GOE 233 (MVA CA4) AIRFOIL (goe233-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 233 (MVA CA4) AIRFOIL (goe233-il) Reynolds number: 50,000 Max Cl/Cd: 33.37 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe233-il-50000-n5.txt Download as CSV file: xf-goe233-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 233 (MVA CA4) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.1831 0.10646 0.09978 -0.0588 0.9580 0.0841
-7.500 -0.1707 0.10334 0.09665 -0.0600 0.9497 0.0827
-7.250 -0.1555 0.09971 0.09301 -0.0633 0.9434 0.0802
-7.000 -0.1510 0.09662 0.08993 -0.0655 0.9331 0.0779
-6.750 -0.1416 0.09056 0.08383 -0.0746 0.9242 0.0739
-6.500 -0.1327 0.08756 0.08084 -0.0765 0.9143 0.0737
-6.250 -0.1104 0.08240 0.07563 -0.0844 0.9086 0.0741
-6.000 -0.1013 0.08119 0.07446 -0.0831 0.8988 0.0755
-5.750 -0.0764 0.07658 0.06978 -0.0901 0.8931 0.0756
-5.500 -0.0621 0.06988 0.06302 -0.0995 0.8827 0.0743
-5.250 -0.0186 0.05998 0.05290 -0.1172 0.8776 0.0740
-5.000 0.0329 0.05223 0.04489 -0.1335 0.8725 0.0756
-4.750 0.1217 0.04230 0.03419 -0.1604 0.8692 0.0813
-4.500 0.1902 0.03758 0.02875 -0.1743 0.8658 0.0858
-4.250 0.2315 0.03641 0.02753 -0.1778 0.8615 0.0905
-4.000 0.2792 0.03497 0.02594 -0.1830 0.8582 0.0996
-3.750 0.3097 0.03439 0.02537 -0.1851 0.8495 0.1117
-3.500 0.3546 0.03343 0.02447 -0.1894 0.8451 0.1402
-3.250 0.3864 0.03363 0.02483 -0.1900 0.8394 0.1748
-3.000 0.4065 0.03465 0.02590 -0.1881 0.8307 0.2029
-2.750 0.4306 0.03605 0.02729 -0.1853 0.8258 0.2229
-2.500 0.4472 0.03701 0.02818 -0.1832 0.8160 0.2396
-2.250 0.4814 0.03734 0.02830 -0.1842 0.8108 0.2635
-2.000 0.5027 0.03815 0.02905 -0.1825 0.8033 0.2800
-1.750 0.5276 0.03860 0.02942 -0.1818 0.7960 0.2960
-1.500 0.5650 0.03832 0.02896 -0.1833 0.7919 0.3120
-1.250 0.5932 0.03826 0.02872 -0.1849 0.7830 0.3249
-1.000 0.6219 0.03814 0.02852 -0.1847 0.7773 0.3335
-0.750 0.6629 0.03749 0.02769 -0.1873 0.7739 0.3458
-0.500 0.6867 0.03777 0.02782 -0.1881 0.7639 0.3569
-0.250 0.7183 0.03753 0.02750 -0.1885 0.7591 0.3663
0.000 0.7470 0.03756 0.02744 -0.1892 0.7525 0.3764
0.250 0.7767 0.03767 0.02740 -0.1904 0.7450 0.3875
0.500 0.8092 0.03733 0.02704 -0.1908 0.7409 0.3958
0.750 0.8298 0.03791 0.02757 -0.1905 0.7319 0.4053
1.000 0.8606 0.03786 0.02746 -0.1911 0.7263 0.4162
1.250 0.8959 0.03745 0.02702 -0.1920 0.7228 0.4257
1.500 0.9125 0.03843 0.02795 -0.1914 0.7124 0.4336
1.750 0.9450 0.03815 0.02767 -0.1919 0.7080 0.4400
2.000 0.9666 0.03878 0.02828 -0.1917 0.6998 0.4455
2.250 0.9954 0.03896 0.02842 -0.1922 0.6935 0.4508
2.500 1.0311 0.03861 0.02804 -0.1931 0.6898 0.4565
