SA7024 (sa7024-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: SA7024 (sa7024-il) Reynolds number: 50,000 Max Cl/Cd: 38.8 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sa7024-il-50000.txt Download as CSV file: xf-sa7024-il-50000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3969 0.10038 0.09385 -0.0181 1.0000 0.1904
-7.250 -0.3832 0.09585 0.08935 -0.0168 1.0000 0.1982
-7.000 -0.3993 0.09546 0.08914 -0.0176 1.0000 0.2046
-6.750 -0.3858 0.09104 0.08475 -0.0153 1.0000 0.2143
-6.250 -0.3972 0.08758 0.08155 -0.0191 1.0000 0.2331
-6.000 -0.3878 0.08382 0.07784 -0.0164 1.0000 0.2460
-5.750 -0.3806 0.08050 0.07459 -0.0144 1.0000 0.2581
-5.500 -0.3804 0.07808 0.07221 -0.0149 1.0000 0.2736
-5.250 -0.3788 0.07559 0.06981 -0.0155 1.0000 0.2893
-4.750 -0.3701 0.07023 0.06459 -0.0122 1.0000 0.3310
-4.500 -0.3663 0.06764 0.06209 -0.0090 1.0000 0.3588
-4.000 -0.3577 0.06209 0.05672 0.0015 1.0000 0.4209
-3.250 -0.1770 0.03771 0.02986 -0.0568 1.0000 0.1335
-3.000 -0.1429 0.03377 0.02527 -0.0588 1.0000 0.1191
-2.750 -0.1112 0.03060 0.02150 -0.0599 1.0000 0.1121
-2.500 -0.0792 0.02838 0.01845 -0.0602 1.0000 0.1084
-2.250 -0.0517 0.02625 0.01602 -0.0600 1.0000 0.1096
-2.000 -0.0260 0.02466 0.01424 -0.0595 1.0000 0.1156
-1.750 -0.0003 0.02342 0.01284 -0.0589 1.0000 0.1304
-1.500 0.0261 0.02222 0.01147 -0.0580 1.0000 0.1506
-1.250 0.0612 0.01849 0.00990 -0.0587 1.0000 0.4863
-1.000 0.0719 0.01696 0.00902 -0.0538 1.0000 1.0000
-0.750 0.0949 0.01726 0.00875 -0.0534 1.0000 1.0000
-0.500 0.1169 0.01760 0.00864 -0.0530 1.0000 1.0000
-0.250 0.1382 0.01799 0.00871 -0.0527 1.0000 1.0000
0.000 0.1589 0.01844 0.00888 -0.0523 1.0000 1.0000
0.250 0.1789 0.01894 0.00915 -0.0520 1.0000 1.0000
0.500 0.1985 0.01949 0.00948 -0.0518 1.0000 1.0000
0.750 0.2174 0.02012 0.00994 -0.0515 1.0000 1.0000
1.000 0.2357 0.02081 0.01050 -0.0514 1.0000 1.0000
1.250 0.2534 0.02157 0.01116 -0.0512 1.0000 1.0000
1.500 0.2706 0.02242 0.01192 -0.0512 1.0000 1.0000
1.750 0.3124 0.02364 0.01304 -0.0559 0.9872 1.0000
2.000 0.3696 0.02486 0.01420 -0.0629 0.9655 1.0000
2.250 0.4270 0.02584 0.01517 -0.0694 0.9441 1.0000
2.500 0.4759 0.02654 0.01593 -0.0740 0.9207 1.0000
2.750 0.5269 0.02709 0.01654 -0.0786 0.8977 1.0000
3.000 0.5834 0.02733 0.01691 -0.0835 0.8755 1.0000
3.250 0.6296 0.02746 0.01723 -0.0863 0.8508 1.0000
3.500 0.6806 0.02728 0.01724 -0.0892 0.8266 1.0000
3.750 0.7311 0.02681 0.01697 -0.0913 0.8027 1.0000
4.000 0.7812 0.02607 0.01651 -0.0926 0.7786 1.0000
4.250 0.8200 0.02560 0.01622 -0.0922 0.7514 1.0000
4.500 0.8528 0.02533 0.01610 -0.0909 0.7216 1.0000
4.750 0.8828 0.02517 0.01606 -0.0891 0.6897 1.0000
5.000 0.9138 0.02492 0.01597 -0.0872 0.6568 1.0000
5.250 0.9395 0.02504 0.01616 -0.0850 0.6211 1.0000
5.500 0.9665 0.02513 0.01623 -0.0827 0.5850 1.0000
5.750 0.9896 0.02553 0.01665 -0.0804 0.5462 1.0000
6.000 1.0119 0.02608 0.01718 -0.0781 0.5063 1.0000
6.250 1.0335 0.02671 0.01784 -0.0757 0.4650 1.0000
6.500 1.0541 0.02743 0.01846 -0.0733 0.4223 1.0000
6.750 1.0737 0.02829 0.01915 -0.0709 0.3784 1.0000
7.000 1.0909 0.02945 0.02025 -0.0684 0.3339 1.0000
7.250 1.1076 0.03080 0.02150 -0.0660 0.2900 1.0000
7.500 1.1250 0.03259 0.02318 -0.0638 0.2492 1.0000
7.750 1.1419 0.03451 0.02492 -0.0618 0.2119 1.0000
8.000 1.1572 0.03670 0.02716 -0.0596 0.1794 1.0000
8.250 1.1743 0.03964 0.03027 -0.0576 0.1526 1.0000
8.500 1.1869 0.04241 0.03311 -0.0553 0.1269 1.0000
8.750 1.1991 0.04552 0.03619 -0.0532 0.1055 1.0000
9.000 1.2073 0.04875 0.03974 -0.0509 0.0911 1.0000
9.250 1.2222 0.05286 0.04383 -0.0497 0.0817 1.0000
9.500 1.2227 0.05740 0.04915 -0.0469 0.0799 1.0000
9.750 1.2185 0.06214 0.05449 -0.0444 0.0786 1.0000
10.000 1.2099 0.06691 0.05973 -0.0422 0.0780 1.0000
10.250 1.1967 0.07164 0.06484 -0.0402 0.0780 1.0000
10.500 1.1789 0.07622 0.06969 -0.0384 0.0784 1.0000
10.750 1.1588 0.08082 0.07448 -0.0372 0.0791 1.0000
11.000 1.1387 0.08588 0.07969 -0.0372 0.0799 1.0000
11.250 1.1200 0.09153 0.08546 -0.0385 0.0807 1.0000
11.500 1.1043 0.09772 0.09172 -0.0406 0.0814 1.0000
11.750 1.0038 0.12455 0.11851 -0.0654 0.1172 1.0000
12.000 0.9854 0.13662 0.13048 -0.0731 0.1359 1.0000
12.250 0.9828 0.14312 0.13696 -0.0755 0.1351 1.0000
12.500 0.9871 0.14921 0.14304 -0.0765 0.1334 1.0000
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Polar data table (+)
Polar graphs
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