SA7024 (sa7024-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: SA7024 (sa7024-il) Reynolds number: 100,000 Max Cl/Cd: 59.02 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sa7024-il-100000-n5.txt Download as CSV file: xf-sa7024-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SA7024
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3814 0.09325 0.08844 -0.0246 1.0000 0.0458
-7.500 -0.3894 0.09132 0.08663 -0.0262 1.0000 0.0473
-7.250 -0.3928 0.08880 0.08421 -0.0299 1.0000 0.0479
-7.000 -0.3893 0.08546 0.08091 -0.0338 1.0000 0.0482
-6.750 -0.3834 0.08163 0.07711 -0.0379 1.0000 0.0483
-6.500 -0.3758 0.07762 0.07309 -0.0413 1.0000 0.0484
-6.250 -0.3737 0.07313 0.06869 -0.0398 1.0000 0.0491
-6.000 -0.3719 0.07105 0.06670 -0.0342 1.0000 0.0512
-5.750 -0.3651 0.06856 0.06423 -0.0337 1.0000 0.0550
-5.500 -0.3397 0.06319 0.05849 -0.0475 1.0000 0.0615
-5.000 -0.3178 0.05197 0.04727 -0.0466 1.0000 0.0334
-4.500 -0.2790 0.04259 0.03744 -0.0514 1.0000 0.0289
-4.250 -0.2493 0.03620 0.03045 -0.0551 1.0000 0.0260
-4.000 -0.2202 0.03223 0.02580 -0.0564 1.0000 0.0244
-3.750 -0.1835 0.02952 0.02258 -0.0591 0.9965 0.0238
-3.500 -0.1455 0.02629 0.01881 -0.0621 0.9926 0.0234
-3.250 -0.1081 0.02378 0.01580 -0.0644 0.9879 0.0233
-3.000 -0.0701 0.02180 0.01339 -0.0665 0.9836 0.0233
-2.750 -0.0343 0.02022 0.01149 -0.0680 0.9782 0.0236
-2.500 0.0015 0.01875 0.00979 -0.0696 0.9726 0.0243
-2.250 0.0374 0.01755 0.00850 -0.0713 0.9668 0.0266
-2.000 0.0729 0.01690 0.00777 -0.0729 0.9593 0.0329
-1.750 0.1091 0.01612 0.00684 -0.0745 0.9520 0.0380
-1.500 0.1468 0.01535 0.00606 -0.0763 0.9448 0.0563
-1.250 0.1801 0.01391 0.00575 -0.0781 0.9369 0.3356
-0.750 0.2470 0.01198 0.00533 -0.0789 0.9209 1.0000
-0.500 0.2831 0.01195 0.00505 -0.0803 0.9110 1.0000
-0.250 0.3199 0.01191 0.00478 -0.0818 0.9010 1.0000
0.000 0.3546 0.01188 0.00458 -0.0830 0.8893 1.0000
0.250 0.3882 0.01185 0.00441 -0.0838 0.8760 1.0000
0.750 0.4534 0.01182 0.00415 -0.0850 0.8457 1.0000
1.000 0.4845 0.01183 0.00407 -0.0853 0.8283 1.0000
1.250 0.5155 0.01185 0.00400 -0.0856 0.8105 1.0000
1.500 0.5458 0.01189 0.00397 -0.0856 0.7917 1.0000
1.750 0.5745 0.01197 0.00397 -0.0854 0.7708 1.0000
2.000 0.6032 0.01206 0.00399 -0.0852 0.7492 1.0000
2.250 0.6311 0.01219 0.00403 -0.0848 0.7263 1.0000
2.500 0.6579 0.01234 0.00411 -0.0843 0.7017 1.0000
2.750 0.6844 0.01252 0.00425 -0.0837 0.6765 1.0000
3.000 0.7105 0.01273 0.00439 -0.0830 0.6509 1.0000
3.250 0.7363 0.01297 0.00455 -0.0823 0.6251 1.0000
3.500 0.7616 0.01323 0.00475 -0.0816 0.5985 1.0000
3.750 0.7866 0.01352 0.00497 -0.0808 0.5708 1.0000
4.000 0.8112 0.01383 0.00529 -0.0800 0.5417 1.0000
4.250 0.8354 0.01418 0.00557 -0.0791 0.5120 1.0000
4.500 0.8593 0.01456 0.00589 -0.0782 0.4823 1.0000
4.750 0.8830 0.01497 0.00624 -0.0774 0.4526 1.0000
5.000 0.9065 0.01541 0.00664 -0.0765 0.4232 1.0000
5.250 0.9296 0.01587 0.00716 -0.0756 0.3932 1.0000
5.500 0.9526 0.01637 0.00764 -0.0747 0.3631 1.0000
5.750 0.9748 0.01693 0.00816 -0.0737 0.3309 1.0000
6.000 0.9967 0.01754 0.00872 -0.0727 0.2972 1.0000
6.250 1.0182 0.01820 0.00933 -0.0717 0.2641 1.0000
6.500 1.0394 0.01891 0.01001 -0.0708 0.2337 1.0000
6.750 1.0607 0.01966 0.01083 -0.0698 0.2043 1.0000
7.000 1.0806 0.02054 0.01163 -0.0687 0.1685 1.0000
7.250 1.0995 0.02157 0.01250 -0.0677 0.1288 1.0000
7.500 1.1169 0.02282 0.01349 -0.0666 0.0858 1.0000
7.750 1.1339 0.02418 0.01466 -0.0653 0.0528 1.0000
8.000 1.1494 0.02577 0.01617 -0.0638 0.0296 1.0000
8.250 1.1638 0.02752 0.01800 -0.0619 0.0205 1.0000
8.500 1.1765 0.02936 0.02004 -0.0598 0.0172 1.0000
8.750 1.1891 0.03108 0.02203 -0.0578 0.0156 1.0000
9.000 1.2001 0.03292 0.02418 -0.0556 0.0144 1.0000
9.250 1.2097 0.03486 0.02635 -0.0534 0.0135 1.0000
9.500 1.2180 0.03693 0.02863 -0.0512 0.0129 1.0000
9.750 1.2241 0.03921 0.03111 -0.0489 0.0123 1.0000
10.000 1.2268 0.04172 0.03383 -0.0463 0.0117 1.0000
10.250 1.2261 0.04493 0.03729 -0.0438 0.0112 1.0000
10.500 1.2282 0.04744 0.04006 -0.0416 0.0108 1.0000
10.750 1.2284 0.05001 0.04293 -0.0396 0.0103 1.0000
11.000 1.2253 0.05299 0.04621 -0.0380 0.0099 1.0000
11.250 1.2191 0.05638 0.04990 -0.0368 0.0096 1.0000
11.500 1.2106 0.06020 0.05399 -0.0363 0.0095 1.0000
11.750 1.1994 0.06461 0.05868 -0.0366 0.0094 1.0000
12.000 1.1866 0.06955 0.06388 -0.0378 0.0093 1.0000
12.250 1.1719 0.07522 0.06979 -0.0401 0.0093 1.0000
12.500 1.1557 0.08171 0.07651 -0.0434 0.0094 1.0000
12.750 1.1381 0.08905 0.08406 -0.0477 0.0094 1.0000
13.000 1.1198 0.09724 0.09244 -0.0529 0.0097 1.0000
13.250 1.1008 0.10629 0.10165 -0.0587 0.0100 1.0000
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Polar data table (+)
Polar graphs
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