962 0.8852 0.1012
-2.250 0.1612 0.01714 0.00913 -0.0956 0.8747 0.2153
-2.000 0.1827 0.01539 0.00887 -0.0944 0.8666 0.5432
-1.750 0.2349 0.01412 0.00834 -0.0967 0.8609 1.0000
-1.500 0.2622 0.01426 0.00812 -0.0965 0.8520 1.0000
-1.250 0.2889 0.01441 0.00797 -0.0962 0.8432 1.0000
-1.000 0.3136 0.01465 0.00798 -0.0957 0.8336 1.0000
-0.750 0.3417 0.01477 0.00784 -0.0954 0.8267 1.0000
-0.500 0.3654 0.01508 0.00798 -0.0948 0.8167 1.0000
-0.250 0.3918 0.01530 0.00802 -0.0944 0.8092 1.0000
0.000 0.4171 0.01557 0.00814 -0.0940 0.8008 1.0000
0.250 0.4425 0.01586 0.00830 -0.0935 0.7929 1.0000
0.500 0.4687 0.01611 0.00842 -0.0931 0.7854 1.0000
0.750 0.4936 0.01647 0.00870 -0.0927 0.7773 1.0000
1.000 0.5202 0.01670 0.00883 -0.0923 0.7703 1.0000
1.250 0.5447 0.01712 0.00920 -0.0920 0.7622 1.0000
1.500 0.5714 0.01736 0.00936 -0.0916 0.7556 1.0000
1.750 0.5956 0.01781 0.00980 -0.0912 0.7473 1.0000
2.000 0.6225 0.01806 0.01000 -0.0908 0.7409 1.0000
2.250 0.6464 0.01856 0.01051 -0.0904 0.7326 1.0000
2.500 0.6734 0.01879 0.01071 -0.0900 0.7263 1.0000
2.750 0.6969 0.01933 0.01128 -0.0896 0.7176 1.0000
3.000 0.7244 0.01952 0.01148 -0.0892 0.7114 1.0000
3.250 0.7473 0.02008 0.01210 -0.0887 0.7021 1.0000
3.500 0.7756 0.02018 0.01218 -0.0882 0.6960 1.0000
3.750 0.7981 0.02075 0.01284 -0.0876 0.6859 1.0000
4.000 0.8240 0.02101 0.01318 -0.0870 0.6780 1.0000
4.250 0.8498 0.02122 0.01344 -0.0863 0.6691 1.0000
4.500 0.8735 0.02160 0.01391 -0.0856 0.6588 1.0000
4.750 0.9013 0.02158 0.01393 -0.0848 0.6505 1.0000
5.000 0.9264 0.02171 0.01419 -0.0839 0.6397 1.0000
5.250 0.9506 0.02191 0.01450 -0.0830 0.6280 1.0000
5.500 0.9760 0.02193 0.01462 -0.0820 0.6163 1.0000
5.750 1.0024 0.02178 0.01457 -0.0809 0.6041 1.0000
6.000 1.0289 0.02156 0.01447 -0.0798 0.5909 1.0000
6.250 1.0545 0.02134 0.01436 -0.0786 0.5761 1.0000
6.500 1.0795 0.02109 0.01424 -0.0773 0.5597 1.0000
6.750 1.1049 0.02071 0.01400 -0.0760 0.5415 1.0000
7.000 1.1295 0.02022 0.01361 -0.0744 0.5196 1.0000
7.250 1.1506 0.01966 0.01316 -0.0722 0.4873 1.0000
7.500 1.1684 0.01926 0.01274 -0.0697 0.4395 1.0000
7.750 1.1811 0.01956 0.01285 -0.0669 0.3679 1.0000
8.000 1.1859 0.02093 0.01362 -0.0636 0.2720 1.0000
8.250 1.1841 0.02318 0.01523 -0.0601 0.1832 1.0000
8.500 1.1722 0.02636 0.01761 -0.0557 0.1054 1.0000
8.750 1.1640 0.02905 0.02002 -0.0513 0.0754 1.0000
9.000 1.1620 0.03121 0.02211 -0.0478 0.0652 1.0000
9.250 1.1654 0.03317 0.02403 -0.0452 0.0579 1.0000
9.500 1.1746 0.03512 0.02603 -0.0431 0.0524 1.0000
9.750 1.1885 0.03698 0.02789 -0.0415 0.0483 1.0000
10.000 1.2243 0.04001 0.03083 -0.0418 0.0451 1.0000
10.250 1.2563 0.04274 0.03386 -0.0419 0.0437 1.0000
10.500 1.2836 0.04607 0.03754 -0.0418 0.0429 1.0000
10.750 1.3005 0.04957 0.04143 -0.0407 0.0426 1.0000
11.000 1.3076 0.05292 0.04517 -0.0388 0.0422 1.0000
11.250 1.3074 0.05611 0.04873 -0.0364 0.0419 1.0000
11.500 1.3017 0.05928 0.05223 -0.0338 0.0414 1.0000
11.750 1.2924 0.06268 0.05595 -0.0315 0.0413 1.0000
12.000 1.2797 0.06643 0.06000 -0.0298 0.0413 1.0000
12.250 1.2645 0.07057 0.06443 -0.0287 0.0416 1.0000
12.500 1.2470 0.07509 0.06922 -0.0284 0.0418 1.0000
12.750 1.2276 0.08010 0.07448 -0.0289 0.0422 1.0000
13.000 1.2072 0.08561 0.08021 -0.0301 0.0426 1.0000
13.250 1.1859 0.09161 0.08642 -0.0322 0.0431 1.0000
13.500 1.1640 0.09815 0.09313 -0.0350 0.0435 1.0000
13.750 1.1420 0.10527 0.10041 -0.0386 0.0440 1.0000
14.000 1.1218 0.11282 0.10808 -0.0426 0.0445 1.0000
14.250 1.1071 0.12043 0.11575 -0.0461 0.0451 1.0000
|
Polar data table (+)
Polar graphs
<< Back to E387 (e387-il)