SA7025 (sa7025-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: SA7025 (sa7025-il) Reynolds number: 200,000 Max Cl/Cd: 83.27 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sa7025-il-200000.txt Download as CSV file: xf-sa7025-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3654 0.08796 0.08479 -0.0287 1.0000 0.0345
-7.250 -0.3774 0.08661 0.08351 -0.0258 1.0000 0.0349
-7.000 -0.3919 0.08529 0.08226 -0.0229 1.0000 0.0352
-6.750 -0.3999 0.08333 0.08036 -0.0217 1.0000 0.0357
-6.500 -0.4061 0.08110 0.07818 -0.0210 1.0000 0.0366
-6.250 -0.4102 0.07858 0.07569 -0.0212 1.0000 0.0373
-6.000 -0.4117 0.07580 0.07293 -0.0221 1.0000 0.0381
-5.750 -0.3978 0.07144 0.06855 -0.0283 0.9984 0.0413
-5.500 -0.3419 0.06106 0.05778 -0.0507 0.9919 0.0443
-5.250 -0.3304 0.05846 0.05536 -0.0484 0.9883 0.0468
-5.000 -0.2973 0.05434 0.05114 -0.0540 0.9844 0.0500
-4.750 -0.2472 0.04692 0.04296 -0.0668 0.9778 0.0574
-4.500 -0.2223 0.04297 0.03918 -0.0687 0.9741 0.0596
-4.250 -0.1853 0.03983 0.03588 -0.0729 0.9709 0.0650
-4.000 -0.1523 0.03573 0.03137 -0.0766 0.9648 0.0732
-3.750 -0.1141 0.03286 0.02806 -0.0803 0.9603 0.0856
-3.500 -0.0764 0.03028 0.02546 -0.0833 0.9576 0.0919
-3.250 -0.0265 0.02157 0.01502 -0.0840 0.9561 0.0338
-3.000 0.0047 0.02054 0.01364 -0.0840 0.9491 0.0321
-2.750 0.0431 0.01826 0.01111 -0.0861 0.9461 0.0345
-2.500 0.0850 0.01695 0.00965 -0.0886 0.9436 0.0358
-2.250 0.1148 0.01598 0.00862 -0.0886 0.9365 0.0365
-2.000 0.1549 0.01509 0.00768 -0.0908 0.9326 0.0390
-1.750 0.1993 0.01423 0.00674 -0.0938 0.9300 0.0490
-1.500 0.2270 0.01265 0.00633 -0.0943 0.9225 0.3470
-1.250 0.2540 0.01122 0.00632 -0.0938 0.9178 0.7297
-1.000 0.3098 0.01061 0.00592 -0.0984 0.9166 1.0000
-0.750 0.3385 0.01056 0.00569 -0.0983 0.9075 1.0000
-0.500 0.3752 0.01037 0.00535 -0.0996 0.9024 1.0000
-0.250 0.4022 0.01030 0.00516 -0.0991 0.8924 1.0000
0.000 0.4330 0.01014 0.00490 -0.0992 0.8848 1.0000
0.250 0.4617 0.01000 0.00466 -0.0988 0.8759 1.0000
0.500 0.4882 0.00991 0.00449 -0.0981 0.8653 1.0000
0.750 0.5157 0.00979 0.00430 -0.0976 0.8553 1.0000
1.000 0.5442 0.00964 0.00407 -0.0971 0.8459 1.0000
1.250 0.5704 0.00955 0.00393 -0.0963 0.8335 1.0000
1.500 0.5966 0.00948 0.00380 -0.0956 0.8202 1.0000
1.750 0.6231 0.00942 0.00368 -0.0948 0.8061 1.0000
2.000 0.6495 0.00938 0.00358 -0.0941 0.7909 1.0000
2.250 0.6753 0.00938 0.00357 -0.0934 0.7732 1.0000
2.500 0.7015 0.00941 0.00353 -0.0927 0.7552 1.0000
2.750 0.7279 0.00946 0.00350 -0.0920 0.7368 1.0000
