SA7026 (sa7026-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: SA7026 (sa7026-il) Reynolds number: 100,000 Max Cl/Cd: 61.89 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sa7026-il-100000-n5.txt Download as CSV file: xf-sa7026-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SA7026
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2769 0.09930 0.09499 -0.0343 1.0000 0.0476
-8.750 -0.2812 0.09707 0.09281 -0.0330 1.0000 0.0482
-8.500 -0.2867 0.09485 0.09064 -0.0316 1.0000 0.0488
-8.250 -0.2845 0.09142 0.08724 -0.0326 0.9980 0.0497
-8.000 -0.2766 0.08712 0.08295 -0.0356 0.9945 0.0504
-7.750 -0.2703 0.08288 0.07872 -0.0384 0.9903 0.0510
-7.500 -0.2632 0.07847 0.07432 -0.0416 0.9859 0.0512
-7.250 -0.2567 0.07396 0.06982 -0.0450 0.9814 0.0510
-7.000 -0.2534 0.06964 0.06552 -0.0480 0.9751 0.0501
-6.500 -0.3160 0.07148 0.06706 -0.0581 0.9733 0.0311
-6.250 -0.2983 0.06706 0.06260 -0.0621 0.9685 0.0290
-6.000 -0.2797 0.06161 0.05706 -0.0682 0.9613 0.0271
-5.750 -0.2504 0.05373 0.04894 -0.0777 0.9566 0.0246
-5.250 -0.1980 0.04150 0.03575 -0.0870 0.9444 0.0215
-5.000 -0.1757 0.03761 0.03146 -0.0888 0.9386 0.0212
-4.750 -0.1476 0.03436 0.02765 -0.0906 0.9336 0.0216
-4.500 -0.1171 0.03078 0.02363 -0.0932 0.9305 0.0233
-4.250 -0.0921 0.02883 0.02130 -0.0935 0.9250 0.0244
-4.000 -0.0624 0.02658 0.01857 -0.0941 0.9204 0.0246
-3.750 -0.0282 0.02459 0.01616 -0.0953 0.9175 0.0247
-3.500 0.0019 0.02311 0.01439 -0.0957 0.9133 0.0251
-3.250 0.0286 0.02193 0.01301 -0.0953 0.9075 0.0257
-3.000 0.0614 0.02083 0.01175 -0.0961 0.9039 0.0266
-2.750 0.0897 0.02000 0.01075 -0.0961 0.8987 0.0280
-2.500 0.1174 0.01936 0.00994 -0.0960 0.8928 0.0300
-2.250 0.1509 0.01865 0.00908 -0.0969 0.8892 0.0342
-2.000 0.1755 0.01808 0.00856 -0.0962 0.8822 0.0552
-1.750 0.2033 0.01661 0.00828 -0.0970 0.8775 0.3151
-1.500 0.2316 0.01557 0.00817 -0.0969 0.8741 0.5874
-1.250 0.2488 0.01492 0.00819 -0.0936 0.8664 0.8222
-1.000 0.3032 0.01462 0.00773 -0.0985 0.8636 1.0000
-0.750 0.3314 0.01464 0.00752 -0.0985 0.8570 1.0000
-0.500 0.3598 0.01464 0.00731 -0.0985 0.8501 1.0000
-0.250 0.3877 0.01465 0.00714 -0.0984 0.8431 1.0000
0.000 0.4162 0.01464 0.00698 -0.0983 0.8361 1.0000
0.250 0.4430 0.01467 0.00688 -0.0980 0.8285 1.0000
0.500 0.4723 0.01463 0.00673 -0.0980 0.8217 1.0000
0.750 0.4979 0.01469 0.00670 -0.0975 0.8130 1.0000
1.000 0.5285 0.01460 0.00653 -0.0977 0.8066 1.0000
1.250 0.5530 0.01467 0.00655 -0.0970 0.7966 1.0000
1.500 0.5804 0.01466 0.00648 -0.0966 0.7877 1.0000
1.750 0.6097 0.01458 0.00634 -0.0966 0.7792 1.0000
2.000 0.6349 0.01462 0.00636 -0.0959 0.7681 1.0000
2.250 0.6613 0.01464 0.00639 -0.0954 0.7573 1.0000
2.500 0.6887 0.01463 0.00636 -0.0950 0.7468 1.0000
2.750 0.7167 0.01461 0.00632 -0.0947 0.7360 1.0000
