GOE 242 (MVA PR.2) AIRFOIL (goe242-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 242 (MVA PR.2) AIRFOIL (goe242-il) Reynolds number: 100,000 Max Cl/Cd: 46.79 at α=9.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe242-il-100000.txt Download as CSV file: xf-goe242-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 242 (MVA PR.2) AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-10.000 0.0470 0.10355 0.09931 -0.1054 0.9241 0.1176
-9.750 0.0917 0.09710 0.09281 -0.1033 0.9155 0.1233
-9.500 0.0945 0.09435 0.09005 -0.1070 0.9088 0.1316
-9.250 0.1014 0.09063 0.08633 -0.1078 0.8977 0.1350
-9.000 0.0197 0.10148 0.09703 -0.0992 0.9319 0.1264
-8.750 -0.0007 0.10060 0.09622 -0.1090 0.9153 0.1331
-8.500 0.0531 0.09465 0.09016 -0.1056 0.9131 0.1406
-8.250 0.0353 0.09334 0.08892 -0.1119 0.8962 0.1485
-8.000 0.0781 0.08861 0.08409 -0.1095 0.8922 0.1542
-7.750 0.1534 0.07360 0.06914 -0.1093 0.8409 0.1741
-7.500 0.1420 0.07161 0.06720 -0.1106 0.8289 0.1806
-7.250 0.1648 0.06889 0.06441 -0.1089 0.8220 0.1887
-7.000 0.1078 0.07940 0.07480 -0.1108 0.8444 0.1844
-6.500 0.1220 0.07531 0.07066 -0.1108 0.8257 0.2013
-6.250 0.1141 0.07403 0.06943 -0.1151 0.8131 0.2133
-6.000 0.1718 0.03871 0.03267 -0.1855 0.8039 0.0988
-5.750 0.2302 0.03339 0.02625 -0.1965 0.7972 0.0901
-5.500 0.2711 0.03102 0.02350 -0.1998 0.7928 0.0912
-5.250 0.3025 0.02974 0.02191 -0.2013 0.7838 0.0905
-5.000 0.3376 0.02829 0.02020 -0.2026 0.7786 0.0905
-4.750 0.3682 0.02730 0.01912 -0.2032 0.7730 0.0922
-4.500 0.3960 0.02677 0.01854 -0.2035 0.7660 0.0956
-4.250 0.4270 0.02603 0.01773 -0.2035 0.7617 0.0981
-4.000 0.4537 0.02578 0.01748 -0.2031 0.7564 0.1003
-3.750 0.4788 0.02574 0.01747 -0.2024 0.7500 0.1032
-3.500 0.5118 0.02526 0.01704 -0.2032 0.7459 0.1114
-3.250 0.5504 0.02480 0.01658 -0.2059 0.7417 0.1253
-3.000 0.5965 0.02397 0.01685 -0.2120 0.7358 0.3125
-2.750 0.6182 0.02559 0.01844 -0.2092 0.7315 0.4380
-2.500 0.6322 0.02716 0.02003 -0.2040 0.7284 0.4648
-2.250 0.6462 0.02883 0.02170 -0.2010 0.7227 0.4879
-2.000 0.6583 0.03000 0.02291 -0.1969 0.7177 0.4997
-1.750 0.6777 0.03067 0.02352 -0.1941 0.7143 0.5158
-1.500 0.7046 0.03109 0.02381 -0.1930 0.7118 0.5373
-1.250 0.7051 0.03283 0.02570 -0.1886 0.7055 0.5460
-1.000 0.7204 0.03364 0.02651 -0.1860 0.7013 0.5643
-0.750 0.7474 0.03384 0.02661 -0.1853 0.6984 0.5861
-0.500 0.7729 0.03367 0.02635 -0.1841 0.6961 0.5971
-0.250 0.7782 0.03593 0.02870 -0.1834 0.6887 0.6037
0.000 0.8011 0.03632 0.02905 -0.1831 0.6847 0.6109
0.250 0.8417 0.03599 0.02856 -0.1859 0.6823 0.6189
0.500 0.8744 0.03558 0.02807 -0.1862 0.6803 0.6271
0.750 0.8693 0.03886 0.03146 -0.1847 0.6702 0.6335
1.000 0.9022 0.03798 0.03052 -0.1843 0.6671 0.6438
1.250 0.9499 0.03647 0.02886 -0.1863 0.6648 0.6536
1.500 0.9425 0.03937 0.03189 -0.1837 0.6543 0.6570
1.750 0.9911 0.03819 0.03057 -0.1866 0.6512 0.6619
2.000 1.0462 0.03665 0.02884 -0.1905 0.6489 0.6648
2.250 1.0359 0.03978 0.03214 -0.1873 0.6387 0.6662
2.500 1.0797 0.03856 0.03084 -0.1891 0.6352 0.6694
2.750 1.1324 0.03691 0.02905 -0.1921 0.6327 0.6721
3.000 1.1249 0.03993 0.03222 -0.1894 0.6225 0.6731
