SA7038 (sa7038-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: SA7038 (sa7038-il) Reynolds number: 500,000 Max Cl/Cd: 92.52 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sa7038-il-500000-n5.txt Download as CSV file: xf-sa7038-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SA7038
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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3678 0.08345 0.08126 -0.0354 1.0000 0.0094
-8.250 -0.3750 0.08058 0.07844 -0.0349 1.0000 0.0092
-8.000 -0.3662 0.07567 0.07355 -0.0401 0.9936 0.0089
-7.750 -0.3555 0.06981 0.06769 -0.0477 0.9856 0.0086
-7.500 -0.3387 0.06173 0.05960 -0.0605 0.9775 0.0086
-7.250 -0.3187 0.05061 0.04834 -0.0766 0.9687 0.0083
-7.000 -0.3073 0.03911 0.03650 -0.0862 0.9573 0.0083
-6.750 -0.3009 0.03000 0.02681 -0.0888 0.9458 0.0083
-6.500 -0.2867 0.02472 0.02097 -0.0892 0.9377 0.0084
-6.250 -0.2668 0.02184 0.01767 -0.0889 0.9309 0.0087
-6.000 -0.2446 0.01982 0.01528 -0.0884 0.9246 0.0091
-5.750 -0.2213 0.01815 0.01328 -0.0879 0.9178 0.0093
-5.500 -0.1973 0.01655 0.01138 -0.0874 0.9116 0.0093
-5.250 -0.1726 0.01526 0.00984 -0.0869 0.9043 0.0093
-5.000 -0.1472 0.01418 0.00855 -0.0864 0.8981 0.0093
-4.750 -0.1215 0.01327 0.00748 -0.0859 0.8909 0.0094
-4.500 -0.0954 0.01250 0.00656 -0.0855 0.8845 0.0095
-4.250 -0.0692 0.01184 0.00579 -0.0851 0.8767 0.0097
-4.000 -0.0427 0.01130 0.00515 -0.0847 0.8690 0.0099
-3.750 -0.0163 0.01075 0.00451 -0.0844 0.8601 0.0101
-3.500 0.0101 0.01011 0.00376 -0.0841 0.8506 0.0107
-3.250 0.0370 0.00974 0.00331 -0.0838 0.8410 0.0113
-3.000 0.0642 0.00945 0.00294 -0.0835 0.8306 0.0119
-2.750 0.0915 0.00922 0.00264 -0.0833 0.8196 0.0127
-2.500 0.1189 0.00904 0.00239 -0.0831 0.8081 0.0139
-2.250 0.1464 0.00888 0.00213 -0.0828 0.7959 0.0145
-2.000 0.1738 0.00873 0.00190 -0.0826 0.7822 0.0167
-1.750 0.2010 0.00852 0.00171 -0.0823 0.7669 0.0347
-1.500 0.2278 0.00826 0.00155 -0.0821 0.7503 0.0872
-1.250 0.2547 0.00805 0.00145 -0.0820 0.7338 0.1426
-1.000 0.2814 0.00780 0.00138 -0.0819 0.7173 0.2209
-0.750 0.3074 0.00734 0.00136 -0.0818 0.7007 0.3808
-0.500 0.3333 0.00699 0.00136 -0.0816 0.6837 0.5187
-0.250 0.3594 0.00682 0.00137 -0.0812 0.6660 0.6053
0.000 0.3853 0.00672 0.00139 -0.0808 0.6480 0.6754
0.250 0.4104 0.00663 0.00142 -0.0801 0.6296 0.7456
0.500 0.4342 0.00654 0.00147 -0.0790 0.6105 0.8182
0.750 0.4555 0.00647 0.00151 -0.0771 0.5922 0.8978
1.000 0.4906 0.00650 0.00150 -0.0785 0.5724 0.9791
1.250 0.5211 0.00663 0.00152 -0.0791 0.5534 1.0000
1.500 0.5476 0.00679 0.00156 -0.0788 0.5347 1.0000
1.750 0.5741 0.00696 0.00162 -0.0785 0.5165 1.0000
2.000 0.6006 0.00712 0.00169 -0.0783 0.4980 1.0000
2.250 0.6270 0.00730 0.00177 -0.0780 0.4788 1.0000
2.500 0.6533 0.00750 0.00187 -0.0777 0.4595 1.0000
2.750 0.6797 0.00769 0.00197 -0.0774 0.4399 1.0000
3.000 0.7059 0.00790 0.00209 -0.0772 0.4206 1.0000
3.250 0.7321 0.00811 0.00222 -0.0769 0.4026 1.0000
