SA7026 (sa7026-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: SA7026 (sa7026-il) Reynolds number: 500,000 Max Cl/Cd: 106.44 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sa7026-il-500000-n5.txt Download as CSV file: xf-sa7026-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3306 0.11356 0.11124 -0.0388 1.0000 0.0090
-10.250 -0.3276 0.11054 0.10825 -0.0393 1.0000 0.0090
-10.000 -0.3264 0.10725 0.10499 -0.0398 1.0000 0.0091
-9.500 -0.3115 0.09988 0.09762 -0.0441 0.9911 0.0091
-9.250 -0.3003 0.09553 0.09328 -0.0478 0.9870 0.0091
-9.000 -0.2878 0.09110 0.08885 -0.0519 0.9835 0.0091
-8.750 -0.2753 0.08679 0.08454 -0.0561 0.9789 0.0091
-8.500 -0.2695 0.08056 0.07833 -0.0616 0.9734 0.0095
-8.250 -0.2559 0.07651 0.07427 -0.0663 0.9680 0.0098
-8.000 -0.2420 0.07219 0.06995 -0.0715 0.9601 0.0099
-7.750 -0.2261 0.07008 0.06782 -0.0743 0.9526 0.0108
-7.500 -0.2191 0.06665 0.06438 -0.0777 0.9410 0.0113
-7.250 -0.2138 0.06293 0.06063 -0.0815 0.9299 0.0119
-7.000 -0.2075 0.05868 0.05634 -0.0859 0.9194 0.0124
-6.750 -0.1990 0.05365 0.05125 -0.0910 0.9105 0.0127
-6.500 -0.1790 0.04756 0.04499 -0.0968 0.9028 0.0143
-6.000 -0.1627 0.03335 0.03022 -0.1022 0.8882 0.0087
-5.750 -0.1473 0.02821 0.02470 -0.1033 0.8817 0.0082
-5.500 -0.1284 0.02400 0.02004 -0.1035 0.8765 0.0079
-5.250 -0.1070 0.02055 0.01612 -0.1033 0.8715 0.0076
-5.000 -0.0835 0.01796 0.01310 -0.1029 0.8662 0.0075
-4.750 -0.0587 0.01605 0.01082 -0.1025 0.8616 0.0075
-4.500 -0.0330 0.01460 0.00906 -0.1021 0.8561 0.0075
-4.250 -0.0069 0.01346 0.00768 -0.1017 0.8506 0.0077
-4.000 0.0196 0.01254 0.00658 -0.1014 0.8458 0.0080
-3.750 0.0463 0.01182 0.00573 -0.1011 0.8401 0.0084
-3.500 0.0730 0.01124 0.00503 -0.1009 0.8351 0.0087
-3.250 0.1001 0.01079 0.00449 -0.1007 0.8297 0.0090
-3.000 0.1268 0.01023 0.00383 -0.1005 0.8238 0.0095
-2.750 0.1535 0.00969 0.00320 -0.1003 0.8182 0.0106
-2.500 0.1809 0.00937 0.00282 -0.1001 0.8111 0.0108
-2.250 0.2083 0.00913 0.00248 -0.0999 0.8045 0.0109
-2.000 0.2358 0.00892 0.00220 -0.0998 0.7971 0.0112
-1.750 0.2635 0.00877 0.00195 -0.0997 0.7904 0.0116
-1.500 0.2911 0.00864 0.00176 -0.0996 0.7828 0.0123
-1.250 0.3188 0.00853 0.00160 -0.0995 0.7756 0.0141
-1.000 0.3457 0.00814 0.00146 -0.0994 0.7676 0.0938
-0.750 0.3723 0.00777 0.00138 -0.0994 0.7591 0.2016
-0.500 0.3977 0.00718 0.00138 -0.0993 0.7496 0.4028
-0.250 0.4219 0.00664 0.00143 -0.0988 0.7389 0.6066
0.000 0.4475 0.00645 0.00143 -0.0983 0.7284 0.6879
0.250 0.4712 0.00621 0.00145 -0.0973 0.7182 0.7883
0.500 0.4960 0.00595 0.00146 -0.0962 0.7078 0.9236
0.750 0.5392 0.00596 0.00141 -0.0995 0.6958 1.0000
1.000 0.5657 0.00605 0.00142 -0.0992 0.6829 1.0000
1.500 0.6182 0.00627 0.00147 -0.0986 0.6523 1.0000
1.750 0.6441 0.00641 0.00151 -0.0982 0.6345 1.0000
2.000 0.6699 0.00656 0.00158 -0.0978 0.6165 1.0000
2.250 0.6957 0.00673 0.00165 -0.0974 0.5990 1.0000
2.500 0.7214 0.00689 0.00174 -0.0970 0.5804 1.0000
2.750 0.7469 0.00707 0.00184 -0.0966 0.5607 1.0000
3.000 0.7721 0.00727 0.00197 -0.0962 0.5406 1.0000
3.250 0.7972 0.00749 0.00210 -0.0957 0.5198 1.0000
3.500 0.8219 0.00774 0.00225 -0.0952 0.4970 1.0000
