SD7043 (9.1%) (sd7043-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: SD7043 (9.1%) (sd7043-il) Reynolds number: 50,000 Max Cl/Cd: 41.13 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sd7043-il-50000-n5.txt Download as CSV file: xf-sd7043-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SD7043 (9.1%)
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3434 0.10888 0.10181 -0.0310 1.0000 0.1118
-8.750 -0.3562 0.10768 0.10076 -0.0336 1.0000 0.1157
-8.500 -0.3661 0.10590 0.09913 -0.0351 1.0000 0.1163
-8.000 -0.3529 0.09473 0.08798 -0.0361 1.0000 0.0719
-7.500 -0.3710 0.08827 0.08175 -0.0362 1.0000 0.0594
-7.250 -0.3724 0.08555 0.07912 -0.0350 1.0000 0.0578
-7.000 -0.3776 0.08273 0.07640 -0.0347 1.0000 0.0564
-6.750 -0.3836 0.07958 0.07333 -0.0352 1.0000 0.0549
-6.250 -0.3950 0.06739 0.06097 -0.0462 1.0000 0.0489
-6.000 -0.3909 0.06407 0.05764 -0.0463 1.0000 0.0485
-5.750 -0.3847 0.06028 0.05376 -0.0473 1.0000 0.0481
-5.500 -0.3753 0.05612 0.04944 -0.0490 1.0000 0.0477
-5.250 -0.3617 0.05169 0.04473 -0.0514 1.0000 0.0476
-5.000 -0.3421 0.04674 0.03921 -0.0547 1.0000 0.0485
-4.750 -0.3232 0.04331 0.03553 -0.0561 1.0000 0.0502
-4.500 -0.3028 0.04065 0.03262 -0.0569 1.0000 0.0517
-4.250 -0.2780 0.03746 0.02893 -0.0583 1.0000 0.0525
-4.000 -0.2444 0.03455 0.02550 -0.0607 0.9970 0.0543
-3.750 -0.2059 0.03208 0.02235 -0.0635 0.9923 0.0590
-3.500 -0.1691 0.02991 0.01969 -0.0656 0.9875 0.0619
-3.250 -0.1333 0.02842 0.01799 -0.0675 0.9826 0.0664
-3.000 -0.0984 0.02727 0.01644 -0.0688 0.9767 0.0736
-2.750 -0.0625 0.02612 0.01527 -0.0705 0.9717 0.0805
-2.500 -0.0302 0.02527 0.01427 -0.0714 0.9648 0.0921
-2.250 0.0077 0.02446 0.01337 -0.0735 0.9591 0.1132
-2.000 0.0427 0.02348 0.01267 -0.0754 0.9525 0.1696
-1.750 0.0789 0.02221 0.01245 -0.0779 0.9464 0.3743
-1.500 0.1060 0.02149 0.01259 -0.0773 0.9394 0.5950
-1.250 0.1256 0.02100 0.01262 -0.0741 0.9310 0.7830
-1.000 0.1626 0.02072 0.01224 -0.0754 0.9214 1.0000
-0.750 0.2034 0.02097 0.01206 -0.0782 0.9140 1.0000
-0.500 0.2351 0.02121 0.01200 -0.0792 0.9037 1.0000
-0.250 0.2736 0.02143 0.01194 -0.0814 0.8956 1.0000
0.000 0.3078 0.02166 0.01194 -0.0827 0.8856 1.0000
0.250 0.3404 0.02188 0.01199 -0.0837 0.8752 1.0000
0.500 0.3809 0.02201 0.01194 -0.0859 0.8675 1.0000
0.750 0.4097 0.02222 0.01202 -0.0861 0.8553 1.0000
1.000 0.4402 0.02240 0.01210 -0.0865 0.8436 1.0000
1.250 0.4733 0.02251 0.01212 -0.0872 0.8329 1.0000
1.500 0.5090 0.02252 0.01207 -0.0881 0.8227 1.0000
1.750 0.5377 0.02264 0.01214 -0.0880 0.8094 1.0000
2.000 0.5670 0.02271 0.01219 -0.0879 0.7960 1.0000
