SA7024 (sa7024-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: SA7024 (sa7024-il) Reynolds number: 1,000,000 Max Cl/Cd: 122.37 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sa7024-il-1000000.txt Download as CSV file: xf-sa7024-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: SA7024
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3903 0.09762 0.09599 -0.0211 1.0000 0.0070
-8.500 -0.3882 0.09435 0.09274 -0.0218 1.0000 0.0071
-6.500 -0.3708 0.06443 0.06298 -0.0386 0.9960 0.0077
-6.250 -0.3394 0.05929 0.05780 -0.0477 0.9941 0.0080
-6.000 -0.3088 0.05375 0.05220 -0.0563 0.9907 0.0083
-5.750 -0.2729 0.04722 0.04556 -0.0660 0.9876 0.0085
-5.500 -0.2347 0.04064 0.03882 -0.0746 0.9853 0.0090
-5.250 -0.1955 0.03412 0.03206 -0.0818 0.9835 0.0096
-5.000 -0.1626 0.02885 0.02651 -0.0852 0.9794 0.0107
-4.750 -0.1275 0.02654 0.02398 -0.0868 0.9759 0.0117
-4.500 -0.0917 0.02251 0.01951 -0.0899 0.9731 0.0118
-3.000 0.0955 0.00891 0.00424 -0.0958 0.9396 0.0130
-2.750 0.1265 0.00856 0.00380 -0.0961 0.9296 0.0122
-2.250 0.1826 0.00734 0.00236 -0.0957 0.9006 0.0116
-2.000 0.2100 0.00694 0.00183 -0.0954 0.8845 0.0120
-1.750 0.2374 0.00658 0.00128 -0.0950 0.8679 0.0141
-1.500 0.2645 0.00648 0.00108 -0.0946 0.8507 0.0158
-1.250 0.2915 0.00642 0.00094 -0.0943 0.8334 0.0184
-1.000 0.3183 0.00617 0.00081 -0.0940 0.8148 0.0825
-0.750 0.3447 0.00583 0.00075 -0.0938 0.7952 0.2086
-0.500 0.3709 0.00550 0.00075 -0.0936 0.7749 0.3530
-0.250 0.3970 0.00533 0.00077 -0.0933 0.7527 0.4571
0.000 0.4226 0.00497 0.00082 -0.0930 0.7304 0.6310
0.250 0.4456 0.00423 0.00087 -0.0915 0.7095 1.0000
0.500 0.4723 0.00435 0.00087 -0.0912 0.6877 1.0000
0.750 0.4989 0.00448 0.00089 -0.0909 0.6662 1.0000
1.000 0.5255 0.00462 0.00091 -0.0905 0.6440 1.0000
1.250 0.5522 0.00476 0.00095 -0.0902 0.6213 1.0000
1.500 0.5786 0.00492 0.00099 -0.0899 0.5970 1.0000
1.750 0.6050 0.00509 0.00104 -0.0895 0.5705 1.0000
2.000 0.6314 0.00528 0.00111 -0.0892 0.5439 1.0000
2.250 0.6578 0.00546 0.00118 -0.0889 0.5184 1.0000
2.500 0.6844 0.00563 0.00127 -0.0886 0.4949 1.0000
2.750 0.7108 0.00583 0.00137 -0.0883 0.4695 1.0000
3.000 0.7372 0.00603 0.00147 -0.0880 0.4460 1.0000
3.250 0.7636 0.00624 0.00159 -0.0878 0.4218 1.0000
3.500 0.7897 0.00647 0.00173 -0.0875 0.3954 1.0000
3.750 0.8155 0.00674 0.00188 -0.0871 0.3655 1.0000
4.000 0.8412 0.00703 0.00204 -0.0867 0.3336 1.0000
4.250 0.8671 0.00730 0.00221 -0.0864 0.3077 1.0000
4.500 0.8924 0.00764 0.00241 -0.0860 0.2749 1.0000
4.750 0.9171 0.00805 0.00266 -0.0856 0.2353 1.0000
5.000 0.9416 0.00849 0.00292 -0.0851 0.1984 1.0000
5.250 0.9666 0.00887 0.00317 -0.0846 0.1704 1.0000
5.500 0.9908 0.00935 0.00348 -0.0841 0.1360 1.0000
5.750 1.0148 0.00984 0.00381 -0.0836 0.1048 1.0000
6.000 1.0377 0.01048 0.00425 -0.0829 0.0672 1.0000
6.250 1.0605 0.01114 0.00472 -0.0822 0.0370 1.0000
6.500 1.0830 0.01185 0.00529 -0.0814 0.0132 1.0000
6.750 1.1066 0.01243 0.00583 -0.0806 0.0057 1.0000
7.000 1.1310 0.01286 0.00632 -0.0800 0.0049 1.0000
7.250 1.1547 0.01340 0.00692 -0.0793 0.0042 1.0000
7.500 1.1774 0.01408 0.00772 -0.0784 0.0037 1.0000
7.750 1.1988 0.01494 0.00873 -0.0773 0.0035 1.0000
8.000 1.2188 0.01595 0.00988 -0.0759 0.0034 1.0000
8.250 1.2377 0.01705 0.01113 -0.0745 0.0033 1.0000
8.500 1.2562 0.01815 0.01234 -0.0730 0.0034 1.0000
8.750 1.2738 0.01934 0.01365 -0.0714 0.0034 1.0000
9.000 1.2916 0.02045 0.01488 -0.0699 0.0034 1.0000
9.250 1.3090 0.02160 0.01613 -0.0684 0.0035 1.0000
9.500 1.3260 0.02275 0.01742 -0.0668 0.0035 1.0000
9.750 1.3421 0.02399 0.01879 -0.0652 0.0036 1.0000
10.000 1.3564 0.02549 0.02047 -0.0632 0.0038 1.0000
10.250 1.3551 0.03038 0.02587 -0.0589 0.0048 1.0000
10.500 1.3443 0.03638 0.03235 -0.0545 0.0055 1.0000
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Polar data table (+)
Polar graphs
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