SA7026 (sa7026-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: SA7026 (sa7026-il) Reynolds number: 200,000 Max Cl/Cd: 87.48 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sa7026-il-200000.txt Download as CSV file: xf-sa7026-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3777 0.10099 0.09789 -0.0337 1.0000 0.0361
-8.000 -0.3906 0.09961 0.09658 -0.0313 1.0000 0.0361
-7.750 -0.4085 0.09869 0.09573 -0.0288 1.0000 0.0362
-7.500 -0.4098 0.09580 0.09287 -0.0311 0.9983 0.0363
-7.250 -0.4024 0.08870 0.08580 -0.0330 0.9955 0.0373
-7.000 -0.3862 0.08536 0.08242 -0.0328 0.9929 0.0386
-6.750 -0.3672 0.08140 0.07846 -0.0370 0.9882 0.0402
-6.500 -0.3422 0.07652 0.07355 -0.0449 0.9839 0.0422
-6.250 -0.3234 0.07165 0.06865 -0.0523 0.9768 0.0444
-6.000 -0.2739 0.06309 0.05969 -0.0745 0.9701 0.0485
-5.750 -0.2636 0.05647 0.05300 -0.0779 0.9630 0.0496
-5.500 -0.2422 0.05352 0.05013 -0.0788 0.9599 0.0514
-5.250 -0.2104 0.04994 0.04645 -0.0833 0.9574 0.0548
-5.000 -0.1834 0.04492 0.04067 -0.0893 0.9482 0.0624
-4.750 -0.1564 0.04097 0.03691 -0.0915 0.9457 0.0649
-4.500 -0.1163 0.03751 0.03285 -0.0966 0.9433 0.0765
-4.250 -0.1012 0.03509 0.03052 -0.0955 0.9353 0.0789
-4.000 -0.0655 0.03229 0.02737 -0.0985 0.9322 0.0917
-3.750 -0.0160 0.02536 0.01897 -0.0990 0.9306 0.0362
-3.500 0.0079 0.02340 0.01667 -0.0983 0.9241 0.0364
-3.250 0.0419 0.02064 0.01358 -0.0995 0.9208 0.0348
-3.000 0.0811 0.01889 0.01159 -0.1013 0.9186 0.0341
-2.750 0.1201 0.01755 0.01012 -0.1031 0.9167 0.0344
-2.500 0.1434 0.01688 0.00939 -0.1021 0.9095 0.0354
-2.250 0.1775 0.01584 0.00831 -0.1031 0.9057 0.0398
-2.000 0.2140 0.01472 0.00740 -0.1045 0.9030 0.0982
-1.750 0.2338 0.01349 0.00734 -0.1037 0.8954 0.4113
-1.500 0.2594 0.01256 0.00726 -0.1029 0.8909 0.6526
-1.250 0.3196 0.01161 0.00691 -0.1081 0.8906 1.0000
-1.000 0.3480 0.01158 0.00668 -0.1080 0.8846 1.0000
-0.750 0.3756 0.01152 0.00648 -0.1078 0.8779 1.0000
-0.500 0.4087 0.01136 0.00617 -0.1084 0.8742 1.0000
-0.250 0.4311 0.01142 0.00613 -0.1072 0.8650 1.0000
0.000 0.4627 0.01125 0.00583 -0.1075 0.8608 1.0000
0.250 0.4863 0.01128 0.00579 -0.1065 0.8516 1.0000
0.500 0.5173 0.01107 0.00548 -0.1066 0.8467 1.0000
0.750 0.5413 0.01107 0.00543 -0.1056 0.8370 1.0000
1.000 0.5696 0.01095 0.00524 -0.1053 0.8301 1.0000
1.250 0.5962 0.01087 0.00511 -0.1048 0.8216 1.0000
1.500 0.6224 0.01084 0.00504 -0.1041 0.8127 1.0000
1.750 0.6512 0.01070 0.00484 -0.1039 0.8054 1.0000
2.000 0.6765 0.01069 0.00482 -0.1032 0.7946 1.0000
2.250 0.7029 0.01064 0.00476 -0.1026 0.7842 1.0000
2.500 0.7300 0.01057 0.00465 -0.1021 0.7737 1.0000
2.750 0.7573 0.01050 0.00454 -0.1016 0.7626 1.0000
3.000 0.7837 0.01047 0.00452 -0.1010 0.7499 1.0000
3.250 0.8097 0.01049 0.00451 -0.1003 0.7364 1.0000