3.250 1.1715 0.03878 0.03100 -0.1918 0.6189 0.6763
3.500 1.2249 0.03729 0.02936 -0.1951 0.6162 0.6804
3.750 1.2160 0.04013 0.03239 -0.1917 0.6059 0.6819
4.000 1.2604 0.03897 0.03118 -0.1936 0.6022 0.6851
4.250 1.3115 0.03751 0.02961 -0.1964 0.5993 0.6888
4.500 1.3036 0.04021 0.03250 -0.1930 0.5886 0.6905
4.750 1.3538 0.03889 0.03110 -0.1958 0.5849 0.6952
5.000 1.4041 0.03737 0.02950 -0.1982 0.5818 0.7001
5.250 1.3970 0.03966 0.03200 -0.1944 0.5705 0.7026
5.500 1.4499 0.03805 0.03031 -0.1974 0.5667 0.7078
5.750 1.4521 0.03975 0.03216 -0.1947 0.5562 0.7106
6.000 1.4980 0.03843 0.03080 -0.1966 0.5513 0.7155
6.250 1.5098 0.03935 0.03185 -0.1947 0.5423 0.7197
6.500 1.5485 0.03859 0.03107 -0.1960 0.5357 0.7261
6.750 1.5699 0.03876 0.03131 -0.1951 0.5274 0.7311
7.000 1.6005 0.03829 0.03087 -0.1952 0.5194 0.7371
7.250 1.6186 0.03864 0.03129 -0.1939 0.5099 0.7423
7.500 1.6554 0.03771 0.03034 -0.1947 0.5023 0.7492
7.750 1.6619 0.03857 0.03134 -0.1919 0.4915 0.7551
8.000 1.7087 0.03719 0.02988 -0.1940 0.4848 0.7646
8.250 1.7056 0.03852 0.03139 -0.1900 0.4734 0.7707
8.500 1.7416 0.03781 0.03065 -0.1908 0.4659 0.7804
8.750 1.7461 0.03871 0.03169 -0.1877 0.4559 0.7881
9.000 1.7553 0.03931 0.03240 -0.1851 0.4471 0.7977
9.250 1.7817 0.03885 0.03196 -0.1846 0.4389 0.8120
9.500 1.7716 0.04035 0.03364 -0.1798 0.4298 0.8242
9.750 1.8084 0.03865 0.03195 -0.1801 0.4208 0.8743
10.000 1.7866 0.04103 0.03453 -0.1744 0.4116 1.0000
10.250 1.7987 0.04148 0.03495 -0.1727 0.4017 1.0000
10.500 1.8240 0.04097 0.03428 -0.1721 0.3910 1.0000
10.750 1.8089 0.04375 0.03723 -0.1683 0.3822 1.0000
11.000 1.8249 0.04431 0.03774 -0.1672 0.3734 1.0000
11.250 1.8267 0.04611 0.03959 -0.1651 0.3652 1.0000
11.500 1.8361 0.04738 0.04086 -0.1636 0.3574 1.0000
11.750 1.8401 0.04907 0.04257 -0.1618 0.3494 1.0000
12.000 1.8450 0.05077 0.04430 -0.1600 0.3418 1.0000
12.250 1.8471 0.05271 0.04629 -0.1583 0.3344 1.0000
12.500 1.8536 0.05432 0.04795 -0.1567 0.3273 1.0000
12.750 1.8476 0.05713 0.05088 -0.1548 0.3206 1.0000
13.000 1.8611 0.05805 0.05176 -0.1536 0.3132 1.0000
13.250 1.8451 0.06200 0.05593 -0.1516 0.3074 1.0000
13.500 1.8571 0.06284 0.05669 -0.1503 0.2985 1.0000
13.750 1.8356 0.06764 0.06175 -0.1487 0.2933 1.0000
14.000 1.8441 0.06890 0.06297 -0.1475 0.2846 1.0000
14.250 1.8233 0.07400 0.06832 -0.1464 0.2792 1.0000
14.500 1.8146 0.07763 0.07206 -0.1456 0.2717 1.0000
14.750 1.8012 0.08202 0.07659 -0.1450 0.2643 1.0000
15.000 1.7875 0.08664 0.08135 -0.1447 0.2568 1.0000
15.250 1.7745 0.09129 0.08613 -0.1446 0.2493 1.0000
15.500 1.7578 0.09665 0.09163 -0.1449 0.2411 1.0000
15.750 1.7402 0.10233 0.09747 -0.1454 0.2334 1.0000
16.000 1.7298 0.10692 0.10210 -0.1460 0.2228 1.0000
16.250 1.7031 0.11458 0.11005 -0.1475 0.2172 1.0000
16.500 1.6864 0.12059 0.11617 -0.1489 0.2063 1.0000
16.750 1.6602 0.12856 0.12438 -0.1513 0.1994 1.0000
17.000 1.6364 0.13634 0.13231 -0.1539 0.1893 1.0000
17.250 1.6115 0.14463 0.14075 -0.1572 0.1779 1.0000
17.500 1.5816 0.15422 0.15057 -0.1614 0.1734 1.0000
17.750 1.5641 0.16152 0.15780 -0.1650 0.1288 1.0000
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