SA7025 (sa7025-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: SA7025 (sa7025-il) Reynolds number: 50,000 Max Cl/Cd: 38.07 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sa7025-il-50000.txt Download as CSV file: xf-sa7025-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: SA7025
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3759 0.10109 0.09483 -0.0248 1.0000 0.1948
-7.250 -0.3600 0.09650 0.09026 -0.0229 1.0000 0.2064
-7.000 -0.3863 0.09690 0.09087 -0.0221 1.0000 0.2090
-6.750 -0.3748 0.09290 0.08690 -0.0192 1.0000 0.2211
-6.500 -0.3731 0.08997 0.08405 -0.0172 1.0000 0.2305
-6.250 -0.3957 0.08990 0.08414 -0.0184 1.0000 0.2372
-6.000 -0.3911 0.08671 0.08101 -0.0155 1.0000 0.2504
-5.750 -0.3872 0.08362 0.07799 -0.0127 1.0000 0.2620
-5.500 -0.3880 0.08108 0.07552 -0.0110 1.0000 0.2733
-5.250 -0.3899 0.07867 0.07320 -0.0094 1.0000 0.2870
-5.000 -0.3906 0.07628 0.07088 -0.0079 1.0000 0.3019
-4.750 -0.3963 0.07453 0.06920 -0.0089 1.0000 0.3227
-4.500 -0.3912 0.07139 0.06609 -0.0048 1.0000 0.3396
-4.250 -0.3912 0.06918 0.06394 -0.0034 1.0000 0.3657
-4.000 -0.3872 0.06656 0.06138 0.0006 1.0000 0.3899
-3.750 -0.3869 0.06417 0.05907 0.0038 1.0000 0.4227
-3.500 -0.3843 0.06168 0.05665 0.0089 1.0000 0.4535
-3.250 -0.2238 0.04246 0.03500 -0.0519 1.0000 0.1380
-3.000 -0.1916 0.03820 0.03025 -0.0539 1.0000 0.1208
-2.750 -0.1560 0.03465 0.02582 -0.0559 1.0000 0.1097
-2.500 -0.1269 0.03215 0.02287 -0.0565 1.0000 0.1082
-2.250 -0.0978 0.03027 0.02040 -0.0567 1.0000 0.1104
-2.000 -0.0715 0.02847 0.01838 -0.0567 1.0000 0.1151
-1.750 -0.0452 0.02705 0.01664 -0.0562 1.0000 0.1199
-1.500 -0.0198 0.02581 0.01515 -0.0554 1.0000 0.1280
-1.250 0.0059 0.02484 0.01405 -0.0548 1.0000 0.1532
-1.000 0.0384 0.02050 0.01280 -0.0541 1.0000 0.6479
-0.750 0.0543 0.01998 0.01194 -0.0516 1.0000 1.0000
-0.500 0.0760 0.02043 0.01186 -0.0513 1.0000 1.0000
-0.250 0.0968 0.02093 0.01193 -0.0510 1.0000 1.0000
0.000 0.1170 0.02148 0.01215 -0.0508 1.0000 1.0000
0.250 0.1367 0.02208 0.01248 -0.0506 1.0000 1.0000
0.500 0.1559 0.02274 0.01290 -0.0504 1.0000 1.0000
0.750 0.1746 0.02345 0.01341 -0.0502 1.0000 1.0000
1.000 0.1928 0.02423 0.01400 -0.0502 1.0000 1.0000
1.250 0.2153 0.02516 0.01477 -0.0510 0.9976 1.0000
1.500 0.2682 0.02670 0.01611 -0.0574 0.9802 1.0000
1.750 0.3162 0.02800 0.01726 -0.0626 0.9619 1.0000
2.000 0.3659 0.02925 0.01841 -0.0678 0.9441 1.0000
2.250 0.4072 0.03024 0.01935 -0.0713 0.9248 1.0000
2.500 0.4494 0.03115 0.02025 -0.0748 0.9059 1.0000
2.750 0.4975 0.03197 0.02107 -0.0788 0.8879 1.0000
3.000 0.5299 0.03265 0.02179 -0.0802 0.8674 1.0000
3.250 0.5738 0.03319 0.02243 -0.0831 0.8486 1.0000
3.500 0.6115 0.03365 0.02297 -0.0848 0.8289 1.0000
3.750 0.6509 0.03394 0.02337 -0.0865 0.8090 1.0000
4.000 0.7032 0.03370 0.02331 -0.0894 0.7914 1.0000
4.250 0.7319 0.03398 0.02377 -0.0891 0.7692 1.0000
4.500 0.7842 0.03319 0.02321 -0.0910 0.7514 1.0000
4.750 0.8175 0.03301 0.02320 -0.0905 0.7298 1.0000
5.000 0.8655 0.03184 0.02234 -0.0910 0.7106 1.0000
5.250 0.9003 0.03131 0.02201 -0.0900 0.6875 1.0000
5.500 0.9442 0.03008 0.02099 -0.0894 0.6648 1.0000
5.750 0.9838 0.02909 0.02017 -0.0883 0.6392 1.0000
6.000 1.0136 0.02880 0.02009 -0.0865 0.6101 1.0000
6.250 1.0399 0.02881 0.02022 -0.0845 0.5785 1.0000
6.500 1.0678 0.02876 0.02023 -0.0824 0.5454 1.0000
6.750 1.0931 0.02896 0.02046 -0.0803 0.5107 1.0000
7.000 1.1166 0.02933 0.02090 -0.0781 0.4742 1.0000
7.250 1.1365 0.02999 0.02158 -0.0756 0.4362 1.0000
7.500 1.1559 0.03071 0.02226 -0.0731 0.3965 1.0000
7.750 1.1729 0.03157 0.02303 -0.0704 0.3549 1.0000
8.000 1.1872 0.03260 0.02394 -0.0676 0.3117 1.0000
8.250 1.1993 0.03392 0.02506 -0.0646 0.2674 1.0000
8.500 1.2090 0.03554 0.02634 -0.0615 0.2224 1.0000
8.750 1.2139 0.03766 0.02828 -0.0581 0.1799 1.0000
9.000 1.2215 0.04035 0.03068 -0.0551 0.1417 1.0000
9.250 1.2256 0.04304 0.03335 -0.0521 0.1139 1.0000
9.500 1.2323 0.04590 0.03638 -0.0495 0.0948 1.0000
9.750 1.2476 0.04984 0.04058 -0.0479 0.0844 1.0000
10.000 1.2668 0.05424 0.04496 -0.0471 0.0770 1.0000
10.250 1.2659 0.05800 0.04941 -0.0442 0.0746 1.0000
10.500 1.2620 0.06197 0.05389 -0.0414 0.0724 1.0000
10.750 1.2550 0.06589 0.05821 -0.0389 0.0709 1.0000
11.000 1.2420 0.06977 0.06242 -0.0362 0.0703 1.0000
11.250 1.2234 0.07388 0.06684 -0.0338 0.0705 1.0000
11.500 1.2007 0.07851 0.07174 -0.0325 0.0713 1.0000
11.750 1.1765 0.08375 0.07723 -0.0325 0.0724 1.0000
12.000 1.1525 0.08967 0.08334 -0.0338 0.0737 1.0000
12.250 1.1307 0.09611 0.08992 -0.0361 0.0750 1.0000
12.500 1.1111 0.10306 0.09696 -0.0392 0.0761 1.0000
12.750 1.0946 0.11039 0.10435 -0.0427 0.0769 1.0000
13.000 1.0070 0.13752 0.13139 -0.0653 0.0995 1.0000
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Polar data table (+)
Polar graphs
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