2.250 0.5966 0.02274 0.01221 -0.0877 0.7824 1.0000
2.500 0.6262 0.02274 0.01220 -0.0874 0.7683 1.0000
2.750 0.6557 0.02270 0.01219 -0.0870 0.7536 1.0000
3.000 0.6849 0.02264 0.01215 -0.0865 0.7381 1.0000
3.250 0.7140 0.02256 0.01208 -0.0859 0.7218 1.0000
3.500 0.7433 0.02243 0.01200 -0.0853 0.7048 1.0000
3.750 0.7716 0.02234 0.01192 -0.0845 0.6862 1.0000
4.000 0.7974 0.02236 0.01199 -0.0834 0.6647 1.0000
4.250 0.8260 0.02226 0.01191 -0.0825 0.6436 1.0000
4.500 0.8511 0.02235 0.01202 -0.0814 0.6189 1.0000
4.750 0.8774 0.02242 0.01208 -0.0803 0.5933 1.0000
5.000 0.9030 0.02256 0.01218 -0.0791 0.5660 1.0000
5.250 0.9273 0.02281 0.01241 -0.0779 0.5366 1.0000
5.500 0.9502 0.02317 0.01272 -0.0766 0.5057 1.0000
5.750 0.9723 0.02364 0.01312 -0.0752 0.4739 1.0000
6.000 0.9933 0.02420 0.01359 -0.0738 0.4418 1.0000
6.250 1.0137 0.02485 0.01420 -0.0725 0.4103 1.0000
6.500 1.0332 0.02560 0.01486 -0.0711 0.3799 1.0000
6.750 1.0521 0.02644 0.01561 -0.0697 0.3510 1.0000
7.000 1.0706 0.02735 0.01643 -0.0683 0.3244 1.0000
7.250 1.0885 0.02832 0.01737 -0.0670 0.2995 1.0000
7.500 1.1066 0.02935 0.01839 -0.0657 0.2762 1.0000
7.750 1.1240 0.03044 0.01942 -0.0644 0.2553 1.0000
8.000 1.1417 0.03158 0.02057 -0.0632 0.2359 1.0000
8.250 1.1588 0.03276 0.02182 -0.0620 0.2178 1.0000
8.500 1.1758 0.03401 0.02310 -0.0608 0.2017 1.0000
8.750 1.1923 0.03531 0.02445 -0.0595 0.1870 1.0000
9.000 1.2085 0.03667 0.02587 -0.0583 0.1737 1.0000
9.250 1.2246 0.03810 0.02737 -0.0571 0.1619 1.0000
9.500 1.2397 0.03956 0.02887 -0.0558 0.1514 1.0000
9.750 1.2548 0.04113 0.03060 -0.0546 0.1415 1.0000
10.000 1.2692 0.04284 0.03250 -0.0533 0.1326 1.0000
10.250 1.2827 0.04441 0.03401 -0.0520 0.1252 1.0000
10.500 1.2942 0.04644 0.03643 -0.0505 0.1181 1.0000
10.750 1.3085 0.04818 0.03818 -0.0493 0.1124 1.0000
11.000 1.3146 0.05055 0.04093 -0.0475 0.1068 1.0000
11.250 1.3213 0.05259 0.04313 -0.0460 0.1018 1.0000
11.500 1.3324 0.05486 0.04548 -0.0448 0.0978 1.0000
11.750 1.3302 0.05800 0.04906 -0.0430 0.0945 1.0000
12.000 1.3283 0.06097 0.05231 -0.0416 0.0913 1.0000
12.250 1.3308 0.06343 0.05487 -0.0405 0.0881 1.0000
12.500 1.3314 0.06641 0.05796 -0.0395 0.0854 1.0000
12.750 1.3141 0.07105 0.06302 -0.0389 0.0840 1.0000
13.000 1.2944 0.07633 0.06864 -0.0392 0.0829 1.0000
13.250 1.2708 0.08252 0.07514 -0.0405 0.0823 1.0000
13.500 1.2411 0.09014 0.08303 -0.0434 0.0821 1.0000
13.750 1.2023 0.10024 0.09336 -0.0488 0.0825 1.0000
14.000 1.1519 0.11458 0.10785 -0.0579 0.0836 1.0000
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Polar data table (+)
Polar graphs
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