3.750 0.8461 0.00802 0.00242 -0.0946 0.4710 1.0000
4.000 0.8702 0.00831 0.00261 -0.0940 0.4457 1.0000
4.250 0.8946 0.00858 0.00282 -0.0934 0.4228 1.0000
4.500 0.9189 0.00886 0.00303 -0.0929 0.4016 1.0000
4.750 0.9428 0.00917 0.00326 -0.0923 0.3791 1.0000
5.000 0.9648 0.00962 0.00354 -0.0914 0.3410 1.0000
5.250 0.9835 0.01035 0.00393 -0.0901 0.2797 1.0000
5.500 1.0046 0.01089 0.00430 -0.0891 0.2404 1.0000
5.750 1.0259 0.01141 0.00467 -0.0882 0.2053 1.0000
6.000 1.0466 0.01198 0.00507 -0.0871 0.1718 1.0000
6.250 1.0644 0.01279 0.00559 -0.0858 0.1212 1.0000
6.500 1.0822 0.01359 0.00615 -0.0843 0.0802 1.0000
6.750 1.0997 0.01441 0.00679 -0.0828 0.0457 1.0000
7.250 1.1338 0.01604 0.00819 -0.0796 0.0057 1.0000
7.500 1.1541 0.01654 0.00873 -0.0785 0.0049 1.0000
7.750 1.1737 0.01707 0.00933 -0.0773 0.0044 1.0000
8.000 1.1924 0.01764 0.00999 -0.0759 0.0041 1.0000
8.250 1.2093 0.01829 0.01074 -0.0742 0.0038 1.0000
8.500 1.2250 0.01891 0.01148 -0.0722 0.0037 1.0000
8.750 1.2395 0.01960 0.01226 -0.0702 0.0037 1.0000
9.000 1.2528 0.02037 0.01313 -0.0680 0.0035 1.0000
9.250 1.2648 0.02123 0.01409 -0.0658 0.0034 1.0000
9.500 1.2762 0.02215 0.01510 -0.0635 0.0034 1.0000
9.750 1.2860 0.02319 0.01624 -0.0611 0.0033 1.0000
10.000 1.2951 0.02429 0.01746 -0.0588 0.0033 1.0000
10.250 1.3019 0.02560 0.01888 -0.0563 0.0032 1.0000
10.500 1.3092 0.02690 0.02030 -0.0540 0.0032 1.0000
10.750 1.3150 0.02838 0.02189 -0.0517 0.0032 1.0000
11.000 1.3201 0.02996 0.02362 -0.0496 0.0032 1.0000
11.250 1.3236 0.03177 0.02557 -0.0474 0.0031 1.0000
11.500 1.3276 0.03360 0.02753 -0.0454 0.0031 1.0000
11.750 1.3305 0.03562 0.02969 -0.0436 0.0031 1.0000
12.000 1.3333 0.03773 0.03194 -0.0419 0.0031 1.0000
12.250 1.3348 0.04007 0.03443 -0.0404 0.0031 1.0000
12.500 1.3368 0.04239 0.03690 -0.0392 0.0031 1.0000
12.750 1.3368 0.04506 0.03973 -0.0380 0.0031 1.0000
13.000 1.3361 0.04786 0.04269 -0.0371 0.0030 1.0000
13.250 1.3345 0.05085 0.04584 -0.0364 0.0030 1.0000
13.500 1.3339 0.05376 0.04889 -0.0362 0.0028 1.0000
13.750 1.3260 0.05791 0.05326 -0.0359 0.0029 1.0000
14.000 1.3240 0.06125 0.05673 -0.0363 0.0028 1.0000
14.250 1.3175 0.06550 0.06115 -0.0370 0.0027 1.0000
14.500 1.3121 0.06973 0.06552 -0.0381 0.0027 1.0000
14.750 1.3025 0.07491 0.07089 -0.0396 0.0027 1.0000
15.000 1.2942 0.08011 0.07624 -0.0416 0.0026 1.0000
15.250 1.2824 0.08618 0.08250 -0.0440 0.0026 1.0000
15.500 1.2695 0.09280 0.08931 -0.0470 0.0026 1.0000
15.750 1.2568 0.09969 0.09637 -0.0505 0.0027 1.0000
16.000 1.2435 0.10699 0.10383 -0.0544 0.0026 1.0000
16.250 1.2292 0.11479 0.11180 -0.0587 0.0026 1.0000
16.500 1.2140 0.12318 0.12035 -0.0635 0.0027 1.0000
16.750 1.1984 0.13198 0.12931 -0.0687 0.0027 1.0000
17.000 1.1810 0.14166 0.13915 -0.0745 0.0027 1.0000
17.250 1.1668 0.15087 0.14850 -0.0802 0.0027 1.0000
17.500 1.1496 0.16146 0.15922 -0.0866 0.0028 1.0000
17.750 1.1312 0.17306 0.17094 -0.0936 0.0028 1.0000
18.000 1.1045 0.18874 0.18676 -0.1024 0.0030 1.0000
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Polar data table (+)
Polar graphs
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