SA7026 (sa7026-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: SA7026 (sa7026-il) Reynolds number: 1,000,000 Max Cl/Cd: 143.09 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sa7026-il-1000000.txt Download as CSV file: xf-sa7026-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.3723 0.14212 0.14037 -0.0284 1.0000 0.0057
-12.500 -0.3666 0.13892 0.13718 -0.0295 1.0000 0.0060
-8.500 -0.2725 0.07967 0.07811 -0.0608 0.9828 0.0080
-8.250 -0.2552 0.07668 0.07512 -0.0648 0.9786 0.0084
-8.000 -0.2371 0.07212 0.07054 -0.0712 0.9735 0.0085
-7.750 -0.2203 0.06820 0.06661 -0.0768 0.9652 0.0091
-7.500 -0.2148 0.06420 0.06258 -0.0810 0.9516 0.0092
-7.250 -0.2104 0.06025 0.05859 -0.0850 0.9394 0.0094
-7.000 -0.2050 0.05592 0.05420 -0.0892 0.9289 0.0096
-6.750 -0.1975 0.05085 0.04906 -0.0939 0.9193 0.0099
-6.500 -0.1867 0.04536 0.04345 -0.0981 0.9112 0.0101
-6.250 -0.1722 0.03959 0.03750 -0.1012 0.9042 0.0108
-6.000 -0.1505 0.03547 0.03318 -0.1023 0.8987 0.0114
-5.750 -0.1332 0.03134 0.02875 -0.1032 0.8924 0.0115
-5.500 -0.1238 0.02390 0.02069 -0.1041 0.8859 0.0120
-5.250 -0.1038 0.02099 0.01752 -0.1042 0.8802 0.0126
-5.000 -0.0801 0.01956 0.01593 -0.1042 0.8755 0.0131
-4.750 -0.0554 0.01820 0.01440 -0.1041 0.8708 0.0138
-4.500 -0.0298 0.01687 0.01286 -0.1039 0.8658 0.0150
-4.250 -0.0027 0.01625 0.01205 -0.1036 0.8614 0.0166
-4.000 0.0224 0.01214 0.00730 -0.1024 0.8564 0.0122
-3.750 0.0488 0.01062 0.00563 -0.1019 0.8512 0.0106
-3.500 0.0757 0.00988 0.00474 -0.1015 0.8462 0.0110
-3.250 0.1031 0.00941 0.00422 -0.1013 0.8402 0.0114
-3.000 0.1304 0.00902 0.00375 -0.1011 0.8345 0.0116
-2.750 0.1571 0.00833 0.00296 -0.1009 0.8290 0.0118
-2.500 0.1843 0.00781 0.00234 -0.1007 0.8231 0.0124
-2.250 0.2120 0.00753 0.00197 -0.1006 0.8177 0.0126
-2.000 0.2400 0.00729 0.00167 -0.1005 0.8113 0.0129
-1.750 0.2678 0.00713 0.00142 -0.1004 0.8053 0.0139
-1.500 0.2959 0.00697 0.00124 -0.1003 0.7982 0.0183
-1.250 0.3225 0.00648 0.00109 -0.1003 0.7909 0.1342
-1.000 0.3495 0.00608 0.00102 -0.1003 0.7825 0.2501
-0.750 0.3761 0.00570 0.00100 -0.1003 0.7750 0.3870
-0.500 0.4024 0.00534 0.00101 -0.1002 0.7667 0.5254
-0.250 0.4277 0.00495 0.00104 -0.0998 0.7585 0.6843
0.000 0.4500 0.00457 0.00108 -0.0985 0.7500 0.8416
0.250 0.4887 0.00432 0.00106 -0.1005 0.7409 0.9862
0.500 0.5203 0.00437 0.00104 -0.1014 0.7310 1.0000
0.750 0.5471 0.00444 0.00104 -0.1011 0.7197 1.0000
1.000 0.5738 0.00453 0.00105 -0.1009 0.7073 1.0000
1.250 0.6006 0.00461 0.00106 -0.1007 0.6943 1.0000
1.500 0.6274 0.00470 0.00109 -0.1004 0.6808 1.0000
2.000 0.6807 0.00491 0.00117 -0.1000 0.6517 1.0000
2.250 0.7073 0.00503 0.00123 -0.0997 0.6361 1.0000
2.500 0.7337 0.00516 0.00130 -0.0995 0.6193 1.0000
2.750 0.7598 0.00531 0.00138 -0.0992 0.6006 1.0000
3.000 0.7856 0.00550 0.00148 -0.0988 0.5782 1.0000
3.250 0.8109 0.00571 0.00158 -0.0984 0.5534 1.0000
