SA7024 (sa7024-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: SA7024 (sa7024-il) Reynolds number: 500,000 Max Cl/Cd: 93.93 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sa7024-il-500000-n5.txt Download as CSV file: xf-sa7024-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3845 0.08580 0.08363 -0.0241 1.0000 0.0087
-7.500 -0.3883 0.08315 0.08101 -0.0237 1.0000 0.0087
-7.250 -0.3949 0.08077 0.07869 -0.0227 1.0000 0.0087
-7.000 -0.3957 0.07769 0.07564 -0.0235 1.0000 0.0087
-6.750 -0.3836 0.07308 0.07104 -0.0286 0.9985 0.0087
-6.500 -0.3571 0.06713 0.06507 -0.0379 0.9950 0.0087
-6.250 -0.3296 0.06089 0.05879 -0.0471 0.9909 0.0087
-6.000 -0.2988 0.05419 0.05201 -0.0568 0.9862 0.0087
-5.750 -0.2662 0.04504 0.04267 -0.0687 0.9823 0.0080
-5.500 -0.2359 0.03739 0.03477 -0.0756 0.9754 0.0079
-5.250 -0.2008 0.02976 0.02672 -0.0814 0.9711 0.0080
-5.000 -0.1692 0.02507 0.02161 -0.0839 0.9663 0.0085
-4.750 -0.1389 0.02097 0.01695 -0.0859 0.9606 0.0090
-4.500 -0.1069 0.01751 0.01299 -0.0881 0.9570 0.0099
-4.250 -0.0777 0.01633 0.01161 -0.0888 0.9504 0.0107
-4.000 -0.0444 0.01420 0.00908 -0.0899 0.9451 0.0101
-3.750 -0.0121 0.01289 0.00751 -0.0906 0.9382 0.0097
-3.500 0.0216 0.01193 0.00636 -0.0917 0.9308 0.0094
-3.250 0.0533 0.01111 0.00541 -0.0924 0.9209 0.0093
-3.000 0.0848 0.01040 0.00456 -0.0930 0.9100 0.0092
-2.750 0.1149 0.00976 0.00380 -0.0934 0.8974 0.0092
-2.500 0.1440 0.00921 0.00314 -0.0935 0.8834 0.0093
-2.250 0.1724 0.00878 0.00259 -0.0934 0.8680 0.0094
-2.000 0.2003 0.00844 0.00212 -0.0932 0.8514 0.0099
-1.750 0.2277 0.00823 0.00174 -0.0929 0.8330 0.0109
-1.500 0.2548 0.00810 0.00149 -0.0925 0.8129 0.0125
-1.250 0.2816 0.00804 0.00130 -0.0921 0.7932 0.0142
-1.000 0.3084 0.00787 0.00117 -0.0918 0.7732 0.0469
-0.750 0.3347 0.00756 0.00107 -0.0916 0.7533 0.1466
-0.500 0.3612 0.00737 0.00102 -0.0914 0.7329 0.2304
-0.250 0.3873 0.00715 0.00103 -0.0911 0.7121 0.3428
0.000 0.4132 0.00690 0.00107 -0.0909 0.6905 0.4743
0.250 0.4336 0.00610 0.00120 -0.0894 0.6690 0.7953
0.500 0.4609 0.00587 0.00116 -0.0887 0.6445 1.0000
0.750 0.4871 0.00603 0.00118 -0.0883 0.6198 1.0000
1.000 0.5134 0.00619 0.00120 -0.0879 0.5964 1.0000
1.250 0.5396 0.00636 0.00124 -0.0875 0.5746 1.0000
1.500 0.5661 0.00652 0.00130 -0.0872 0.5527 1.0000
1.750 0.5923 0.00669 0.00136 -0.0868 0.5305 1.0000
2.000 0.6185 0.00689 0.00144 -0.0864 0.5075 1.0000
2.250 0.6445 0.00710 0.00153 -0.0861 0.4809 1.0000
2.500 0.6704 0.00733 0.00165 -0.0857 0.4533 1.0000
2.750 0.6964 0.00756 0.00177 -0.0853 0.4282 1.0000
3.000 0.7225 0.00779 0.00190 -0.0850 0.4046 1.0000
3.250 0.7484 0.00803 0.00205 -0.0846 0.3818 1.0000
