SD7043 (9.1%) (sd7043-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD7043 (9.1%) (sd7043-il) Reynolds number: 50,000 Max Cl/Cd: 38.65 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd7043-il-50000.txt Download as CSV file: xf-sd7043-il-50000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3491 0.10352 0.09692 -0.0258 1.0000 0.2226
-7.750 -0.3299 0.09861 0.09200 -0.0241 1.0000 0.2318
-7.500 -0.3569 0.09934 0.09297 -0.0233 1.0000 0.2381
-7.250 -0.3347 0.09434 0.08795 -0.0216 1.0000 0.2485
-7.000 -0.3693 0.09552 0.08937 -0.0192 1.0000 0.2534
-6.750 -0.3500 0.09094 0.08480 -0.0172 1.0000 0.2655
-6.500 -0.3766 0.09066 0.08472 -0.0148 1.0000 0.2705
-6.250 -0.3754 0.08828 0.08240 -0.0122 1.0000 0.2828
-6.000 -0.3709 0.08528 0.07947 -0.0094 1.0000 0.2929
-5.500 -0.3983 0.08246 0.07690 -0.0066 1.0000 0.3164
-5.250 -0.4011 0.08029 0.07480 -0.0044 1.0000 0.3317
-5.000 -0.3955 0.07740 0.07197 -0.0004 1.0000 0.3495
-4.750 -0.3933 0.07508 0.06972 0.0032 1.0000 0.3702
-4.500 -0.4009 0.07330 0.06803 0.0052 1.0000 0.3945
-3.750 -0.2699 0.04370 0.03626 -0.0538 1.0000 0.1460
-3.500 -0.2322 0.03872 0.03037 -0.0579 1.0000 0.1320
-3.250 -0.2024 0.03570 0.02686 -0.0594 1.0000 0.1316
-3.000 -0.1725 0.03309 0.02378 -0.0605 1.0000 0.1338
-2.750 -0.1445 0.03094 0.02133 -0.0609 1.0000 0.1359
-2.500 -0.1175 0.02937 0.01947 -0.0610 1.0000 0.1424
-2.250 -0.0911 0.02799 0.01783 -0.0610 1.0000 0.1522
-2.000 -0.0655 0.02680 0.01638 -0.0605 1.0000 0.1641
-1.750 -0.0417 0.02582 0.01548 -0.0599 1.0000 0.1875
-1.500 -0.0143 0.02467 0.01448 -0.0597 1.0000 0.2403
-1.250 0.0098 0.02167 0.01405 -0.0573 1.0000 0.6568
-1.000 0.0127 0.02069 0.01344 -0.0518 1.0000 1.0000
-0.750 0.0379 0.02115 0.01329 -0.0524 1.0000 1.0000
-0.500 0.0611 0.02166 0.01338 -0.0528 1.0000 1.0000
-0.250 0.0832 0.02223 0.01360 -0.0530 1.0000 1.0000
0.000 0.1046 0.02284 0.01392 -0.0532 1.0000 1.0000
0.250 0.1254 0.02351 0.01435 -0.0534 1.0000 1.0000
0.500 0.1456 0.02423 0.01486 -0.0535 1.0000 1.0000
0.750 0.1652 0.02501 0.01546 -0.0537 1.0000 1.0000
1.000 0.1990 0.02617 0.01642 -0.0565 0.9933 1.0000
1.250 0.2483 0.02758 0.01764 -0.0620 0.9765 1.0000
1.500 0.2973 0.02894 0.01885 -0.0672 0.9596 1.0000
1.750 0.3464 0.03022 0.02002 -0.0722 0.9425 1.0000
2.000 0.3851 0.03120 0.02094 -0.0752 0.9233 1.0000
2.250 0.4265 0.03215 0.02185 -0.0784 0.9042 1.0000
2.500 0.4715 0.03303 0.02271 -0.0818 0.8852 1.0000
2.750 0.5161 0.03376 0.02346 -0.0849 0.8661 1.0000
3.000 0.5500 0.03439 0.02412 -0.0861 0.8447 1.0000
3.250 0.5956 0.03476 0.02455 -0.0887 0.8248 1.0000
3.500 0.6367 0.03501 0.02489 -0.0903 0.8041 1.0000
3.750 0.6759 0.03509 0.02507 -0.0913 0.7823 1.0000
4.000 0.7332 0.03431 0.02444 -0.0938 0.7632 1.0000
4.250 0.7659 0.03412 0.02439 -0.0932 0.7396 1.0000
4.500 0.8167 0.03276 0.02318 -0.0936 0.7197 1.0000
4.750 0.8530 0.03196 0.02254 -0.0925 0.6958 1.0000
5.000 0.9025 0.03008 0.02079 -0.0918 0.6738 1.0000
5.250 0.9372 0.02910 0.01990 -0.0901 0.6457 1.0000
5.500 0.9728 0.02807 0.01892 -0.0883 0.6154 1.0000
5.750 1.0053 0.02738 0.01818 -0.0863 0.5819 1.0000
6.000 1.0306 0.02737 0.01812 -0.0841 0.5445 1.0000
6.250 1.0586 0.02739 0.01797 -0.0822 0.5074 1.0000
6.500 1.0800 0.02804 0.01852 -0.0801 0.4692 1.0000
6.750 1.1045 0.02870 0.01893 -0.0784 0.4336 1.0000
7.000 1.1248 0.02978 0.01992 -0.0767 0.3995 1.0000
7.250 1.1456 0.03096 0.02103 -0.0751 0.3681 1.0000
7.500 1.1670 0.03228 0.02224 -0.0737 0.3397 1.0000
7.750 1.1900 0.03364 0.02339 -0.0725 0.3136 1.0000
8.000 1.2073 0.03539 0.02531 -0.0710 0.2904 1.0000
8.250 1.2311 0.03698 0.02671 -0.0701 0.2692 1.0000
8.500 1.2478 0.03906 0.02902 -0.0686 0.2512 1.0000
8.750 1.2649 0.04111 0.03123 -0.0672 0.2344 1.0000
9.000 1.2828 0.04348 0.03376 -0.0659 0.2207 1.0000
9.250 1.3002 0.04584 0.03626 -0.0647 0.2079 1.0000
9.500 1.3206 0.04819 0.03859 -0.0638 0.1959 1.0000
9.750 1.3207 0.05184 0.04293 -0.0612 0.1893 1.0000
10.000 1.3385 0.05461 0.04574 -0.0602 0.1805 1.0000
10.250 1.3302 0.05862 0.05035 -0.0573 0.1755 1.0000
10.500 1.3556 0.06138 0.05298 -0.0571 0.1674 1.0000
10.750 1.3378 0.06623 0.05840 -0.0541 0.1660 1.0000
11.000 1.3153 0.07132 0.06391 -0.0515 0.1653 1.0000
11.250 1.2863 0.07657 0.06945 -0.0491 0.1654 1.0000
11.500 1.2542 0.08213 0.07519 -0.0474 0.1661 1.0000
11.750 1.2226 0.08867 0.08186 -0.0475 0.1670 1.0000
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Polar data table (+)
Polar graphs
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