3.000 0.7536 0.00956 0.00355 -0.0913 0.7157 1.0000
3.250 0.7795 0.00969 0.00361 -0.0906 0.6947 1.0000
3.500 0.8047 0.00986 0.00372 -0.0899 0.6711 1.0000
3.750 0.8298 0.01007 0.00385 -0.0892 0.6475 1.0000
4.000 0.8547 0.01031 0.00401 -0.0884 0.6236 1.0000
4.250 0.8792 0.01057 0.00419 -0.0876 0.5987 1.0000
4.500 0.9035 0.01085 0.00445 -0.0868 0.5727 1.0000
4.750 0.9273 0.01115 0.00469 -0.0860 0.5458 1.0000
5.000 0.9509 0.01148 0.00496 -0.0851 0.5184 1.0000
5.250 0.9743 0.01184 0.00526 -0.0843 0.4911 1.0000
5.500 0.9973 0.01223 0.00562 -0.0834 0.4635 1.0000
5.750 1.0200 0.01264 0.00598 -0.0824 0.4352 1.0000
6.000 1.0422 0.01308 0.00637 -0.0815 0.4060 1.0000
6.250 1.0637 0.01358 0.00679 -0.0804 0.3752 1.0000
6.500 1.0850 0.01409 0.00725 -0.0793 0.3431 1.0000
6.750 1.1052 0.01466 0.00776 -0.0782 0.3079 1.0000
7.000 1.1236 0.01537 0.00827 -0.0768 0.2626 1.0000
7.250 1.1419 0.01613 0.00885 -0.0755 0.2168 1.0000
7.500 1.1606 0.01693 0.00953 -0.0743 0.1809 1.0000
7.750 1.1777 0.01790 0.01028 -0.0729 0.1358 1.0000
8.000 1.1922 0.01917 0.01127 -0.0713 0.0860 1.0000
8.250 1.1939 0.02195 0.01356 -0.0675 0.0290 1.0000
8.500 1.2025 0.02372 0.01541 -0.0647 0.0224 1.0000
8.750 1.2159 0.02493 0.01680 -0.0626 0.0195 1.0000
9.000 1.2259 0.02633 0.01833 -0.0600 0.0179 1.0000
9.250 1.2333 0.02783 0.01994 -0.0572 0.0170 1.0000
9.500 1.2394 0.02959 0.02179 -0.0543 0.0161 1.0000
9.750 1.2463 0.03167 0.02398 -0.0518 0.0155 1.0000
10.000 1.2567 0.03439 0.02683 -0.0498 0.0150 1.0000
10.250 1.2726 0.03751 0.03014 -0.0485 0.0148 1.0000
10.500 1.2878 0.04086 0.03376 -0.0473 0.0147 1.0000
10.750 1.2976 0.04363 0.03680 -0.0455 0.0148 1.0000
11.000 1.3027 0.04640 0.03984 -0.0433 0.0149 1.0000
11.250 1.3049 0.04884 0.04254 -0.0409 0.0150 1.0000
11.500 1.3031 0.05151 0.04549 -0.0385 0.0153 1.0000
11.750 1.2973 0.05449 0.04883 -0.0362 0.0155 1.0000
12.000 1.2857 0.05826 0.05297 -0.0341 0.0160 1.0000
12.250 1.2697 0.06302 0.05811 -0.0327 0.0166 1.0000
12.500 1.2463 0.06849 0.06395 -0.0324 0.0171 1.0000
12.750 1.2237 0.07438 0.07008 -0.0334 0.0174 1.0000
13.000 1.2015 0.08070 0.07666 -0.0355 0.0177 1.0000
13.250 1.1794 0.08767 0.08386 -0.0388 0.0180 1.0000
13.500 1.1573 0.09531 0.09169 -0.0432 0.0181 1.0000
13.750 1.1355 0.10370 0.10026 -0.0486 0.0182 1.0000
14.000 1.1131 0.11325 0.10997 -0.0552 0.0183 1.0000
14.250 1.0898 0.12418 0.12103 -0.0628 0.0184 1.0000
14.500 1.0637 0.13753 0.13448 -0.0717 0.0187 1.0000
|
Polar data table (+)
Polar graphs
<< Back to SA7025 (sa7025-il)