GOE 242 (MVA PR.2) AIRFOIL (goe242-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 242 (MVA PR.2) AIRFOIL (goe242-il) Reynolds number: 50,000 Max Cl/Cd: 20.93 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe242-il-50000-n5.txt Download as CSV file: xf-goe242-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.0178 0.11473 0.10838 -0.0882 0.9176 0.1441
-9.250 -0.0277 0.11380 0.10749 -0.0930 0.9056 0.1487
-8.750 -0.0221 0.09749 0.09108 -0.1041 0.8861 0.0732
-8.500 0.0011 0.09385 0.08736 -0.1052 0.8800 0.0715
-8.250 0.0074 0.09088 0.08438 -0.1058 0.8680 0.0703
-8.000 0.0112 0.08756 0.08106 -0.1072 0.8570 0.0697
-7.750 0.0153 0.08383 0.07732 -0.1095 0.8478 0.0696
-7.500 0.0115 0.08092 0.07443 -0.1100 0.8349 0.0695
-7.250 0.0108 0.07735 0.07087 -0.1120 0.8238 0.0692
-7.000 0.0146 0.07236 0.06586 -0.1166 0.8153 0.0686
-6.750 0.0108 0.06711 0.06057 -0.1220 0.8031 0.0674
-6.500 0.0194 0.05806 0.05126 -0.1378 0.7935 0.0658
-6.250 0.0569 0.04982 0.04234 -0.1562 0.7850 0.0655
-6.000 0.1064 0.04492 0.03676 -0.1675 0.7808 0.0685
-5.750 0.1392 0.04231 0.03364 -0.1727 0.7711 0.0703
-5.500 0.1812 0.03972 0.03050 -0.1772 0.7665 0.0715
-5.250 0.2115 0.03836 0.02877 -0.1789 0.7589 0.0733
-5.000 0.2374 0.03724 0.02762 -0.1789 0.7528 0.0765
-4.750 0.2695 0.03613 0.02632 -0.1795 0.7489 0.0796
-4.500 0.2889 0.03591 0.02599 -0.1785 0.7408 0.0815
-4.250 0.3169 0.03532 0.02522 -0.1782 0.7359 0.0839
-4.000 0.3500 0.03459 0.02435 -0.1789 0.7325 0.0881
-3.750 0.3718 0.03460 0.02442 -0.1791 0.7244 0.0935
-3.500 0.4059 0.03411 0.02379 -0.1808 0.7199 0.1004
-3.250 0.4505 0.03317 0.02286 -0.1848 0.7168 0.1117
-3.000 0.4949 0.03248 0.02263 -0.1912 0.7107 0.1620
-2.750 0.5068 0.03351 0.02470 -0.1870 0.7056 0.3159
-2.250 0.5596 0.03568 0.02635 -0.1859 0.6968 0.4486
-2.000 0.5766 0.03690 0.02743 -0.1839 0.6909 0.4737
-1.750 0.5933 0.03774 0.02821 -0.1805 0.6872 0.4958
-1.500 0.6203 0.03816 0.02844 -0.1795 0.6847 0.5206
-1.250 0.6248 0.03965 0.02995 -0.1768 0.6775 0.5290
-1.000 0.6545 0.03998 0.03008 -0.1781 0.6735 0.5400
-0.750 0.6835 0.03999 0.02993 -0.1783 0.6705 0.5482
-0.500 0.7185 0.03985 0.02959 -0.1795 0.6683 0.5592
-0.250 0.7185 0.04198 0.03178 -0.1774 0.6600 0.5668
0.000 0.7428 0.04243 0.03214 -0.1772 0.6564 0.5773
0.250 0.7772 0.04246 0.03200 -0.1787 0.6538 0.5888
0.750 0.8024 0.04525 0.03477 -0.1772 0.6420 0.5987
1.000 0.8380 0.04543 0.03480 -0.1794 0.6389 0.6039
1.250 0.8727 0.04521 0.03448 -0.1804 0.6367 0.6080
1.750 0.8937 0.04855 0.03782 -0.1789 0.6230 0.6142
2.000 0.9385 0.04801 0.03712 -0.1815 0.6205 0.6191
2.500 0.9599 0.05072 0.03985 -0.1790 0.6056 0.6247
2.750 1.0068 0.04968 0.03869 -0.1811 0.6033 0.6287
3.250 1.0303 0.05267 0.04169 -0.1795 0.5877 0.6354
3.500 1.0754 0.05139 0.04033 -0.1808 0.5856 0.6395
4.000 1.0768 0.05618 0.04525 -0.1774 0.5665 0.6450
4.500 1.1209 0.05745 0.04650 -0.1770 0.5534 0.6522
5.000 1.1440 0.06031 0.04948 -0.1749 0.5369 0.6591
5.500 1.1699 0.06312 0.05234 -0.1734 0.5202 0.6670
6.000 1.1580 0.06984 0.05926 -0.1704 0.4948 0.6719
6.250 1.1828 0.06979 0.05925 -0.1699 0.4891 0.6767
6.500 1.2192 0.06849 0.05794 -0.1697 0.4865 0.6829
6.750 1.2073 0.07259 0.06217 -0.1683 0.4721 0.6854
7.250 1.2009 0.07913 0.06886 -0.1662 0.4476 0.6924
7.500 1.2214 0.07961 0.06939 -0.1657 0.4415 0.6981
7.750 1.2523 0.07855 0.06839 -0.1649 0.4389 0.7042
8.000 1.2404 0.08315 0.07310 -0.1641 0.4252 0.7074
8.500 1.2582 0.08699 0.07708 -0.1628 0.4094 0.7184
9.000 1.2721 0.09152 0.08177 -0.1616 0.3942 0.7305
9.500 1.2781 0.09752 0.08798 -0.1608 0.3795 0.7426
10.000 1.2789 0.10452 0.09518 -0.1603 0.3652 0.7562
10.250 1.3036 0.10410 0.09489 -0.1595 0.3632 0.7691
10.750 1.2924 0.11339 0.10446 -0.1599 0.3489 0.7875
11.250 1.2683 0.12553 0.11687 -0.1616 0.3356 0.8113
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Polar data table (+)
Polar graphs
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