SA7024 (sa7024-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: SA7024 (sa7024-il) Reynolds number: 50,000 Max Cl/Cd: 42.26 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sa7024-il-50000-n5.txt Download as CSV file: xf-sa7024-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3868 0.09629 0.08967 -0.0224 1.0000 0.1097
-7.250 -0.3944 0.09451 0.08803 -0.0234 1.0000 0.1138
-7.000 -0.4030 0.09274 0.08644 -0.0298 1.0000 0.1159
-6.750 -0.3928 0.08829 0.08202 -0.0266 1.0000 0.1173
-6.500 -0.3864 0.08493 0.07871 -0.0263 1.0000 0.1189
-6.250 -0.3813 0.08170 0.07554 -0.0271 1.0000 0.1202
-6.000 -0.3675 0.07339 0.06713 -0.0379 1.0000 0.0631
-5.500 -0.3405 0.06343 0.05697 -0.0447 1.0000 0.0475
-5.250 -0.3297 0.05990 0.05343 -0.0451 1.0000 0.0462
-5.000 -0.3152 0.05594 0.04938 -0.0469 1.0000 0.0448
-4.750 -0.2973 0.05170 0.04490 -0.0493 1.0000 0.0433
-4.500 -0.2762 0.04732 0.04026 -0.0519 1.0000 0.0419
-4.250 -0.2521 0.04297 0.03553 -0.0544 1.0000 0.0405
-4.000 -0.2260 0.03891 0.03100 -0.0565 1.0000 0.0395
-3.750 -0.1988 0.03534 0.02688 -0.0580 1.0000 0.0387
-3.500 -0.1731 0.03270 0.02379 -0.0587 1.0000 0.0396
-3.250 -0.1476 0.03059 0.02128 -0.0591 1.0000 0.0423
-3.000 -0.1210 0.02859 0.01879 -0.0592 1.0000 0.0449
-2.750 -0.0946 0.02679 0.01651 -0.0589 1.0000 0.0466
-2.500 -0.0690 0.02525 0.01458 -0.0583 1.0000 0.0477
-2.250 -0.0448 0.02387 0.01294 -0.0576 1.0000 0.0496
-2.000 -0.0209 0.02283 0.01176 -0.0569 1.0000 0.0530
-1.750 0.0043 0.02202 0.01069 -0.0563 1.0000 0.0586
-1.500 0.0302 0.02127 0.00980 -0.0562 1.0000 0.0683
-1.250 0.0581 0.02021 0.00911 -0.0567 1.0000 0.1344
-1.000 0.0757 0.01746 0.00912 -0.0547 1.0000 0.7132
-0.750 0.1158 0.01732 0.00861 -0.0572 0.9875 1.0000
-0.500 0.1577 0.01766 0.00845 -0.0603 0.9760 1.0000
-0.250 0.1986 0.01796 0.00836 -0.0633 0.9638 1.0000
0.000 0.2388 0.01821 0.00830 -0.0660 0.9511 1.0000
0.250 0.2786 0.01843 0.00825 -0.0685 0.9382 1.0000
0.500 0.3179 0.01862 0.00824 -0.0709 0.9250 1.0000
0.750 0.3569 0.01876 0.00824 -0.0731 0.9115 1.0000
1.000 0.3958 0.01888 0.00824 -0.0752 0.8978 1.0000
1.250 0.4346 0.01895 0.00824 -0.0771 0.8836 1.0000
1.500 0.4718 0.01900 0.00824 -0.0786 0.8685 1.0000
1.750 0.5080 0.01902 0.00823 -0.0798 0.8526 1.0000
2.000 0.5440 0.01901 0.00824 -0.0808 0.8363 1.0000
2.250 0.5777 0.01902 0.00825 -0.0813 0.8185 1.0000
2.500 0.6090 0.01906 0.00832 -0.0814 0.7987 1.0000
2.750 0.6425 0.01904 0.00832 -0.0817 0.7798 1.0000
3.000 0.6710 0.01914 0.00851 -0.0812 0.7571 1.0000
3.250 0.7006 0.01921 0.00861 -0.0808 0.7344 1.0000
3.500 0.7300 0.01930 0.00871 -0.0803 0.7106 1.0000
3.750 0.7575 0.01946 0.00890 -0.0795 0.6849 1.0000
4.000 0.7841 0.01967 0.00922 -0.0786 0.6579 1.0000
4.250 0.8101 0.01992 0.00950 -0.0776 0.6303 1.0000
4.500 0.8354 0.02023 0.00982 -0.0765 0.6017 1.0000
4.750 0.8597 0.02060 0.01023 -0.0754 0.5715 1.0000
5.000 0.8834 0.02101 0.01067 -0.0741 0.5403 1.0000
5.250 0.9068 0.02147 0.01114 -0.0729 0.5088 1.0000
5.500 0.9293 0.02199 0.01180 -0.0716 0.4764 1.0000
5.750 0.9512 0.02258 0.01243 -0.0702 0.4434 1.0000
6.000 0.9728 0.02323 0.01308 -0.0689 0.4110 1.0000
6.250 0.9935 0.02396 0.01387 -0.0676 0.3772 1.0000
6.500 1.0133 0.02476 0.01468 -0.0661 0.3435 1.0000
6.750 1.0322 0.02564 0.01560 -0.0646 0.3081 1.0000
7.000 1.0498 0.02663 0.01665 -0.0631 0.2735 1.0000
7.250 1.0670 0.02772 0.01781 -0.0616 0.2386 1.0000
7.500 1.0832 0.02897 0.01905 -0.0600 0.2071 1.0000
7.750 1.0987 0.03038 0.02049 -0.0585 0.1761 1.0000
8.000 1.1131 0.03199 0.02214 -0.0568 0.1475 1.0000
8.250 1.1253 0.03376 0.02391 -0.0551 0.1200 1.0000
8.500 1.1358 0.03589 0.02604 -0.0531 0.0962 1.0000
8.750 1.1425 0.03820 0.02824 -0.0511 0.0748 1.0000
9.000 1.1489 0.04052 0.03069 -0.0492 0.0548 1.0000
9.250 1.1542 0.04296 0.03323 -0.0473 0.0431 1.0000
9.500 1.1576 0.04569 0.03604 -0.0451 0.0376 1.0000
9.750 1.1637 0.04834 0.03915 -0.0430 0.0327 1.0000
10.000 1.1648 0.05096 0.04189 -0.0411 0.0298 1.0000
10.250 1.1646 0.05410 0.04516 -0.0394 0.0278 1.0000
10.500 1.1670 0.05748 0.04897 -0.0379 0.0264 1.0000
10.750 1.1652 0.06126 0.05312 -0.0367 0.0256 1.0000
11.000 1.1593 0.06537 0.05758 -0.0360 0.0251 1.0000
11.250 1.1496 0.06996 0.06248 -0.0360 0.0248 1.0000
11.500 1.1373 0.07501 0.06782 -0.0371 0.0247 1.0000
11.750 1.1225 0.08077 0.07384 -0.0391 0.0246 1.0000
12.000 1.1061 0.08723 0.08053 -0.0423 0.0248 1.0000
12.250 1.0886 0.09453 0.08803 -0.0466 0.0250 1.0000
12.500 1.0710 0.10260 0.09628 -0.0516 0.0254 1.0000
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Polar data table (+)
Polar graphs
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