3.000 0.7440 0.01461 0.00632 -0.0943 0.7239 1.0000
3.250 0.7703 0.01465 0.00641 -0.0938 0.7102 1.0000
3.500 0.7962 0.01471 0.00647 -0.0932 0.6953 1.0000
3.750 0.8215 0.01480 0.00658 -0.0925 0.6786 1.0000
4.000 0.8472 0.01488 0.00668 -0.0918 0.6614 1.0000
4.250 0.8733 0.01498 0.00678 -0.0912 0.6438 1.0000
4.500 0.8988 0.01512 0.00698 -0.0905 0.6252 1.0000
4.750 0.9235 0.01530 0.00718 -0.0897 0.6046 1.0000
5.000 0.9479 0.01552 0.00740 -0.0889 0.5829 1.0000
5.250 0.9717 0.01577 0.00764 -0.0879 0.5592 1.0000
5.500 0.9946 0.01608 0.00799 -0.0869 0.5334 1.0000
5.750 1.0169 0.01643 0.00833 -0.0858 0.5066 1.0000
6.000 1.0385 0.01684 0.00873 -0.0846 0.4796 1.0000
6.250 1.0593 0.01730 0.00918 -0.0833 0.4521 1.0000
6.500 1.0793 0.01782 0.00967 -0.0819 0.4236 1.0000
6.750 1.0980 0.01840 0.01021 -0.0803 0.3933 1.0000
7.000 1.1156 0.01904 0.01087 -0.0787 0.3608 1.0000
7.250 1.1322 0.01974 0.01153 -0.0769 0.3278 1.0000
7.500 1.1478 0.02051 0.01224 -0.0750 0.2963 1.0000
7.750 1.1622 0.02135 0.01303 -0.0731 0.2615 1.0000
8.000 1.1716 0.02248 0.01391 -0.0706 0.2133 1.0000
8.250 1.1784 0.02388 0.01492 -0.0679 0.1554 1.0000
8.500 1.1834 0.02544 0.01608 -0.0651 0.1026 1.0000
8.750 1.1875 0.02714 0.01743 -0.0623 0.0596 1.0000
9.000 1.1928 0.02881 0.01903 -0.0595 0.0366 1.0000
9.250 1.1964 0.03065 0.02084 -0.0566 0.0254 1.0000
9.500 1.2023 0.03230 0.02265 -0.0540 0.0214 1.0000
9.750 1.2068 0.03405 0.02456 -0.0515 0.0190 1.0000
10.000 1.2087 0.03603 0.02669 -0.0490 0.0176 1.0000
10.250 1.2075 0.03834 0.02915 -0.0464 0.0166 1.0000
10.500 1.2101 0.04040 0.03142 -0.0444 0.0161 1.0000
10.750 1.2124 0.04261 0.03384 -0.0424 0.0155 1.0000
11.000 1.2154 0.04487 0.03630 -0.0408 0.0148 1.0000
11.250 1.2185 0.04722 0.03883 -0.0393 0.0137 1.0000
11.500 1.2214 0.04965 0.04144 -0.0381 0.0130 1.0000
11.750 1.2232 0.05224 0.04419 -0.0370 0.0122 1.0000
12.000 1.2240 0.05503 0.04715 -0.0362 0.0117 1.0000
12.250 1.2235 0.05812 0.05040 -0.0354 0.0113 1.0000
12.500 1.2229 0.06139 0.05393 -0.0348 0.0111 1.0000
12.750 1.2211 0.06498 0.05772 -0.0344 0.0110 1.0000
13.000 1.2174 0.06896 0.06192 -0.0342 0.0108 1.0000
13.250 1.2119 0.07326 0.06646 -0.0344 0.0107 1.0000
13.500 1.2045 0.07792 0.07136 -0.0351 0.0107 1.0000
13.750 1.1943 0.08310 0.07679 -0.0363 0.0106 1.0000
14.000 1.1841 0.08842 0.08235 -0.0380 0.0106 1.0000
14.250 1.1715 0.09444 0.08861 -0.0404 0.0106 1.0000
14.500 1.1594 0.10062 0.09502 -0.0433 0.0106 1.0000
14.750 1.1463 0.10737 0.10198 -0.0469 0.0106 1.0000
15.000 1.1325 0.11470 0.10952 -0.0512 0.0107 1.0000
15.250 1.1188 0.12252 0.11754 -0.0560 0.0108 1.0000
15.500 1.1033 0.13134 0.12655 -0.0617 0.0109 1.0000
15.750 1.0859 0.14162 0.13703 -0.0684 0.0111 1.0000
16.000 1.0609 0.15568 0.15126 -0.0774 0.0115 1.0000
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