SA7024 (sa7024-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: SA7024 (sa7024-il) Reynolds number: 1,000,000 Max Cl/Cd: 107.2 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sa7024-il-1000000-n5.txt Download as CSV file: xf-sa7024-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4146 0.11233 0.11063 -0.0159 1.0000 0.0035
-9.750 -0.4116 0.10807 0.10639 -0.0172 1.0000 0.0042
-9.500 -0.4083 0.10536 0.10368 -0.0177 1.0000 0.0037
-5.750 -0.2207 0.02924 0.02697 -0.0869 0.9701 0.0042
-5.500 -0.1953 0.01895 0.01584 -0.0903 0.9611 0.0043
-5.250 -0.1634 0.01681 0.01336 -0.0919 0.9565 0.0044
-5.000 -0.1350 0.01319 0.00917 -0.0931 0.9480 0.0050
-4.750 -0.1031 0.01240 0.00824 -0.0942 0.9396 0.0053
-4.500 -0.0721 0.01167 0.00734 -0.0950 0.9278 0.0057
-4.250 -0.0433 0.01094 0.00643 -0.0952 0.9133 0.0059
-4.000 -0.0158 0.01029 0.00562 -0.0951 0.8975 0.0062
-3.750 0.0111 0.00968 0.00484 -0.0948 0.8809 0.0064
-3.500 0.0378 0.00922 0.00425 -0.0944 0.8643 0.0067
-3.250 0.0645 0.00884 0.00374 -0.0941 0.8479 0.0071
-3.000 0.0911 0.00837 0.00312 -0.0937 0.8310 0.0072
-2.750 0.1178 0.00797 0.00256 -0.0933 0.8123 0.0072
-2.500 0.1444 0.00767 0.00212 -0.0929 0.7919 0.0072
-2.250 0.1711 0.00745 0.00174 -0.0925 0.7700 0.0072
-2.000 0.1979 0.00729 0.00145 -0.0922 0.7497 0.0074
-1.750 0.2249 0.00719 0.00121 -0.0919 0.7300 0.0077
-1.500 0.2519 0.00714 0.00104 -0.0915 0.7102 0.0082
-1.250 0.2790 0.00709 0.00088 -0.0912 0.6897 0.0103
-1.000 0.3059 0.00708 0.00080 -0.0910 0.6691 0.0147
-0.750 0.3328 0.00692 0.00072 -0.0908 0.6482 0.0690
-0.500 0.3595 0.00669 0.00070 -0.0907 0.6264 0.1703
-0.250 0.3860 0.00647 0.00071 -0.0907 0.6025 0.2878
0.000 0.4125 0.00628 0.00075 -0.0906 0.5774 0.4065
0.250 0.4392 0.00622 0.00079 -0.0904 0.5542 0.4786
0.500 0.4660 0.00619 0.00083 -0.0903 0.5346 0.5395
0.750 0.4928 0.00612 0.00088 -0.0901 0.5155 0.6146
1.000 0.5185 0.00591 0.00096 -0.0897 0.4954 0.7496
1.250 0.5375 0.00560 0.00105 -0.0875 0.4776 0.9179
1.500 0.5685 0.00568 0.00107 -0.0881 0.4525 1.0000
1.750 0.5950 0.00588 0.00114 -0.0878 0.4259 1.0000
2.000 0.6216 0.00607 0.00122 -0.0876 0.4008 1.0000
2.250 0.6483 0.00625 0.00130 -0.0874 0.3800 1.0000
2.500 0.6750 0.00644 0.00141 -0.0871 0.3583 1.0000
2.750 0.7017 0.00663 0.00151 -0.0869 0.3394 1.0000
3.000 0.7282 0.00683 0.00162 -0.0867 0.3181 1.0000
3.250 0.7547 0.00704 0.00174 -0.0865 0.2985 1.0000
3.500 0.7807 0.00731 0.00189 -0.0862 0.2718 1.0000