3.500 0.7584 0.00832 0.00235 -0.0767 0.3858 1.0000
3.750 0.7845 0.00854 0.00250 -0.0764 0.3677 1.0000
4.000 0.8104 0.00879 0.00268 -0.0761 0.3486 1.0000
4.250 0.8361 0.00905 0.00286 -0.0758 0.3282 1.0000
4.500 0.8617 0.00932 0.00304 -0.0755 0.3088 1.0000
4.750 0.8873 0.00959 0.00325 -0.0751 0.2921 1.0000
5.000 0.9127 0.00987 0.00348 -0.0748 0.2749 1.0000
5.250 0.9382 0.01015 0.00371 -0.0745 0.2589 1.0000
5.500 0.9636 0.01043 0.00395 -0.0741 0.2442 1.0000
5.750 0.9886 0.01074 0.00420 -0.0737 0.2275 1.0000
6.000 1.0135 0.01106 0.00449 -0.0733 0.2124 1.0000
6.250 1.0379 0.01143 0.00480 -0.0729 0.1952 1.0000
6.500 1.0619 0.01183 0.00512 -0.0724 0.1773 1.0000
6.750 1.0861 0.01220 0.00545 -0.0719 0.1626 1.0000
7.000 1.1099 0.01260 0.00582 -0.0714 0.1470 1.0000
7.250 1.1334 0.01302 0.00620 -0.0708 0.1327 1.0000
7.500 1.1564 0.01348 0.00661 -0.0701 0.1171 1.0000
7.750 1.1783 0.01404 0.00707 -0.0694 0.0992 1.0000
8.000 1.2001 0.01458 0.00755 -0.0686 0.0832 1.0000
8.250 1.2219 0.01510 0.00805 -0.0678 0.0716 1.0000
8.500 1.2430 0.01567 0.00858 -0.0670 0.0595 1.0000
8.750 1.2633 0.01631 0.00916 -0.0660 0.0469 1.0000
9.000 1.2827 0.01698 0.00979 -0.0649 0.0362 1.0000
9.250 1.3022 0.01762 0.01041 -0.0638 0.0294 1.0000
9.500 1.3213 0.01826 0.01106 -0.0627 0.0238 1.0000
9.750 1.3396 0.01893 0.01174 -0.0614 0.0186 1.0000
10.000 1.3565 0.01967 0.01252 -0.0600 0.0138 1.0000
10.250 1.3714 0.02052 0.01337 -0.0583 0.0087 1.0000
10.500 1.3840 0.02138 0.01426 -0.0562 0.0060 1.0000
10.750 1.3945 0.02228 0.01522 -0.0538 0.0047 1.0000
11.000 1.4063 0.02310 0.01613 -0.0516 0.0043 1.0000
11.250 1.4173 0.02398 0.01711 -0.0495 0.0041 1.0000
11.500 1.4265 0.02501 0.01824 -0.0473 0.0037 1.0000
11.750 1.4354 0.02609 0.01941 -0.0452 0.0035 1.0000
12.000 1.4420 0.02736 0.02080 -0.0430 0.0033 1.0000
12.250 1.4485 0.02869 0.02226 -0.0411 0.0032 1.0000
12.500 1.4514 0.03036 0.02406 -0.0390 0.0029 1.0000
12.750 1.4560 0.03196 0.02578 -0.0373 0.0028 1.0000
13.000 1.4597 0.03371 0.02766 -0.0357 0.0028 1.0000
13.250 1.4623 0.03566 0.02973 -0.0344 0.0027 1.0000
13.500 1.4620 0.03799 0.03221 -0.0333 0.0027 1.0000
13.750 1.4616 0.04049 0.03484 -0.0324 0.0026 1.0000
14.000 1.4598 0.04329 0.03778 -0.0319 0.0026 1.0000
14.250 1.4571 0.04637 0.04100 -0.0318 0.0026 1.0000
14.500 1.4510 0.05008 0.04487 -0.0321 0.0025 1.0000
14.750 1.4452 0.05396 0.04889 -0.0328 0.0025 1.0000
15.000 1.4375 0.05835 0.05343 -0.0339 0.0025 1.0000
15.250 1.4279 0.06329 0.05853 -0.0356 0.0024 1.0000
15.500 1.4169 0.06871 0.06410 -0.0377 0.0024 1.0000
15.750 1.4061 0.07438 0.06992 -0.0401 0.0024 1.0000
16.000 1.3910 0.08104 0.07674 -0.0431 0.0024 1.0000
16.250 1.3782 0.08753 0.08339 -0.0462 0.0024 1.0000
16.500 1.3625 0.09482 0.09083 -0.0499 0.0023 1.0000
16.750 1.3463 0.10239 0.09855 -0.0537 0.0024 1.0000
17.000 1.3306 0.11009 0.10639 -0.0578 0.0024 1.0000
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