GOE 421 AIRFOIL (goe421-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 421 AIRFOIL (goe421-il) Reynolds number: 200,000 Max Cl/Cd: 60.42 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe421-il-200000-n5.txt Download as CSV file: xf-goe421-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 421 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.2323 0.04596 0.04091 -0.1793 0.8785 0.0468
-12.000 -0.2581 0.04043 0.03520 -0.1836 0.8670 0.0471
-11.750 -0.2677 0.03599 0.03051 -0.1889 0.8588 0.0475
-11.500 -0.2651 0.03392 0.02825 -0.1896 0.8511 0.0482
-11.250 -0.2509 0.03189 0.02598 -0.1912 0.8466 0.0491
-11.000 -0.2444 0.03049 0.02438 -0.1903 0.8389 0.0499
-10.750 -0.2290 0.02897 0.02258 -0.1906 0.8336 0.0510
-10.500 -0.2062 0.02759 0.02097 -0.1916 0.8301 0.0520
-10.250 -0.1912 0.02688 0.02025 -0.1904 0.8236 0.0528
-10.000 -0.1701 0.02609 0.01939 -0.1902 0.8184 0.0537
-9.750 -0.1438 0.02517 0.01834 -0.1910 0.8145 0.0549
-9.500 -0.1230 0.02442 0.01745 -0.1906 0.8093 0.0561
-9.250 -0.1033 0.02373 0.01662 -0.1898 0.8036 0.0574
-9.000 -0.0778 0.02298 0.01566 -0.1901 0.7994 0.0587
-8.750 -0.0493 0.02221 0.01485 -0.1910 0.7961 0.0601
-8.500 -0.0309 0.02176 0.01437 -0.1897 0.7901 0.0613
-8.250 -0.0077 0.02125 0.01378 -0.1893 0.7849 0.0627
-8.000 0.0204 0.02069 0.01308 -0.1898 0.7809 0.0645
-7.750 0.0478 0.02021 0.01244 -0.1901 0.7769 0.0664
-7.500 0.0674 0.01978 0.01204 -0.1890 0.7714 0.0681
-7.250 0.0923 0.01938 0.01159 -0.1888 0.7668 0.0701
-7.000 0.1214 0.01896 0.01106 -0.1893 0.7631 0.0725
-6.750 0.1482 0.01862 0.01060 -0.1894 0.7589 0.0750
-6.500 0.1693 0.01829 0.01029 -0.1884 0.7534 0.0775
-6.250 0.1952 0.01799 0.00992 -0.1883 0.7490 0.0809
-6.000 0.2249 0.01769 0.00950 -0.1889 0.7455 0.0847
-5.750 0.2522 0.01736 0.00914 -0.1891 0.7417 0.0889
-5.500 0.2741 0.01716 0.00892 -0.1881 0.7365 0.0939
-5.250 0.2999 0.01689 0.00861 -0.1880 0.7319 0.1000
-5.000 0.3294 0.01662 0.00827 -0.1885 0.7283 0.1084
-4.750 0.3587 0.01635 0.00799 -0.1890 0.7250 0.1201
-4.500 0.3803 0.01624 0.00797 -0.1880 0.7199 0.1349
-4.250 0.4059 0.01622 0.00801 -0.1877 0.7154 0.1541
-4.000 0.4352 0.01625 0.00797 -0.1880 0.7116 0.1714
-3.750 0.4673 0.01627 0.00788 -0.1889 0.7086 0.1838
-3.500 0.4883 0.01638 0.00792 -0.1876 0.7034 0.1927
-3.250 0.5126 0.01641 0.00794 -0.1870 0.6982 0.1996
-3.000 0.5416 0.01641 0.00782 -0.1873 0.6936 0.2071
-2.750 0.5680 0.01641 0.00773 -0.1870 0.6886 0.2130
-2.500 0.5888 0.01642 0.00777 -0.1858 0.6822 0.2184
-2.250 0.6160 0.01641 0.00767 -0.1857 0.6768 0.2249
-2.000 0.6424 0.01644 0.00759 -0.1855 0.6715 0.2309
-1.750 0.6620 0.01642 0.00763 -0.1840 0.6648 0.2361
-1.500 0.6885 0.01639 0.00753 -0.1838 0.6589 0.2414
-1.250 0.7118 0.01644 0.00752 -0.1830 0.6531 0.2469
-1.000 0.7320 0.01646 0.00754 -0.1817 0.6472 0.2517
-0.750 0.7575 0.01643 0.00751 -0.1813 0.6425 0.2560
-0.500 0.7840 0.01643 0.00746 -0.1812 0.6381 0.2589
-0.250 0.8017 0.01652 0.00756 -0.1794 0.6327 0.2615
0.000 0.8245 0.01657 0.00760 -0.1785 0.6277 0.2650
0.250 0.8510 0.01661 0.00756 -0.1784 0.6234 0.2687
0.500 0.8725 0.01669 0.00768 -0.1774 0.6185 0.2720
0.750 0.8931 0.01682 0.00785 -0.1762 0.6130 0.2758
1.000 0.9173 0.01690 0.00792 -0.1757 0.6078 0.2804
1.250 0.9415 0.01701 0.00800 -0.1752 0.6028 0.2858
1.500 0.9603 0.01721 0.00826 -0.1738 0.5964 0.2915
