SA7026 (sa7026-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: SA7026 (sa7026-il) Reynolds number: 1,000,000 Max Cl/Cd: 120.7 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sa7026-il-1000000-n5.txt Download as CSV file: xf-sa7026-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2379 0.08342 0.08171 -0.0655 0.9603 0.0045
-8.500 -0.2257 0.07875 0.07702 -0.0704 0.9497 0.0041
-8.250 -0.2195 0.07461 0.07284 -0.0735 0.9370 0.0037
-8.000 -0.2328 0.06799 0.06619 -0.0761 0.9202 0.0032
-7.750 -0.2440 0.06374 0.06192 -0.0770 0.9070 0.0030
-7.500 -0.2469 0.05887 0.05703 -0.0812 0.8964 0.0030
-7.250 -0.2415 0.05420 0.05230 -0.0858 0.8879 0.0029
-7.000 -0.2406 0.04548 0.04347 -0.0935 0.8778 0.0029
-6.750 -0.2592 0.02414 0.02124 -0.1009 0.8664 0.0032
-6.500 -0.2391 0.02151 0.01831 -0.1011 0.8616 0.0033
-6.250 -0.2167 0.01947 0.01599 -0.1012 0.8570 0.0035
-6.000 -0.1931 0.01783 0.01407 -0.1011 0.8520 0.0037
-5.750 -0.1693 0.01607 0.01200 -0.1009 0.8474 0.0039
-5.500 -0.1441 0.01470 0.01038 -0.1007 0.8422 0.0042
-5.250 -0.1186 0.01347 0.00890 -0.1005 0.8364 0.0043
-5.000 -0.0926 0.01246 0.00768 -0.1003 0.8310 0.0045
-4.750 -0.0660 0.01164 0.00670 -0.1001 0.8254 0.0046
-4.500 -0.0390 0.01122 0.00616 -0.1000 0.8203 0.0049
-4.250 -0.0117 0.01070 0.00553 -0.0999 0.8152 0.0051
-4.000 0.0150 0.01001 0.00471 -0.0997 0.8094 0.0051
-3.750 0.0419 0.00941 0.00399 -0.0995 0.8039 0.0051
-3.500 0.0691 0.00892 0.00341 -0.0994 0.7969 0.0052
-3.250 0.0963 0.00853 0.00291 -0.0992 0.7897 0.0052
-3.000 0.1237 0.00814 0.00244 -0.0991 0.7815 0.0053
-2.750 0.1511 0.00774 0.00191 -0.0990 0.7743 0.0059
-2.500 0.1788 0.00754 0.00165 -0.0989 0.7667 0.0069
-2.250 0.2066 0.00740 0.00146 -0.0989 0.7592 0.0079
-1.750 0.2621 0.00712 0.00113 -0.0988 0.7433 0.0229
-1.500 0.2894 0.00690 0.00102 -0.0988 0.7342 0.0647
-1.000 0.3435 0.00646 0.00089 -0.0987 0.7114 0.1976
-0.750 0.3708 0.00629 0.00085 -0.0987 0.7004 0.2620
-0.500 0.3979 0.00614 0.00084 -0.0987 0.6895 0.3302
-0.250 0.4250 0.00603 0.00083 -0.0987 0.6775 0.3899
0.000 0.4519 0.00590 0.00084 -0.0986 0.6650 0.4618
0.250 0.4787 0.00582 0.00086 -0.0985 0.6515 0.5230
0.500 0.5053 0.00576 0.00090 -0.0983 0.6369 0.5811
0.750 0.5314 0.00569 0.00095 -0.0980 0.6203 0.6536
1.000 0.5566 0.00560 0.00101 -0.0976 0.6017 0.7371
1.250 0.5799 0.00547 0.00109 -0.0966 0.5827 0.8365
1.500 0.6107 0.00534 0.00115 -0.0970 0.5626 0.9696
1.750 0.6426 0.00549 0.00120 -0.0981 0.5428 1.0000
2.000 0.6689 0.00565 0.00128 -0.0978 0.5242 1.0000
2.250 0.6950 0.00582 0.00136 -0.0975 0.5055 1.0000
2.500 0.7211 0.00600 0.00145 -0.0973 0.4874 1.0000
2.750 0.7471 0.00619 0.00155 -0.0970 0.4666 1.0000
3.000 0.7725 0.00643 0.00168 -0.0966 0.4412 1.0000
3.250 0.7977 0.00668 0.00183 -0.0962 0.4153 1.0000
3.500 0.8232 0.00691 0.00196 -0.0959 0.3940 1.0000
3.750 0.8488 0.00713 0.00210 -0.0956 0.3752 1.0000
4.000 0.8743 0.00735 0.00225 -0.0952 0.3552 1.0000
