SA7025 (sa7025-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: SA7025 (sa7025-il) Reynolds number: 1,000,000 Max Cl/Cd: 112.38 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sa7025-il-1000000-n5.txt Download as CSV file: xf-sa7025-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SA7025
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
------ -------- --------- --------- -------- -------- --------
-12.000 -0.3967 0.13436 0.13262 -0.0208 1.0000 0.0030
-11.750 -0.3910 0.13139 0.12966 -0.0220 1.0000 0.0041
-11.500 -0.3864 0.12771 0.12599 -0.0231 1.0000 0.0039
-11.250 -0.3793 0.12536 0.12364 -0.0240 1.0000 0.0049
-11.000 -0.3753 0.12178 0.12007 -0.0251 1.0000 0.0044
-10.750 -0.3699 0.11875 0.11704 -0.0260 1.0000 0.0048
-10.500 -0.3635 0.11544 0.11374 -0.0275 1.0000 0.0059
-10.250 -0.2681 0.10204 0.10051 -0.0339 0.9995 0.0061
-9.750 -0.2550 0.09387 0.09234 -0.0379 0.9915 0.0061
-9.500 -0.2479 0.08958 0.08804 -0.0402 0.9880 0.0061
-9.250 -0.2406 0.08522 0.08369 -0.0426 0.9849 0.0061
-9.000 -0.2332 0.08077 0.07924 -0.0451 0.9811 0.0061
-8.750 -0.2263 0.07638 0.07485 -0.0475 0.9762 0.0061
-8.500 -0.3243 0.08924 0.08766 -0.0378 0.9900 0.0061
-8.250 -0.3112 0.08471 0.08313 -0.0423 0.9855 0.0061
-8.000 -0.2957 0.08019 0.07861 -0.0475 0.9817 0.0061
-7.750 -0.2845 0.07523 0.07365 -0.0531 0.9750 0.0051
-7.500 -0.2688 0.07001 0.06842 -0.0602 0.9650 0.0047
-7.250 -0.2596 0.06470 0.06307 -0.0668 0.9505 0.0043
-7.000 -0.2575 0.05765 0.05597 -0.0740 0.9344 0.0039
-6.750 -0.2540 0.04845 0.04665 -0.0826 0.9205 0.0037
-6.500 -0.2421 0.04077 0.03878 -0.0884 0.9112 0.0038
-6.250 -0.2290 0.03210 0.02977 -0.0924 0.9027 0.0038
-6.000 -0.2123 0.02530 0.02256 -0.0939 0.8957 0.0040
-5.750 -0.1913 0.02172 0.01864 -0.0942 0.8896 0.0043
-5.500 -0.1685 0.01863 0.01517 -0.0943 0.8837 0.0047
-5.250 -0.1442 0.01641 0.01261 -0.0942 0.8775 0.0049
-5.000 -0.1188 0.01470 0.01059 -0.0940 0.8720 0.0051
-4.750 -0.0926 0.01334 0.00897 -0.0938 0.8659 0.0053
-4.500 -0.0660 0.01250 0.00794 -0.0937 0.8602 0.0055
-4.250 -0.0388 0.01182 0.00710 -0.0935 0.8534 0.0058
-4.000 -0.0121 0.01092 0.00601 -0.0933 0.8466 0.0058
-3.750 0.0150 0.01006 0.00500 -0.0931 0.8388 0.0058
-3.500 0.0420 0.00937 0.00417 -0.0929 0.8309 0.0058
-3.250 0.0692 0.00879 0.00348 -0.0927 0.8219 0.0058
-3.000 0.0967 0.00833 0.00291 -0.0925 0.8128 0.0059
-2.750 0.1241 0.00797 0.00244 -0.0924 0.8030 0.0059
-2.500 0.1517 0.00770 0.00207 -0.0922 0.7917 0.0061
-2.250 0.1792 0.00748 0.00177 -0.0921 0.7781 0.0063
-2.000 0.2067 0.00721 0.00135 -0.0919 0.7621 0.0076
-1.750 0.2341 0.00712 0.00117 -0.0917 0.7443 0.0088
-1.500 0.2615 0.00708 0.00103 -0.0915 0.7266 0.0100
-1.250 0.2888 0.00702 0.00092 -0.0914 0.7094 0.0181
-1.000 0.3160 0.00683 0.00084 -0.0913 0.6915 0.0709
-0.750 0.3431 0.00668 0.00079 -0.0913 0.6736 0.1329
-0.250 0.3967 0.00625 0.00079 -0.0912 0.6355 0.3378
0.000 0.4235 0.00621 0.00081 -0.0911 0.6140 0.4012
0.250 0.4503 0.00614 0.00084 -0.0910 0.5930 0.4730
0.500 0.4771 0.00610 0.00088 -0.0909 0.5736 0.5353
0.750 0.5039 0.00602 0.00093 -0.0908 0.5556 0.6118
1.000 0.5295 0.00581 0.00101 -0.0904 0.5374 0.7396
1.250 0.5495 0.00552 0.00110 -0.0885 0.5193 0.9025
1.500 0.5827 0.00555 0.00113 -0.0896 0.4984 1.0000