2.750 1.0440 0.03983 0.02929 -0.1918 0.6795 0.4604
3.000 1.0784 0.03971 0.02910 -0.1927 0.6748 0.4649
3.250 1.0971 0.04048 0.02992 -0.1918 0.6669 0.4684
3.500 1.1218 0.04085 0.03032 -0.1915 0.6598 0.4729
3.750 1.1616 0.04018 0.02958 -0.1925 0.6559 0.4782
4.000 1.1713 0.04150 0.03095 -0.1906 0.6439 0.4808
4.250 1.2127 0.04036 0.02982 -0.1913 0.6390 0.4851
4.500 1.2237 0.04135 0.03088 -0.1891 0.6264 0.4886
4.750 1.2707 0.03975 0.02922 -0.1903 0.6210 0.4949
5.000 1.2798 0.04079 0.03036 -0.1878 0.6076 0.4978
5.250 1.2990 0.04120 0.03084 -0.1864 0.5976 0.5012
5.500 1.3266 0.04112 0.03082 -0.1858 0.5898 0.5052
5.750 1.3399 0.04212 0.03192 -0.1840 0.5797 0.5091
6.000 1.3688 0.04192 0.03180 -0.1835 0.5721 0.5143
6.250 1.3762 0.04322 0.03323 -0.1810 0.5609 0.5179
6.500 1.4102 0.04263 0.03272 -0.1809 0.5540 0.5238
6.750 1.4093 0.04440 0.03463 -0.1776 0.5417 0.5268
7.000 1.4488 0.04341 0.03374 -0.1780 0.5351 0.5324
7.250 1.4467 0.04513 0.03562 -0.1744 0.5223 0.5358
7.500 1.4521 0.04654 0.03716 -0.1718 0.5101 0.5404
7.750 1.4922 0.04517 0.03593 -0.1718 0.5027 0.5486
8.000 1.4905 0.04710 0.03802 -0.1686 0.4892 0.5528
8.250 1.4963 0.04857 0.03964 -0.1663 0.4767 0.5580
8.500 1.5212 0.04837 0.03958 -0.1650 0.4667 0.5650
8.750 1.5393 0.04873 0.04011 -0.1633 0.4550 0.5723
9.000 1.5439 0.05035 0.04190 -0.1610 0.4416 0.5790
9.250 1.5570 0.05125 0.04296 -0.1591 0.4296 0.5883
9.500 1.5907 0.05030 0.04216 -0.1583 0.4198 0.6035
9.750 1.5883 0.05273 0.04481 -0.1558 0.4065 0.6130
10.250 1.6167 0.05450 0.04699 -0.1524 0.3839 0.6641
10.500 1.6144 0.05621 0.04885 -0.1494 0.3711 1.0000
10.750 1.6096 0.05883 0.05154 -0.1471 0.3567 1.0000
11.000 1.6066 0.06116 0.05390 -0.1449 0.3412 1.0000
11.250 1.6033 0.06353 0.05628 -0.1428 0.3249 1.0000
11.500 1.5996 0.06606 0.05880 -0.1409 0.3087 1.0000
11.750 1.5960 0.06880 0.06156 -0.1392 0.2938 1.0000
12.000 1.5938 0.07158 0.06438 -0.1378 0.2807 1.0000
12.250 1.5940 0.07409 0.06691 -0.1364 0.2683 1.0000
12.500 1.5954 0.07639 0.06919 -0.1349 0.2557 1.0000
12.750 1.5917 0.07956 0.07244 -0.1338 0.2431 1.0000
13.000 1.5847 0.08340 0.07641 -0.1331 0.2308 1.0000
13.250 1.5793 0.08700 0.08007 -0.1324 0.2178 1.0000
13.500 1.5728 0.09080 0.08391 -0.1319 0.2041 1.0000
13.750 1.5642 0.09509 0.08827 -0.1317 0.1899 1.0000
14.000 1.5532 0.10000 0.09329 -0.1321 0.1750 1.0000
14.250 1.5418 0.10521 0.09862 -0.1328 0.1594 1.0000
14.500 1.5320 0.11021 0.10367 -0.1336 0.1440 1.0000
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Polar data table (+)
Polar graphs
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