4.250 0.8995 0.00761 0.00244 -0.0949 0.3345 1.0000
4.500 0.9246 0.00787 0.00262 -0.0945 0.3140 1.0000
4.750 0.9481 0.00825 0.00285 -0.0939 0.2819 1.0000
5.000 0.9724 0.00857 0.00307 -0.0934 0.2571 1.0000
5.250 0.9962 0.00893 0.00333 -0.0928 0.2311 1.0000
5.500 1.0190 0.00937 0.00362 -0.0921 0.2006 1.0000
5.750 1.0397 0.00999 0.00400 -0.0911 0.1557 1.0000
6.000 1.0619 0.01047 0.00433 -0.0903 0.1275 1.0000
6.250 1.0842 0.01092 0.00468 -0.0895 0.1050 1.0000
6.500 1.1046 0.01154 0.00514 -0.0884 0.0725 1.0000
6.750 1.1243 0.01221 0.00563 -0.0873 0.0442 1.0000
7.000 1.1458 0.01269 0.00605 -0.0864 0.0302 1.0000
7.250 1.1662 0.01326 0.00654 -0.0853 0.0169 1.0000
7.500 1.1856 0.01390 0.00711 -0.0840 0.0058 1.0000
7.750 1.2068 0.01437 0.00760 -0.0830 0.0040 1.0000
8.000 1.2283 0.01478 0.00805 -0.0821 0.0036 1.0000
8.250 1.2490 0.01523 0.00857 -0.0810 0.0031 1.0000
8.500 1.2690 0.01572 0.00910 -0.0799 0.0028 1.0000
8.750 1.2874 0.01630 0.00974 -0.0785 0.0024 1.0000
9.000 1.3035 0.01702 0.01054 -0.0767 0.0021 1.0000
9.250 1.3194 0.01758 0.01116 -0.0748 0.0020 1.0000
9.500 1.3343 0.01815 0.01180 -0.0728 0.0020 1.0000
9.750 1.3488 0.01875 0.01246 -0.0708 0.0019 1.0000
10.000 1.3626 0.01940 0.01318 -0.0687 0.0019 1.0000
10.250 1.3761 0.02008 0.01394 -0.0667 0.0017 1.0000
10.500 1.3870 0.02095 0.01491 -0.0644 0.0017 1.0000
10.750 1.3995 0.02173 0.01576 -0.0625 0.0016 1.0000
11.000 1.4093 0.02270 0.01682 -0.0602 0.0015 1.0000
11.250 1.4200 0.02364 0.01784 -0.0582 0.0014 1.0000
11.500 1.4290 0.02472 0.01901 -0.0561 0.0014 1.0000
11.750 1.4365 0.02594 0.02033 -0.0540 0.0014 1.0000
12.000 1.4462 0.02703 0.02149 -0.0522 0.0012 1.0000
12.250 1.4536 0.02832 0.02287 -0.0504 0.0012 1.0000
12.500 1.4594 0.02980 0.02444 -0.0485 0.0011 1.0000
12.750 1.4635 0.03145 0.02621 -0.0466 0.0011 1.0000
13.000 1.4621 0.03368 0.02856 -0.0446 0.0010 1.0000
13.250 1.4666 0.03545 0.03045 -0.0431 0.0010 1.0000
13.500 1.4648 0.03791 0.03305 -0.0416 0.0010 1.0000
13.750 1.4444 0.04246 0.03783 -0.0396 0.0009 1.0000
14.000 1.4458 0.04491 0.04038 -0.0389 0.0009 1.0000
14.250 1.4316 0.04931 0.04497 -0.0382 0.0009 1.0000
14.500 1.4278 0.05271 0.04852 -0.0381 0.0009 1.0000
14.750 1.4204 0.05679 0.05274 -0.0383 0.0009 1.0000
15.000 1.4172 0.06047 0.05654 -0.0389 0.0009 1.0000
15.250 1.4002 0.06647 0.06273 -0.0403 0.0009 1.0000
15.500 1.3941 0.07113 0.06752 -0.0418 0.0009 1.0000
15.750 1.3828 0.07686 0.07341 -0.0439 0.0009 1.0000
16.000 1.3703 0.08309 0.07979 -0.0464 0.0009 1.0000
16.250 1.3583 0.08951 0.08636 -0.0493 0.0009 1.0000
16.500 1.3433 0.09678 0.09378 -0.0528 0.0009 1.0000
16.750 1.3298 0.10404 0.10119 -0.0565 0.0009 1.0000
17.000 1.3133 0.11213 0.10942 -0.0608 0.0009 1.0000
17.250 1.2960 0.12066 0.11809 -0.0654 0.0009 1.0000
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Polar data table (+)
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