3.500 0.8366 0.00590 0.00170 -0.0980 0.5312 1.0000
3.750 0.8620 0.00612 0.00183 -0.0976 0.5086 1.0000
4.000 0.8873 0.00635 0.00199 -0.0972 0.4863 1.0000
4.250 0.9125 0.00659 0.00214 -0.0968 0.4628 1.0000
4.500 0.9372 0.00685 0.00232 -0.0964 0.4373 1.0000
4.750 0.9607 0.00722 0.00253 -0.0957 0.4019 1.0000
5.000 0.9840 0.00761 0.00277 -0.0950 0.3642 1.0000
5.250 1.0070 0.00802 0.00302 -0.0943 0.3283 1.0000
5.500 1.0292 0.00850 0.00330 -0.0935 0.2889 1.0000
5.750 1.0505 0.00905 0.00363 -0.0925 0.2431 1.0000
6.000 1.0721 0.00958 0.00398 -0.0916 0.2059 1.0000
6.250 1.0927 0.01017 0.00437 -0.0906 0.1657 1.0000
6.500 1.1124 0.01084 0.00481 -0.0894 0.1236 1.0000
6.750 1.1310 0.01159 0.00532 -0.0881 0.0820 1.0000
7.000 1.1475 0.01252 0.00597 -0.0864 0.0390 1.0000
7.250 1.1632 0.01351 0.00675 -0.0845 0.0085 1.0000
7.500 1.1841 0.01403 0.00730 -0.0834 0.0061 1.0000
7.750 1.2053 0.01449 0.00782 -0.0824 0.0056 1.0000
8.000 1.2253 0.01504 0.00844 -0.0811 0.0051 1.0000
8.250 1.2447 0.01561 0.00908 -0.0798 0.0048 1.0000
8.500 1.2631 0.01622 0.00976 -0.0783 0.0047 1.0000
8.750 1.2802 0.01689 0.01050 -0.0766 0.0046 1.0000
9.000 1.2946 0.01760 0.01131 -0.0744 0.0046 1.0000
9.250 1.3065 0.01837 0.01217 -0.0719 0.0044 1.0000
9.500 1.3175 0.01920 0.01309 -0.0692 0.0044 1.0000
9.750 1.3274 0.02011 0.01408 -0.0666 0.0042 1.0000
10.000 1.3353 0.02118 0.01523 -0.0638 0.0041 1.0000
10.250 1.3421 0.02235 0.01651 -0.0610 0.0040 1.0000
10.500 1.3491 0.02356 0.01781 -0.0584 0.0040 1.0000
10.750 1.3544 0.02495 0.01930 -0.0557 0.0039 1.0000
11.000 1.3585 0.02652 0.02097 -0.0531 0.0039 1.0000
11.250 1.3621 0.02820 0.02277 -0.0506 0.0038 1.0000
11.500 1.3661 0.02996 0.02463 -0.0483 0.0038 1.0000
11.750 1.3658 0.03229 0.02710 -0.0458 0.0037 1.0000
12.000 1.3721 0.03395 0.02889 -0.0441 0.0038 1.0000
12.250 1.3719 0.03652 0.03161 -0.0421 0.0037 1.0000
12.500 1.3722 0.03914 0.03438 -0.0403 0.0037 1.0000
12.750 1.3734 0.04161 0.03698 -0.0388 0.0037 1.0000
13.000 1.3664 0.04547 0.04107 -0.0371 0.0037 1.0000
13.250 1.3504 0.05083 0.04673 -0.0354 0.0036 1.0000
13.500 1.3448 0.05425 0.05031 -0.0347 0.0036 1.0000
13.750 1.3502 0.05590 0.05200 -0.0346 0.0037 1.0000
14.000 1.3409 0.06010 0.05638 -0.0345 0.0037 1.0000
14.250 1.3122 0.06767 0.06426 -0.0352 0.0036 1.0000
14.500 1.3125 0.07066 0.06733 -0.0361 0.0037 1.0000
14.750 1.2898 0.07791 0.07481 -0.0382 0.0036 1.0000
15.000 1.2880 0.08177 0.07876 -0.0399 0.0037 1.0000
15.250 1.2809 0.08685 0.08396 -0.0423 0.0037 1.0000
15.500 1.2660 0.09376 0.09102 -0.0456 0.0037 1.0000
15.750 1.2518 0.10091 0.09832 -0.0494 0.0037 1.0000
16.000 1.2435 0.10716 0.10469 -0.0531 0.0038 1.0000
16.250 1.2272 0.11547 0.11316 -0.0579 0.0038 1.0000
16.500 1.2146 0.12336 0.12118 -0.0628 0.0038 1.0000
16.750 1.2027 0.13143 0.12937 -0.0678 0.0038 1.0000
17.000 1.1888 0.14042 0.13851 -0.0735 0.0039 1.0000
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