1.750 0.6093 0.00572 0.00119 -0.0894 0.4775 1.0000
2.000 0.6361 0.00589 0.00126 -0.0892 0.4576 1.0000
2.250 0.6627 0.00608 0.00135 -0.0890 0.4364 1.0000
2.500 0.6893 0.00625 0.00144 -0.0889 0.4177 1.0000
2.750 0.7160 0.00643 0.00153 -0.0887 0.3986 1.0000
3.000 0.7424 0.00663 0.00164 -0.0885 0.3796 1.0000
3.250 0.7687 0.00684 0.00176 -0.0882 0.3573 1.0000
3.500 0.7947 0.00708 0.00191 -0.0880 0.3340 1.0000
3.750 0.8208 0.00732 0.00206 -0.0878 0.3130 1.0000
4.000 0.8470 0.00754 0.00221 -0.0875 0.2960 1.0000
4.250 0.8731 0.00777 0.00237 -0.0873 0.2765 1.0000
4.500 0.8974 0.00820 0.00262 -0.0868 0.2374 1.0000
4.750 0.9216 0.00863 0.00287 -0.0863 0.2017 1.0000
5.000 0.9459 0.00905 0.00314 -0.0859 0.1694 1.0000
5.250 0.9701 0.00948 0.00342 -0.0854 0.1397 1.0000
5.500 0.9929 0.01006 0.00378 -0.0848 0.1009 1.0000
5.750 1.0143 0.01081 0.00428 -0.0839 0.0545 1.0000
6.000 1.0354 0.01159 0.00483 -0.0830 0.0180 1.0000
6.250 1.0587 0.01210 0.00528 -0.0823 0.0055 1.0000
6.500 1.0832 0.01244 0.00563 -0.0818 0.0037 1.0000
6.750 1.1078 0.01277 0.00600 -0.0813 0.0033 1.0000
7.000 1.1320 0.01313 0.00639 -0.0808 0.0030 1.0000
7.250 1.1555 0.01357 0.00689 -0.0802 0.0026 1.0000
7.500 1.1785 0.01403 0.00742 -0.0795 0.0023 1.0000
7.750 1.2006 0.01461 0.00808 -0.0786 0.0022 1.0000
8.000 1.2215 0.01529 0.00885 -0.0775 0.0020 1.0000
8.250 1.2419 0.01599 0.00963 -0.0764 0.0020 1.0000
8.500 1.2625 0.01663 0.01035 -0.0753 0.0020 1.0000
8.750 1.2821 0.01734 0.01114 -0.0741 0.0019 1.0000
9.000 1.3006 0.01811 0.01199 -0.0728 0.0019 1.0000
9.250 1.3179 0.01895 0.01295 -0.0713 0.0019 1.0000
9.500 1.3337 0.01986 0.01396 -0.0696 0.0019 1.0000
9.750 1.3501 0.02066 0.01484 -0.0680 0.0019 1.0000
10.000 1.3647 0.02153 0.01580 -0.0662 0.0018 1.0000
10.250 1.3774 0.02233 0.01668 -0.0640 0.0018 1.0000
10.500 1.3874 0.02323 0.01767 -0.0614 0.0017 1.0000
10.750 1.3960 0.02422 0.01877 -0.0588 0.0017 1.0000
11.000 1.4036 0.02533 0.01998 -0.0562 0.0016 1.0000
11.250 1.4085 0.02668 0.02145 -0.0534 0.0016 1.0000
11.500 1.4118 0.02822 0.02312 -0.0507 0.0016 1.0000
11.750 1.4177 0.02959 0.02462 -0.0485 0.0016 1.0000
12.000 1.4190 0.03144 0.02660 -0.0461 0.0016 1.0000
12.250 1.4205 0.03334 0.02864 -0.0440 0.0015 1.0000
12.500 1.4200 0.03554 0.03098 -0.0421 0.0015 1.0000
12.750 1.4194 0.03785 0.03343 -0.0405 0.0015 1.0000
13.000 1.4178 0.04041 0.03613 -0.0392 0.0015 1.0000
13.250 1.4159 0.04313 0.03899 -0.0383 0.0014 1.0000
13.500 1.4128 0.04615 0.04215 -0.0378 0.0014 1.0000
13.750 1.4052 0.04995 0.04612 -0.0376 0.0014 1.0000
14.000 1.3988 0.05384 0.05016 -0.0380 0.0014 1.0000
14.250 1.3917 0.05809 0.05455 -0.0390 0.0014 1.0000
14.500 1.3812 0.06314 0.05976 -0.0404 0.0014 1.0000
14.750 1.3700 0.06867 0.06545 -0.0425 0.0014 1.0000
15.000 1.3595 0.07443 0.07135 -0.0451 0.0013 1.0000
15.250 1.3456 0.08113 0.07821 -0.0483 0.0013 1.0000
15.500 1.3293 0.08866 0.08591 -0.0521 0.0014 1.0000
15.750 1.3139 0.09637 0.09376 -0.0563 0.0014 1.0000
16.000 1.3002 0.10408 0.10160 -0.0606 0.0013 1.0000
16.250 1.2847 0.11245 0.11011 -0.0654 0.0013 1.0000
16.500 1.2646 0.12215 0.11995 -0.0709 0.0014 1.0000
16.750 1.2485 0.13123 0.12916 -0.0762 0.0014 1.0000
|
Polar data table (+)
Polar graphs
<< Back to SA7025 (sa7025-il)