3.500 0.7745 0.00826 0.00220 -0.0843 0.3600 1.0000
3.750 0.8003 0.00852 0.00240 -0.0840 0.3363 1.0000
4.250 0.8512 0.00913 0.00281 -0.0832 0.2844 1.0000
4.500 0.8739 0.00979 0.00311 -0.0825 0.2197 1.0000
4.750 0.8977 0.01031 0.00342 -0.0820 0.1762 1.0000
5.000 0.9224 0.01072 0.00371 -0.0815 0.1493 1.0000
5.250 0.9465 0.01121 0.00409 -0.0810 0.1185 1.0000
5.500 0.9702 0.01174 0.00447 -0.0804 0.0895 1.0000
5.750 0.9923 0.01251 0.00499 -0.0796 0.0483 1.0000
6.000 1.0154 0.01313 0.00549 -0.0790 0.0256 1.0000
6.250 1.0377 0.01387 0.00612 -0.0781 0.0062 1.0000
6.500 1.0614 0.01440 0.00667 -0.0775 0.0040 1.0000
6.750 1.0856 0.01486 0.00723 -0.0768 0.0036 1.0000
7.000 1.1094 0.01534 0.00780 -0.0762 0.0033 1.0000
7.250 1.1328 0.01589 0.00845 -0.0755 0.0031 1.0000
7.500 1.1556 0.01649 0.00917 -0.0746 0.0029 1.0000
7.750 1.1776 0.01719 0.00998 -0.0737 0.0027 1.0000
8.000 1.1989 0.01797 0.01087 -0.0727 0.0026 1.0000
8.250 1.2194 0.01881 0.01184 -0.0716 0.0025 1.0000
8.500 1.2386 0.01978 0.01297 -0.0703 0.0024 1.0000
8.750 1.2570 0.02080 0.01413 -0.0690 0.0023 1.0000
9.000 1.2741 0.02193 0.01540 -0.0674 0.0023 1.0000
9.250 1.2899 0.02317 0.01678 -0.0658 0.0023 1.0000
9.500 1.3045 0.02449 0.01825 -0.0639 0.0022 1.0000
9.750 1.3174 0.02594 0.01986 -0.0620 0.0022 1.0000
10.000 1.3289 0.02745 0.02154 -0.0598 0.0022 1.0000
10.250 1.3385 0.02909 0.02336 -0.0575 0.0022 1.0000
10.500 1.3445 0.03077 0.02522 -0.0548 0.0022 1.0000
10.750 1.3471 0.03255 0.02719 -0.0516 0.0022 1.0000
11.000 1.3477 0.03448 0.02932 -0.0485 0.0022 1.0000
11.250 1.3459 0.03669 0.03173 -0.0456 0.0022 1.0000
11.500 1.3427 0.03909 0.03437 -0.0431 0.0022 1.0000
11.750 1.3371 0.04190 0.03740 -0.0410 0.0022 1.0000
12.000 1.3299 0.04504 0.04075 -0.0395 0.0022 1.0000
12.250 1.3206 0.04870 0.04463 -0.0388 0.0022 1.0000
12.500 1.3100 0.05287 0.04901 -0.0389 0.0022 1.0000
12.750 1.2970 0.05778 0.05414 -0.0399 0.0023 1.0000
13.000 1.2840 0.06318 0.05973 -0.0418 0.0023 1.0000
13.250 1.2693 0.06940 0.06615 -0.0447 0.0023 1.0000
13.500 1.2523 0.07661 0.07356 -0.0486 0.0023 1.0000
13.750 1.2362 0.08422 0.08134 -0.0531 0.0023 1.0000
14.000 1.2181 0.09282 0.09011 -0.0583 0.0023 1.0000
14.250 1.2008 0.10179 0.09923 -0.0638 0.0023 1.0000
14.500 1.1822 0.11155 0.10914 -0.0698 0.0023 1.0000
14.750 1.1642 0.12172 0.11944 -0.0759 0.0024 1.0000
15.000 1.1453 0.13256 0.13037 -0.0823 0.0024 1.0000
15.250 1.1268 0.14386 0.14178 -0.0889 0.0024 1.0000
15.500 1.1066 0.15642 0.15443 -0.0959 0.0025 1.0000
15.750 1.0814 0.17186 0.16994 -0.1040 0.0025 1.0000
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Polar data table (+)
Polar graphs
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