EPPLER 479 AIRFOIL (e479-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: EPPLER 479 AIRFOIL (e479-il) Reynolds number: 200,000 Max Cl/Cd: 52.16 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e479-il-200000.txt Download as CSV file: xf-e479-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 479 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.750 -1.0696 0.12789 0.12333 -0.0004 1.0000 0.0572
-19.500 -1.1060 0.11719 0.11237 -0.0070 1.0000 0.0581
-19.250 -1.1356 0.10806 0.10297 -0.0126 1.0000 0.0591
-19.000 -1.1195 0.10762 0.10268 -0.0121 1.0000 0.0616
-18.750 -1.1229 0.10345 0.09849 -0.0144 1.0000 0.0637
-18.500 -1.1388 0.09715 0.09204 -0.0179 1.0000 0.0655
-18.250 -1.1584 0.09036 0.08503 -0.0217 1.0000 0.0670
-18.000 -1.1617 0.08658 0.08121 -0.0233 1.0000 0.0692
-17.750 -1.1603 0.08356 0.07822 -0.0246 1.0000 0.0715
-17.500 -1.1674 0.07917 0.07375 -0.0268 1.0000 0.0738
-17.250 -1.1800 0.07404 0.06844 -0.0294 1.0000 0.0758
-17.000 -1.1910 0.06936 0.06358 -0.0316 1.0000 0.0778
-16.750 -1.1858 0.06717 0.06150 -0.0320 1.0000 0.0806
-16.500 -1.1898 0.06368 0.05795 -0.0335 1.0000 0.0831
-16.250 -1.1976 0.05976 0.05389 -0.0352 1.0000 0.0856
-16.000 -1.2095 0.05551 0.04940 -0.0370 1.0000 0.0876
-15.750 -1.2023 0.05373 0.04775 -0.0368 1.0000 0.0908
-15.500 -1.2043 0.05087 0.04486 -0.0376 1.0000 0.0936
-15.250 -1.2083 0.04783 0.04168 -0.0385 1.0000 0.0965
-15.000 -1.2144 0.04469 0.03833 -0.0393 1.0000 0.0990
-14.750 -1.2083 0.04288 0.03665 -0.0390 1.0000 0.1026
-14.500 -1.2080 0.04060 0.03430 -0.0392 1.0000 0.1059
-14.250 -1.2094 0.03825 0.03180 -0.0392 1.0000 0.1093
-14.000 -1.2068 0.03629 0.02979 -0.0388 1.0000 0.1129
-13.750 -1.2035 0.03458 0.02810 -0.0382 1.0000 0.1166
-13.500 -1.2019 0.03289 0.02632 -0.0375 1.0000 0.1206
-13.250 -1.2002 0.03130 0.02458 -0.0363 1.0000 0.1245
-13.000 -1.1937 0.03002 0.02338 -0.0351 1.0000 0.1288
-12.750 -1.1896 0.02887 0.02215 -0.0334 1.0000 0.1333
-12.500 -1.1861 0.02778 0.02090 -0.0313 1.0000 0.1376
-12.250 -1.1773 0.02680 0.02002 -0.0295 1.0000 0.1424
-12.000 -1.1712 0.02602 0.01917 -0.0270 1.0000 0.1473
-11.750 -1.1640 0.02520 0.01826 -0.0244 1.0000 0.1523
-11.500 -1.1526 0.02446 0.01759 -0.0224 1.0000 0.1575
-11.250 -1.1407 0.02384 0.01684 -0.0204 1.0000 0.1635
-11.000 -1.1258 0.02306 0.01611 -0.0188 1.0000 0.1693
-10.750 -1.1107 0.02250 0.01551 -0.0171 1.0000 0.1756
-10.500 -1.0946 0.02185 0.01480 -0.0155 1.0000 0.1821
-10.250 -1.0775 0.02130 0.01429 -0.0140 1.0000 0.1886
-10.000 -1.0603 0.02079 0.01365 -0.0125 1.0000 0.1957
-9.750 -1.0416 0.02024 0.01320 -0.0111 1.0000 0.2025
-9.250 -1.0039 0.01931 0.01226 -0.0084 1.0000 0.2172
-9.000 -0.9851 0.01896 0.01177 -0.0069 1.0000 0.2253
-8.750 -0.9650 0.01850 0.01143 -0.0056 1.0000 0.2325
-8.500 -0.9458 0.01820 0.01101 -0.0042 1.0000 0.2409
