SA7025 (sa7025-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: SA7025 (sa7025-il) Reynolds number: 1,000,000 Max Cl/Cd: 129.74 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sa7025-il-1000000.txt Download as CSV file: xf-sa7025-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3434 0.09401 0.09243 -0.0322 1.0000 0.0076
-8.500 -0.3482 0.09173 0.09019 -0.0310 1.0000 0.0080
-8.250 -0.3463 0.08877 0.08726 -0.0319 0.9992 0.0080
-8.000 -0.3306 0.08422 0.08270 -0.0373 0.9967 0.0084
-7.750 -0.3141 0.07963 0.07811 -0.0432 0.9926 0.0086
-7.500 -0.2960 0.07508 0.07357 -0.0493 0.9880 0.0088
-7.250 -0.2738 0.06961 0.06810 -0.0580 0.9846 0.0089
-7.000 -0.2487 0.06386 0.06233 -0.0676 0.9808 0.0089
-6.750 -0.2241 0.05775 0.05619 -0.0772 0.9742 0.0089
-6.500 -0.2015 0.05087 0.04923 -0.0863 0.9654 0.0089
-6.250 -0.1847 0.04479 0.04302 -0.0914 0.9559 0.0089
-6.000 -0.1837 0.03367 0.03153 -0.0967 0.9432 0.0096
-5.750 -0.1653 0.03205 0.02981 -0.0973 0.9367 0.0101
-5.500 -0.1460 0.02910 0.02666 -0.0977 0.9307 0.0106
-5.250 -0.1247 0.02619 0.02352 -0.0981 0.9248 0.0115
-5.000 -0.1019 0.02327 0.02032 -0.0980 0.9191 0.0125
-4.750 -0.0740 0.02310 0.01997 -0.0973 0.9147 0.0139
-4.500 -0.0549 0.01742 0.01367 -0.0976 0.9083 0.0152
-4.250 -0.0301 0.01627 0.01240 -0.0975 0.9033 0.0162
-4.000 -0.0041 0.01525 0.01123 -0.0973 0.8980 0.0173
-3.750 0.0227 0.01437 0.01019 -0.0970 0.8921 0.0192
-3.500 0.0492 0.01310 0.00861 -0.0967 0.8870 0.0229
-3.250 0.0769 0.00958 0.00469 -0.0953 0.8809 0.0112
-3.000 0.1038 0.00868 0.00365 -0.0949 0.8751 0.0110
-2.750 0.1312 0.00816 0.00305 -0.0946 0.8686 0.0119
-2.500 0.1586 0.00777 0.00257 -0.0944 0.8619 0.0125
-2.250 0.1863 0.00745 0.00218 -0.0942 0.8545 0.0130
-2.000 0.2139 0.00721 0.00186 -0.0940 0.8467 0.0135
-1.750 0.2417 0.00702 0.00162 -0.0939 0.8376 0.0140
-1.500 0.2696 0.00681 0.00131 -0.0937 0.8288 0.0144
-1.250 0.2974 0.00669 0.00109 -0.0935 0.8191 0.0169
-1.000 0.3248 0.00624 0.00095 -0.0935 0.8083 0.1163
-0.750 0.3519 0.00583 0.00089 -0.0936 0.7967 0.2508
-0.500 0.3789 0.00555 0.00086 -0.0935 0.7834 0.3574
-0.250 0.4052 0.00516 0.00088 -0.0934 0.7681 0.5245
0.000 0.4263 0.00437 0.00097 -0.0920 0.7512 0.8382
0.250 0.4590 0.00416 0.00092 -0.0927 0.7328 1.0000
0.500 0.4858 0.00427 0.00092 -0.0924 0.7136 1.0000
1.000 0.5394 0.00451 0.00095 -0.0919 0.6752 1.0000
1.250 0.5662 0.00465 0.00098 -0.0916 0.6552 1.0000
1.500 0.5929 0.00479 0.00102 -0.0914 0.6344 1.0000
1.750 0.6195 0.00495 0.00107 -0.0911 0.6130 1.0000
2.000 0.6462 0.00510 0.00113 -0.0909 0.5912 1.0000
2.500 0.6994 0.00544 0.00129 -0.0905 0.5482 1.0000
