SA7025 (sa7025-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: SA7025 (sa7025-il) Reynolds number: 500,000 Max Cl/Cd: 111.6 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sa7025-il-500000.txt Download as CSV file: xf-sa7025-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3482 0.09124 0.08910 -0.0324 1.0000 0.0138
-8.000 -0.3586 0.08974 0.08766 -0.0298 1.0000 0.0138
-7.750 -0.3717 0.08844 0.08641 -0.0268 1.0000 0.0138
-7.500 -0.3578 0.08417 0.08214 -0.0322 0.9970 0.0139
-7.250 -0.3380 0.07906 0.07703 -0.0399 0.9926 0.0140
-7.000 -0.3140 0.07331 0.07128 -0.0489 0.9880 0.0140
-6.750 -0.2961 0.06432 0.06228 -0.0607 0.9844 0.0148
-6.500 -0.2738 0.06124 0.05917 -0.0651 0.9814 0.0157
-6.250 -0.2472 0.05632 0.05420 -0.0727 0.9766 0.0165
-6.000 -0.2131 0.05041 0.04818 -0.0822 0.9736 0.0177
-5.750 -0.1645 0.04360 0.04110 -0.0925 0.9716 0.0212
-5.500 -0.1342 0.03893 0.03610 -0.0972 0.9670 0.0214
-5.250 -0.1175 0.03173 0.02868 -0.1015 0.9611 0.0236
-5.000 -0.0884 0.02976 0.02659 -0.1036 0.9582 0.0256
-4.750 -0.0636 0.02718 0.02375 -0.1042 0.9525 0.0283
-4.500 -0.0325 0.02732 0.02353 -0.1036 0.9475 0.0316
-4.250 -0.0119 0.02139 0.01716 -0.1049 0.9431 0.0342
-4.000 0.0103 0.01999 0.01568 -0.1042 0.9363 0.0361
-3.750 0.0363 0.01854 0.01400 -0.1038 0.9316 0.0391
-3.500 0.0648 0.01357 0.00819 -0.1016 0.9265 0.0182
-3.250 0.0902 0.01196 0.00634 -0.1005 0.9205 0.0170
-3.000 0.1166 0.01102 0.00527 -0.0998 0.9159 0.0173
-2.750 0.1420 0.01036 0.00453 -0.0990 0.9090 0.0180
-2.500 0.1684 0.00985 0.00394 -0.0984 0.9034 0.0191
-2.250 0.1947 0.00948 0.00352 -0.0979 0.8969 0.0206
-2.000 0.2215 0.00904 0.00299 -0.0974 0.8904 0.0210
-1.750 0.2484 0.00869 0.00252 -0.0969 0.8835 0.0224
-1.500 0.2753 0.00824 0.00215 -0.0964 0.8761 0.0596
-1.250 0.3011 0.00751 0.00199 -0.0963 0.8678 0.2399
-1.000 0.3272 0.00702 0.00190 -0.0960 0.8601 0.3869
-0.750 0.3518 0.00640 0.00189 -0.0955 0.8502 0.5860
-0.500 0.3829 0.00537 0.00185 -0.0954 0.8420 1.0000
-0.250 0.4095 0.00538 0.00174 -0.0950 0.8321 1.0000
0.000 0.4361 0.00540 0.00166 -0.0946 0.8204 1.0000
0.250 0.4629 0.00543 0.00160 -0.0942 0.8078 1.0000
0.500 0.4896 0.00546 0.00154 -0.0938 0.7939 1.0000
0.750 0.5162 0.00552 0.00150 -0.0934 0.7787 1.0000
1.000 0.5428 0.00559 0.00147 -0.0930 0.7619 1.0000
1.250 0.5694 0.00567 0.00147 -0.0926 0.7439 1.0000
1.500 0.5958 0.00578 0.00147 -0.0922 0.7252 1.0000
1.750 0.6221 0.00591 0.00150 -0.0918 0.7058 1.0000
2.000 0.6484 0.00606 0.00154 -0.0914 0.6850 1.0000
2.250 0.6744 0.00622 0.00161 -0.0910 0.6640 1.0000