-8.250 -0.9253 0.01779 0.01071 -0.0029 1.0000 0.2480
-8.000 -0.9058 0.01753 0.01035 -0.0014 1.0000 0.2565
-7.750 -0.8852 0.01716 0.01009 -0.0002 1.0000 0.2636
-7.500 -0.8654 0.01692 0.00977 0.0013 1.0000 0.2720
-7.250 -0.8451 0.01660 0.00953 0.0026 1.0000 0.2791
-7.000 -0.8258 0.01639 0.00927 0.0042 1.0000 0.2873
-6.750 -0.8068 0.01609 0.00904 0.0057 1.0000 0.2942
-6.500 -0.7893 0.01592 0.00886 0.0074 1.0000 0.3019
-6.250 -0.7741 0.01570 0.00865 0.0095 1.0000 0.3088
-6.000 -0.7380 0.01555 0.00854 0.0075 0.9942 0.3179
-5.750 -0.6903 0.01530 0.00830 0.0034 0.9834 0.3279
-5.500 -0.6444 0.01512 0.00806 -0.0001 0.9707 0.3385
-5.250 -0.5998 0.01481 0.00784 -0.0034 0.9566 0.3475
-5.000 -0.5564 0.01457 0.00753 -0.0063 0.9392 0.3575
-4.750 -0.5134 0.01430 0.00733 -0.0090 0.9199 0.3664
-4.500 -0.4769 0.01409 0.00703 -0.0103 0.8939 0.3755
-4.250 -0.4449 0.01394 0.00686 -0.0107 0.8667 0.3834
-4.000 -0.4185 0.01385 0.00663 -0.0099 0.8377 0.3917
-3.750 -0.3927 0.01375 0.00650 -0.0091 0.8116 0.3989
-3.500 -0.3677 0.01373 0.00631 -0.0081 0.7860 0.4074
-3.250 -0.3421 0.01361 0.00617 -0.0073 0.7628 0.4144
-3.000 -0.3166 0.01358 0.00601 -0.0065 0.7403 0.4230
-2.750 -0.2907 0.01347 0.00588 -0.0058 0.7187 0.4305
-2.500 -0.2648 0.01345 0.00575 -0.0051 0.6981 0.4392
-2.250 -0.2387 0.01336 0.00562 -0.0045 0.6786 0.4472
-2.000 -0.2125 0.01334 0.00552 -0.0039 0.6601 0.4564
-1.750 -0.1861 0.01327 0.00542 -0.0034 0.6424 0.4649
-1.500 -0.1597 0.01326 0.00533 -0.0028 0.6252 0.4747
-1.250 -0.1332 0.01320 0.00527 -0.0023 0.6090 0.4838
-0.750 -0.0801 0.01317 0.00516 -0.0014 0.5795 0.5044
-0.500 -0.0534 0.01317 0.00510 -0.0009 0.5657 0.5156
-0.250 -0.0267 0.01315 0.00509 -0.0005 0.5517 0.5274
0.000 0.0000 0.01313 0.00511 0.0000 0.5390 0.5390
0.250 0.0267 0.01315 0.00509 0.0005 0.5274 0.5517
0.500 0.0534 0.01317 0.00510 0.0009 0.5156 0.5657
0.750 0.0801 0.01317 0.00516 0.0014 0.5044 0.5794
1.250 0.1332 0.01320 0.00527 0.0023 0.4837 0.6090
1.500 0.1597 0.01326 0.00533 0.0028 0.4747 0.6252
1.750 0.1862 0.01327 0.00542 0.0034 0.4648 0.6424
2.000 0.2125 0.01334 0.00552 0.0039 0.4563 0.6602
2.250 0.2387 0.01336 0.00562 0.0045 0.4472 0.6785
2.500 0.2649 0.01345 0.00575 0.0051 0.4392 0.6981
2.750 0.2908 0.01348 0.00588 0.0058 0.4305 0.7187
3.000 0.3166 0.01358 0.00601 0.0065 0.4230 0.7403
3.250 0.3421 0.01361 0.00617 0.0073 0.4145 0.7628
3.500 0.3677 0.01373 0.00631 0.0081 0.4074 0.7860
3.750 0.3927 0.01375 0.00650 0.0091 0.3989 0.8116
4.000 0.4185 0.01385 0.00663 0.0099 0.3917 0.8377
4.250 0.4449 0.01394 0.00686 0.0107 0.3834 0.8667
4.500 0.4769 0.01409 0.00703 0.0103 0.3755 0.8941
4.750 0.5134 0.01430 0.00733 0.0090 0.3665 0.9199
5.000 0.5564 0.01457 0.00753 0.0063 0.3575 0.9393
5.250 0.5998 0.01481 0.00785 0.0034 0.3475 0.9566