3.500 0.8358 0.01052 0.00453 -0.0997 0.7221 1.0000
3.750 0.8612 0.01058 0.00459 -0.0990 0.7063 1.0000
4.000 0.8863 0.01067 0.00471 -0.0983 0.6888 1.0000
4.250 0.9115 0.01076 0.00478 -0.0976 0.6701 1.0000
4.500 0.9364 0.01089 0.00487 -0.0968 0.6498 1.0000
4.750 0.9606 0.01105 0.00500 -0.0959 0.6273 1.0000
5.000 0.9844 0.01127 0.00522 -0.0950 0.6038 1.0000
5.250 1.0078 0.01152 0.00543 -0.0940 0.5794 1.0000
5.500 1.0305 0.01182 0.00568 -0.0929 0.5533 1.0000
5.750 1.0524 0.01216 0.00596 -0.0917 0.5251 1.0000
6.000 1.0732 0.01256 0.00630 -0.0904 0.4938 1.0000
6.250 1.0932 0.01301 0.00669 -0.0890 0.4612 1.0000
6.500 1.1126 0.01351 0.00711 -0.0875 0.4298 1.0000
6.750 1.1315 0.01404 0.00758 -0.0860 0.3976 1.0000
7.000 1.1477 0.01468 0.00807 -0.0841 0.3565 1.0000
7.250 1.1615 0.01545 0.00862 -0.0819 0.3073 1.0000
7.500 1.1748 0.01630 0.00928 -0.0797 0.2613 1.0000
7.750 1.1883 0.01718 0.00997 -0.0776 0.2162 1.0000
8.000 1.1996 0.01825 0.01078 -0.0753 0.1677 1.0000
8.250 1.2095 0.01947 0.01173 -0.0729 0.1179 1.0000
8.500 1.2059 0.02164 0.01332 -0.0685 0.0483 1.0000
8.750 1.2041 0.02372 0.01527 -0.0640 0.0287 1.0000
9.000 1.2118 0.02503 0.01667 -0.0612 0.0238 1.0000
9.250 1.2123 0.02687 0.01859 -0.0578 0.0208 1.0000
9.500 1.2191 0.02834 0.02020 -0.0552 0.0197 1.0000
9.750 1.2251 0.02998 0.02197 -0.0526 0.0187 1.0000
10.000 1.2313 0.03175 0.02389 -0.0502 0.0177 1.0000
10.250 1.2387 0.03360 0.02586 -0.0481 0.0170 1.0000
10.500 1.2480 0.03555 0.02792 -0.0462 0.0166 1.0000
10.750 1.2596 0.03765 0.03015 -0.0446 0.0163 1.0000
11.000 1.2732 0.03996 0.03262 -0.0431 0.0160 1.0000
11.250 1.2875 0.04250 0.03538 -0.0418 0.0159 1.0000
11.500 1.2997 0.04546 0.03864 -0.0403 0.0161 1.0000
11.750 1.3071 0.04893 0.04246 -0.0385 0.0164 1.0000
12.000 1.3059 0.05281 0.04672 -0.0364 0.0168 1.0000
12.250 1.2975 0.05705 0.05134 -0.0344 0.0173 1.0000
12.500 1.2849 0.06146 0.05610 -0.0327 0.0178 1.0000
12.750 1.2698 0.06606 0.06100 -0.0316 0.0182 1.0000
13.000 1.2526 0.07105 0.06626 -0.0312 0.0185 1.0000
13.250 1.2342 0.07637 0.07183 -0.0316 0.0188 1.0000
13.500 1.2143 0.08219 0.07788 -0.0328 0.0191 1.0000
13.750 1.1945 0.08831 0.08421 -0.0349 0.0193 1.0000
14.000 1.1742 0.09500 0.09109 -0.0379 0.0195 1.0000
14.250 1.1528 0.10250 0.09877 -0.0420 0.0196 1.0000
14.500 1.1320 0.11058 0.10702 -0.0469 0.0197 1.0000
14.750 1.1111 0.11954 0.11614 -0.0527 0.0198 1.0000
15.000 1.0902 0.12945 0.12617 -0.0595 0.0200 1.0000
15.250 1.0688 0.14056 0.13739 -0.0670 0.0201 1.0000
15.500 1.0481 0.15265 0.14953 -0.0747 0.0205 1.0000
15.750 1.0377 0.16451 0.16146 -0.0812 0.0224 1.0000
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Polar data table (+)
Polar graphs
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