GOE 234 (MVA CA5) AIRFOIL (goe234-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 234 (MVA CA5) AIRFOIL (goe234-il) Reynolds number: 50,000 Max Cl/Cd: 27.67 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe234-il-50000-n5.txt Download as CSV file: xf-goe234-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 234 (MVA CA5) 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.1359 0.12969 0.12291 -0.0629 0.9569 0.1486
-9.000 -0.1353 0.12803 0.12127 -0.0649 0.9487 0.1493
-8.750 -0.1319 0.11958 0.11273 -0.0705 0.9436 0.1067
-8.500 -0.1237 0.11480 0.10790 -0.0725 0.9375 0.0941
-8.250 -0.1105 0.11161 0.10470 -0.0736 0.9311 0.0920
-8.000 -0.0974 0.10806 0.10112 -0.0771 0.9264 0.0914
-7.750 -0.0990 0.10590 0.09899 -0.0768 0.9169 0.0910
-7.500 -0.0894 0.10257 0.09565 -0.0796 0.9112 0.0903
-7.250 -0.0938 0.10037 0.09348 -0.0790 0.9014 0.0891
-7.000 -0.0861 0.09631 0.08941 -0.0827 0.8950 0.0872
-6.750 -0.0928 0.09297 0.08610 -0.0838 0.8844 0.0856
-6.500 -0.0808 0.08801 0.08111 -0.0895 0.8786 0.0850
-6.250 -0.0786 0.08618 0.07930 -0.0890 0.8689 0.0859
-6.000 -0.0602 0.08275 0.07584 -0.0930 0.8633 0.0874
-5.750 -0.0542 0.07921 0.07229 -0.0961 0.8546 0.0879
-5.500 -0.0357 0.07298 0.06599 -0.1047 0.8478 0.0876
-5.250 0.0372 0.05568 0.04812 -0.1405 0.8451 0.0897
-5.000 0.1407 0.04582 0.03727 -0.1705 0.8443 0.0958
-4.750 0.1594 0.04547 0.03694 -0.1701 0.8353 0.0979
-4.500 0.2007 0.04430 0.03566 -0.1742 0.8308 0.1029
-4.250 0.2471 0.04314 0.03440 -0.1789 0.8277 0.1100
-4.000 0.2739 0.04288 0.03413 -0.1801 0.8199 0.1159
-3.750 0.3094 0.04246 0.03375 -0.1826 0.8141 0.1252
-3.500 0.3517 0.04201 0.03342 -0.1857 0.8105 0.1430
-3.250 0.3714 0.04274 0.03435 -0.1840 0.8033 0.1604
-2.750 0.4125 0.04508 0.03678 -0.1786 0.7913 0.2128
-2.500 0.4312 0.04625 0.03781 -0.1781 0.7819 0.2428
-2.000 0.4925 0.04792 0.03913 -0.1780 0.7725 0.2922
-1.750 0.5014 0.04903 0.04019 -0.1758 0.7622 0.3039
-1.500 0.5265 0.04951 0.04058 -0.1749 0.7570 0.3205
-1.250 0.5580 0.04959 0.04055 -0.1747 0.7539 0.3391
-1.000 0.5677 0.05058 0.04151 -0.1736 0.7431 0.3490
-0.750 0.6039 0.05012 0.04089 -0.1758 0.7388 0.3570
-0.500 0.6514 0.04927 0.03984 -0.1802 0.7362 0.3643
-0.250 0.6572 0.05030 0.04088 -0.1783 0.7252 0.3683
0.250 0.7383 0.04914 0.03946 -0.1838 0.7184 0.3835
0.500 0.7466 0.05044 0.04075 -0.1828 0.7071 0.3885
0.750 0.7850 0.04996 0.04017 -0.1850 0.7033 0.3959
1.000 0.8275 0.04916 0.03927 -0.1875 0.7008 0.4030
1.250 0.8352 0.05076 0.04086 -0.1867 0.6887 0.4066
1.500 0.8743 0.05000 0.04004 -0.1885 0.6853 0.4114
2.000 0.9221 0.05071 0.04070 -0.1891 0.6700 0.4178
2.250 0.9709 0.04958 0.03945 -0.1924 0.6672 0.4213
2.500 0.9792 0.05110 0.04098 -0.1912 0.6547 0.4238
2.750 1.0220 0.04970 0.03956 -0.1926 0.6509 0.4271
3.250 1.0780 0.04935 0.03918 -0.1930 0.6343 0.4305
3.750 1.1343 0.04909 0.03887 -0.1934 0.6174 0.4357
4.250 1.1874 0.04915 0.03894 -0.1934 0.6003 0.4404
4.500 1.2231 0.04838 0.03815 -0.1940 0.5943 0.4422
4.750 1.2354 0.04948 0.03933 -0.1926 0.5830 0.4433
5.000 1.2824 0.04786 0.03766 -0.1942 0.5791 0.4460
5.250 1.2808 0.05007 0.03997 -0.1915 0.5653 0.4476
5.500 1.3282 0.04843 0.03828 -0.1931 0.5611 0.4518
5.750 1.3257 0.05077 0.04072 -0.1903 0.5471 0.4533
6.250 1.3689 0.05141 0.04142 -0.1887 0.5284 0.4572
6.750 1.4121 0.05194 0.04202 -0.1869 0.5094 0.4608
7.000 1.4116 0.05421 0.04439 -0.1845 0.4959 0.4624
7.250 1.4548 0.05257 0.04271 -0.1850 0.4905 0.4670
7.500 1.4495 0.05537 0.04562 -0.1824 0.4766 0.4688
7.750 1.4554 0.05732 0.04764 -0.1806 0.4651 0.4710
8.000 1.4850 0.05678 0.04711 -0.1801 0.4580 0.4741
8.250 1.4832 0.05948 0.04991 -0.1780 0.4459 0.4756
8.500 1.5181 0.05846 0.04889 -0.1777 0.4399 0.4787
8.750 1.5102 0.06190 0.05244 -0.1754 0.4279 0.4798
9.000 1.5465 0.06075 0.05126 -0.1751 0.4225 0.4838
9.250 1.5323 0.06505 0.05569 -0.1728 0.4111 0.4852
9.500 1.5644 0.06430 0.05498 -0.1723 0.4062 0.4896
9.750 1.5467 0.06924 0.06008 -0.1701 0.3962 0.4908
10.000 1.5678 0.06977 0.06068 -0.1692 0.3910 0.4948
10.250 1.6065 0.06842 0.05934 -0.1689 0.3878 0.4998
10.500 1.5554 0.07763 0.06879 -0.1664 0.3765 0.4986
10.750 1.5850 0.07712 0.06833 -0.1657 0.3730 0.5025
11.250 1.5415 0.08963 0.08115 -0.1636 0.3574 0.5035
11.500 1.5713 0.08887 0.08050 -0.1626 0.3552 0.5075
12.000 1.4625 0.11391 0.10580 -0.1650 0.3352 0.5040
12.500 1.4333 0.12759 0.11970 -0.1674 0.3221 0.5056
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Polar data table (+)
Polar graphs
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