3.750 0.8041 0.00790 0.00216 -0.0855 0.2048 1.0000
4.000 0.8275 0.00852 0.00246 -0.0849 0.1423 1.0000
4.250 0.8518 0.00903 0.00274 -0.0844 0.1012 1.0000
4.500 0.8762 0.00952 0.00304 -0.0839 0.0654 1.0000
4.750 0.9006 0.01000 0.00337 -0.0834 0.0370 1.0000
5.000 0.9253 0.01045 0.00373 -0.0829 0.0177 1.0000
5.250 0.9502 0.01086 0.00409 -0.0824 0.0055 1.0000
5.500 0.9759 0.01116 0.00439 -0.0820 0.0034 1.0000
5.750 1.0015 0.01144 0.00470 -0.0817 0.0031 1.0000
6.000 1.0270 0.01175 0.00504 -0.0813 0.0029 1.0000
6.250 1.0522 0.01209 0.00542 -0.0808 0.0026 1.0000
6.500 1.0770 0.01248 0.00589 -0.0803 0.0023 1.0000
6.750 1.1006 0.01306 0.00656 -0.0795 0.0019 1.0000
7.000 1.1249 0.01349 0.00705 -0.0790 0.0018 1.0000
7.250 1.1487 0.01399 0.00760 -0.0783 0.0018 1.0000
7.500 1.1720 0.01455 0.00824 -0.0776 0.0017 1.0000
7.750 1.1947 0.01518 0.00894 -0.0768 0.0017 1.0000
8.000 1.2168 0.01587 0.00972 -0.0759 0.0016 1.0000
8.250 1.2381 0.01664 0.01059 -0.0749 0.0016 1.0000
8.500 1.2584 0.01750 0.01158 -0.0737 0.0016 1.0000
8.750 1.2781 0.01841 0.01260 -0.0725 0.0016 1.0000
9.000 1.2965 0.01945 0.01375 -0.0711 0.0015 1.0000
9.250 1.3142 0.02052 0.01495 -0.0697 0.0015 1.0000
9.500 1.3305 0.02172 0.01628 -0.0680 0.0015 1.0000
9.750 1.3456 0.02302 0.01773 -0.0663 0.0015 1.0000
10.000 1.3592 0.02442 0.01928 -0.0643 0.0015 1.0000
10.250 1.3712 0.02592 0.02093 -0.0623 0.0015 1.0000
10.500 1.3811 0.02756 0.02274 -0.0599 0.0015 1.0000
10.750 1.3884 0.02923 0.02458 -0.0574 0.0015 1.0000
11.000 1.3901 0.03093 0.02648 -0.0539 0.0015 1.0000
11.250 1.3890 0.03279 0.02850 -0.0504 0.0015 1.0000
11.500 1.3864 0.03480 0.03069 -0.0472 0.0015 1.0000
11.750 1.3808 0.03721 0.03329 -0.0443 0.0015 1.0000
12.000 1.3735 0.03995 0.03621 -0.0419 0.0015 1.0000
12.250 1.3653 0.04301 0.03945 -0.0403 0.0016 1.0000
12.500 1.3549 0.04664 0.04327 -0.0394 0.0016 1.0000
12.750 1.3435 0.05077 0.04757 -0.0395 0.0016 1.0000
13.000 1.3309 0.05553 0.05251 -0.0405 0.0016 1.0000
13.250 1.3154 0.06130 0.05847 -0.0426 0.0016 1.0000
13.500 1.3001 0.06764 0.06497 -0.0457 0.0016 1.0000
13.750 1.2848 0.07461 0.07209 -0.0496 0.0016 1.0000
14.000 1.2678 0.08248 0.08012 -0.0542 0.0016 1.0000
14.250 1.2489 0.09133 0.08913 -0.0596 0.0016 1.0000
14.500 1.2313 0.10041 0.09833 -0.0652 0.0016 1.0000
14.750 1.2118 0.11042 0.10847 -0.0712 0.0016 1.0000
15.000 1.1933 0.12065 0.11882 -0.0773 0.0016 1.0000
|
Polar data table (+)
Polar graphs
<< Back to SA7024 (sa7024-il)