2.750 0.7259 0.00562 0.00138 -0.0902 0.5269 1.0000
3.000 0.7525 0.00580 0.00147 -0.0900 0.5051 1.0000
3.250 0.7787 0.00602 0.00160 -0.0897 0.4808 1.0000
3.500 0.8048 0.00624 0.00172 -0.0895 0.4561 1.0000
3.750 0.8310 0.00646 0.00185 -0.0892 0.4333 1.0000
4.000 0.8571 0.00668 0.00200 -0.0890 0.4102 1.0000
4.250 0.8830 0.00693 0.00217 -0.0887 0.3887 1.0000
4.500 0.9090 0.00717 0.00233 -0.0884 0.3656 1.0000
4.750 0.9341 0.00749 0.00253 -0.0881 0.3352 1.0000
5.000 0.9580 0.00795 0.00278 -0.0875 0.2915 1.0000
5.250 0.9822 0.00838 0.00303 -0.0871 0.2535 1.0000
5.500 1.0064 0.00879 0.00331 -0.0866 0.2221 1.0000
5.750 1.0299 0.00930 0.00363 -0.0860 0.1838 1.0000
6.000 1.0531 0.00982 0.00397 -0.0854 0.1474 1.0000
6.250 1.0747 0.01053 0.00441 -0.0846 0.1035 1.0000
6.500 1.0967 0.01117 0.00487 -0.0838 0.0693 1.0000
6.750 1.1164 0.01208 0.00553 -0.0827 0.0277 1.0000
7.000 1.1369 0.01291 0.00621 -0.0816 0.0074 1.0000
7.250 1.1602 0.01339 0.00673 -0.0809 0.0053 1.0000
7.500 1.1834 0.01385 0.00726 -0.0801 0.0049 1.0000
7.750 1.2057 0.01441 0.00789 -0.0792 0.0044 1.0000
8.000 1.2273 0.01502 0.00857 -0.0783 0.0042 1.0000
8.250 1.2482 0.01570 0.00935 -0.0772 0.0040 1.0000
8.500 1.2678 0.01647 0.01022 -0.0759 0.0039 1.0000
8.750 1.2864 0.01731 0.01116 -0.0745 0.0039 1.0000
9.000 1.3039 0.01820 0.01215 -0.0729 0.0039 1.0000
9.250 1.3202 0.01914 0.01320 -0.0712 0.0039 1.0000
9.500 1.3344 0.02021 0.01438 -0.0692 0.0039 1.0000
9.750 1.3471 0.02133 0.01561 -0.0670 0.0039 1.0000
10.000 1.3564 0.02256 0.01695 -0.0643 0.0038 1.0000
10.250 1.3621 0.02385 0.01834 -0.0611 0.0037 1.0000
10.500 1.3652 0.02540 0.02003 -0.0577 0.0037 1.0000
10.750 1.3713 0.02679 0.02153 -0.0549 0.0037 1.0000
11.000 1.3769 0.02831 0.02318 -0.0522 0.0037 1.0000
11.250 1.3816 0.02996 0.02496 -0.0497 0.0037 1.0000
11.500 1.3844 0.03188 0.02702 -0.0472 0.0037 1.0000
11.750 1.3882 0.03375 0.02905 -0.0450 0.0038 1.0000
12.000 1.3886 0.03603 0.03148 -0.0428 0.0038 1.0000
12.250 1.3884 0.03842 0.03403 -0.0409 0.0038 1.0000
12.500 1.3861 0.04110 0.03689 -0.0391 0.0038 1.0000
12.750 1.3763 0.04524 0.04133 -0.0372 0.0040 1.0000
13.000 1.3691 0.04874 0.04501 -0.0362 0.0041 1.0000
13.250 1.3615 0.05232 0.04875 -0.0358 0.0040 1.0000
13.500 1.3216 0.06163 0.05856 -0.0361 0.0045 1.0000
13.750 1.3020 0.06790 0.06505 -0.0378 0.0046 1.0000
14.000 1.2794 0.07520 0.07257 -0.0406 0.0048 1.0000
14.250 1.2567 0.08320 0.08076 -0.0445 0.0049 1.0000
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Polar data table (+)
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