5.500 0.6445 0.01512 0.00806 0.0001 0.3385 0.9708
5.750 0.6904 0.01530 0.00830 -0.0035 0.3279 0.9835
6.000 0.7381 0.01555 0.00853 -0.0075 0.3179 0.9942
6.250 0.7740 0.01570 0.00865 -0.0094 0.3088 1.0000
6.500 0.7892 0.01592 0.00886 -0.0074 0.3019 1.0000
6.750 0.8067 0.01609 0.00904 -0.0057 0.2943 1.0000
7.000 0.8257 0.01639 0.00927 -0.0041 0.2873 1.0000
7.250 0.8450 0.01660 0.00953 -0.0026 0.2791 1.0000
7.500 0.8654 0.01692 0.00977 -0.0013 0.2720 1.0000
7.750 0.8851 0.01716 0.01009 0.0002 0.2636 1.0000
8.000 0.9058 0.01753 0.01034 0.0014 0.2565 1.0000
8.250 0.9253 0.01779 0.01071 0.0029 0.2481 1.0000
8.500 0.9458 0.01820 0.01101 0.0042 0.2409 1.0000
8.750 0.9650 0.01850 0.01143 0.0056 0.2325 1.0000
9.000 0.9851 0.01896 0.01177 0.0069 0.2253 1.0000
9.250 1.0040 0.01931 0.01226 0.0084 0.2173 1.0000
9.500 1.0236 0.01983 0.01265 0.0096 0.2101 1.0000
9.750 1.0417 0.02024 0.01320 0.0111 0.2025 1.0000
10.000 1.0604 0.02078 0.01365 0.0125 0.1957 1.0000
10.250 1.0777 0.02130 0.01429 0.0140 0.1886 1.0000
10.500 1.0948 0.02185 0.01480 0.0155 0.1821 1.0000
10.750 1.1109 0.02250 0.01551 0.0171 0.1756 1.0000
11.000 1.1261 0.02306 0.01611 0.0187 0.1693 1.0000
11.250 1.1409 0.02384 0.01684 0.0203 0.1635 1.0000
11.500 1.1530 0.02446 0.01759 0.0224 0.1575 1.0000
11.750 1.1645 0.02521 0.01826 0.0243 0.1522 1.0000
12.000 1.1717 0.02602 0.01917 0.0269 0.1473 1.0000
12.250 1.1778 0.02679 0.02001 0.0294 0.1423 1.0000
12.500 1.1867 0.02778 0.02089 0.0312 0.1375 1.0000
12.750 1.1901 0.02887 0.02214 0.0333 0.1332 1.0000
13.000 1.1943 0.03001 0.02337 0.0350 0.1287 1.0000
13.250 1.2011 0.03129 0.02456 0.0362 0.1243 1.0000
13.500 1.2025 0.03290 0.02632 0.0374 0.1205 1.0000
13.750 1.2043 0.03457 0.02809 0.0381 0.1165 1.0000
14.000 1.2078 0.03627 0.02977 0.0387 0.1128 1.0000
14.250 1.2104 0.03824 0.03179 0.0391 0.1092 1.0000
14.500 1.2091 0.04059 0.03429 0.0390 0.1058 1.0000
14.750 1.2095 0.04286 0.03661 0.0389 0.1025 1.0000
15.000 1.2161 0.04463 0.03825 0.0392 0.0988 1.0000
15.250 1.2095 0.04782 0.04167 0.0383 0.0964 1.0000
15.500 1.2056 0.05085 0.04483 0.0375 0.0935 1.0000
15.750 1.2038 0.05370 0.04772 0.0366 0.0907 1.0000
16.000 1.2097 0.05564 0.04954 0.0367 0.0875 1.0000
16.250 1.1988 0.05978 0.05391 0.0349 0.0854 1.0000
16.500 1.1915 0.06363 0.05789 0.0333 0.0830 1.0000
16.750 1.1879 0.06708 0.06139 0.0319 0.0805 1.0000
17.000 1.1941 0.06910 0.06331 0.0316 0.0776 1.0000
17.250 1.1813 0.07406 0.06846 0.0292 0.0757 1.0000
17.500 1.1694 0.07909 0.07367 0.0266 0.0737 1.0000
17.750 1.1624 0.08349 0.07815 0.0244 0.0714 1.0000
18.000 1.1646 0.08637 0.08098 0.0232 0.0690 1.0000
18.250 1.1604 0.09030 0.08496 0.0216 0.0670 1.0000
18.500 1.1403 0.09718 0.09207 0.0176 0.0654 1.0000
|
Polar data table (+)
Polar graphs
<< Back to EPPLER 479 AIRFOIL (e479-il)