2.500 0.7004 0.00640 0.00169 -0.0905 0.6417 1.0000
2.750 0.7263 0.00658 0.00178 -0.0901 0.6193 1.0000
3.000 0.7520 0.00679 0.00188 -0.0897 0.5969 1.0000
3.250 0.7779 0.00699 0.00202 -0.0893 0.5742 1.0000
3.500 0.8035 0.00720 0.00216 -0.0889 0.5516 1.0000
3.750 0.8288 0.00745 0.00231 -0.0884 0.5268 1.0000
4.000 0.8540 0.00771 0.00247 -0.0880 0.5009 1.0000
4.250 0.8793 0.00796 0.00265 -0.0875 0.4761 1.0000
4.500 0.9044 0.00824 0.00287 -0.0871 0.4515 1.0000
4.750 0.9294 0.00853 0.00308 -0.0866 0.4271 1.0000
5.000 0.9541 0.00884 0.00331 -0.0861 0.4021 1.0000
5.250 0.9787 0.00917 0.00356 -0.0856 0.3756 1.0000
5.500 1.0024 0.00958 0.00386 -0.0850 0.3415 1.0000
5.750 1.0248 0.01012 0.00419 -0.0843 0.2959 1.0000
6.000 1.0471 0.01068 0.00454 -0.0835 0.2536 1.0000
6.250 1.0693 0.01126 0.00493 -0.0828 0.2132 1.0000
6.500 1.0919 0.01180 0.00534 -0.0821 0.1827 1.0000
6.750 1.1141 0.01238 0.00581 -0.0813 0.1502 1.0000
7.000 1.1340 0.01320 0.00637 -0.0803 0.1065 1.0000
7.250 1.1516 0.01428 0.00712 -0.0790 0.0569 1.0000
7.500 1.1668 0.01562 0.00815 -0.0772 0.0154 1.0000
7.750 1.1861 0.01651 0.00908 -0.0758 0.0094 1.0000
8.000 1.2067 0.01722 0.00990 -0.0746 0.0084 1.0000
8.250 1.2263 0.01800 0.01082 -0.0733 0.0078 1.0000
8.500 1.2445 0.01888 0.01181 -0.0719 0.0072 1.0000
8.750 1.2609 0.01987 0.01291 -0.0702 0.0069 1.0000
9.000 1.2755 0.02095 0.01411 -0.0682 0.0067 1.0000
9.250 1.2881 0.02214 0.01543 -0.0660 0.0067 1.0000
9.500 1.2977 0.02344 0.01686 -0.0633 0.0066 1.0000
9.750 1.3048 0.02477 0.01832 -0.0602 0.0066 1.0000
10.000 1.3106 0.02628 0.01996 -0.0572 0.0066 1.0000
10.250 1.3165 0.02793 0.02177 -0.0543 0.0067 1.0000
10.500 1.3218 0.02991 0.02393 -0.0515 0.0068 1.0000
10.750 1.3279 0.03214 0.02635 -0.0490 0.0069 1.0000
11.000 1.3331 0.03481 0.02929 -0.0465 0.0071 1.0000
11.250 1.3374 0.03728 0.03197 -0.0443 0.0072 1.0000
11.500 1.3408 0.03924 0.03407 -0.0423 0.0070 1.0000
11.750 1.3394 0.04243 0.03753 -0.0400 0.0071 1.0000
12.000 1.3392 0.04464 0.03988 -0.0384 0.0068 1.0000
12.250 1.3346 0.04778 0.04323 -0.0368 0.0068 1.0000
12.500 1.3219 0.05228 0.04805 -0.0352 0.0070 1.0000
12.750 1.3023 0.05785 0.05395 -0.0344 0.0074 1.0000
13.000 1.2860 0.06297 0.05932 -0.0346 0.0075 1.0000
13.250 1.2685 0.06858 0.06516 -0.0358 0.0076 1.0000
13.500 1.2485 0.07502 0.07181 -0.0380 0.0078 1.0000
13.750 1.2298 0.08175 0.07873 -0.0410 0.0079 1.0000
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Polar data table (+)
Polar graphs
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