1.750 0.9830 0.01734 0.00840 -0.1731 0.5905 0.2998
2.000 1.0052 0.01750 0.00858 -0.1723 0.5847 0.3100
2.250 1.0235 0.01775 0.00889 -0.1708 0.5779 0.3235
2.500 1.0457 0.01791 0.00907 -0.1700 0.5718 0.3423
2.750 1.0651 0.01816 0.00938 -0.1688 0.5653 0.3636
3.000 1.0836 0.01842 0.00971 -0.1675 0.5581 0.3859
3.250 1.1044 0.01863 0.00993 -0.1665 0.5515 0.4092
3.500 1.1209 0.01896 0.01036 -0.1649 0.5435 0.4321
3.750 1.1400 0.01922 0.01065 -0.1637 0.5360 0.4598
4.000 1.1562 0.01956 0.01114 -0.1621 0.5274 0.4978
4.250 1.1739 0.01978 0.01154 -0.1607 0.5189 0.5804
4.500 1.1806 0.01954 0.01196 -0.1568 0.5099 1.0000
4.750 1.1964 0.02005 0.01238 -0.1552 0.5005 1.0000
5.000 1.2104 0.02066 0.01295 -0.1533 0.4899 1.0000
5.250 1.2245 0.02130 0.01351 -0.1515 0.4794 1.0000
5.500 1.2370 0.02201 0.01414 -0.1496 0.4686 1.0000
5.750 1.2501 0.02275 0.01483 -0.1478 0.4577 1.0000
6.000 1.2621 0.02355 0.01556 -0.1458 0.4477 1.0000
6.250 1.2744 0.02438 0.01633 -0.1440 0.4377 1.0000
6.500 1.2868 0.02523 0.01712 -0.1423 0.4290 1.0000
6.750 1.2990 0.02612 0.01796 -0.1405 0.4205 1.0000
7.000 1.3120 0.02700 0.01880 -0.1390 0.4132 1.0000
7.250 1.3250 0.02790 0.01967 -0.1375 0.4060 1.0000
7.500 1.3377 0.02883 0.02052 -0.1359 0.3999 1.0000
7.750 1.3522 0.02969 0.02140 -0.1347 0.3942 1.0000
8.000 1.3664 0.03059 0.02228 -0.1335 0.3889 1.0000
8.250 1.3803 0.03149 0.02314 -0.1322 0.3843 1.0000
8.500 1.3953 0.03236 0.02401 -0.1311 0.3800 1.0000
8.750 1.4096 0.03329 0.02497 -0.1300 0.3751 1.0000
9.000 1.4228 0.03428 0.02594 -0.1287 0.3703 1.0000
9.250 1.4363 0.03524 0.02684 -0.1275 0.3660 1.0000
9.500 1.4505 0.03622 0.02787 -0.1265 0.3620 1.0000
9.750 1.4648 0.03719 0.02888 -0.1255 0.3582 1.0000
10.000 1.4788 0.03818 0.02989 -0.1245 0.3546 1.0000
10.250 1.4929 0.03915 0.03085 -0.1235 0.3514 1.0000
10.500 1.5084 0.04000 0.03166 -0.1226 0.3485 1.0000
10.750 1.5229 0.04100 0.03274 -0.1218 0.3458 1.0000
11.000 1.5370 0.04202 0.03384 -0.1209 0.3433 1.0000
11.250 1.5507 0.04308 0.03496 -0.1200 0.3406 1.0000
11.500 1.5637 0.04419 0.03612 -0.1191 0.3375 1.0000
11.750 1.5766 0.04529 0.03724 -0.1182 0.3344 1.0000
12.000 1.5914 0.04620 0.03813 -0.1174 0.3315 1.0000
12.250 1.6031 0.04745 0.03945 -0.1164 0.3287 1.0000
12.500 1.6120 0.04896 0.04109 -0.1154 0.3253 1.0000
12.750 1.6201 0.05055 0.04276 -0.1143 0.3215 1.0000
13.000 1.6289 0.05203 0.04427 -0.1132 0.3173 1.0000
13.250 1.6399 0.05327 0.04546 -0.1123 0.3130 1.0000
13.500 1.6437 0.05537 0.04773 -0.1112 0.3089 1.0000
13.750 1.6481 0.05742 0.04989 -0.1101 0.3044 1.0000
14.000 1.6542 0.05925 0.05176 -0.1091 0.2999 1.0000
14.250 1.6630 0.06076 0.05325 -0.1082 0.2959 1.0000
14.500 1.6653 0.06314 0.05580 -0.1072 0.2917 1.0000
14.750 1.6672 0.06555 0.05833 -0.1063 0.2866 1.0000
15.000 1.6698 0.06784 0.06066 -0.1053 0.2813 1.0000
15.250 1.6703 0.07046 0.06339 -0.1045 0.2758 1.0000
15.500 1.6693 0.07332 0.06637 -0.1036 0.2695 1.0000
15.750 1.6688 0.07606 0.06914 -0.1028 0.2633 1.0000
16.000 1.6659 0.07922 0.07247 -0.1021 0.2560 1.0000
16.250 1.6602 0.08270 0.07601 -0.1014 0.2470 1.0000
16.500 1.6520 0.08655 0.07994 -0.1007 0.2347 1.0000
16.750 1.6413 0.09075 0.08418 -0.1001 0.2175 1.0000
17.000 1.6179 0.09655 0.08988 -0.0994 0.1922 1.0000
17.250 1.5892 0.10312 0.09637 -0.0990 0.1763 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 421 AIRFOIL (goe421-il)