SD7043 (9.1%) (sd7043-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: SD7043 (9.1%) (sd7043-il) Reynolds number: 1,000,000 Max Cl/Cd: 105.61 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sd7043-il-1000000-n5.txt Download as CSV file: xf-sd7043-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.4259 0.14097 0.13915 -0.0165 1.0000 0.0038
-12.750 -0.4201 0.13781 0.13599 -0.0177 1.0000 0.0038
-10.750 -0.6895 0.03068 0.02839 -0.0911 0.9736 0.0046
-10.500 -0.6763 0.02593 0.02322 -0.0948 0.9607 0.0046
-10.250 -0.6589 0.02359 0.02061 -0.0956 0.9510 0.0047
-10.000 -0.6398 0.02174 0.01852 -0.0958 0.9429 0.0049
-9.750 -0.6193 0.02012 0.01667 -0.0959 0.9353 0.0050
-9.500 -0.5979 0.01867 0.01498 -0.0958 0.9288 0.0051
-9.250 -0.5745 0.01752 0.01363 -0.0958 0.9228 0.0053
-9.000 -0.5506 0.01647 0.01240 -0.0958 0.9169 0.0054
-8.750 -0.5260 0.01555 0.01130 -0.0956 0.9116 0.0055
-8.500 -0.5005 0.01474 0.01035 -0.0956 0.9062 0.0057
-8.250 -0.4747 0.01408 0.00954 -0.0955 0.9008 0.0058
-8.000 -0.4487 0.01336 0.00867 -0.0954 0.8959 0.0059
-7.750 -0.4225 0.01260 0.00780 -0.0954 0.8904 0.0062
-7.500 -0.3959 0.01209 0.00719 -0.0953 0.8851 0.0065
-7.250 -0.3688 0.01168 0.00670 -0.0953 0.8802 0.0067
-7.000 -0.3414 0.01129 0.00625 -0.0952 0.8747 0.0070
-6.750 -0.3142 0.01092 0.00579 -0.0952 0.8693 0.0073
-6.500 -0.2866 0.01055 0.00535 -0.0951 0.8643 0.0077
-6.250 -0.2589 0.01021 0.00493 -0.0951 0.8588 0.0080
-6.000 -0.2313 0.00987 0.00451 -0.0950 0.8536 0.0085
-5.750 -0.2033 0.00961 0.00423 -0.0951 0.8485 0.0092
-5.500 -0.1753 0.00942 0.00401 -0.0950 0.8427 0.0099
-5.000 -0.1191 0.00896 0.00344 -0.0950 0.8314 0.0113
-4.750 -0.0911 0.00874 0.00319 -0.0950 0.8251 0.0122
-4.500 -0.0629 0.00857 0.00299 -0.0950 0.8191 0.0131
-4.250 -0.0346 0.00840 0.00278 -0.0949 0.8122 0.0141
-4.000 -0.0065 0.00825 0.00257 -0.0949 0.8058 0.0149
-3.750 0.0219 0.00804 0.00235 -0.0949 0.7985 0.0163
-3.500 0.0500 0.00791 0.00218 -0.0949 0.7912 0.0175
-3.250 0.0784 0.00777 0.00200 -0.0949 0.7828 0.0184
-3.000 0.1067 0.00764 0.00182 -0.0949 0.7745 0.0196
-2.750 0.1350 0.00749 0.00164 -0.0949 0.7650 0.0213
-2.500 0.1633 0.00738 0.00149 -0.0948 0.7554 0.0229
-2.250 0.1916 0.00731 0.00136 -0.0948 0.7449 0.0242
-2.000 0.2198 0.00721 0.00124 -0.0947 0.7329 0.0282
-1.750 0.2479 0.00710 0.00114 -0.0947 0.7196 0.0419
-1.500 0.2760 0.00697 0.00105 -0.0947 0.7052 0.0712
-1.250 0.3040 0.00686 0.00099 -0.0947 0.6899 0.1035
-1.000 0.3319 0.00674 0.00094 -0.0947 0.6737 0.1480
-0.750 0.3598 0.00666 0.00091 -0.0947 0.6565 0.1908
-0.500 0.3875 0.00656 0.00089 -0.0947 0.6376 0.2440
-0.250 0.4152 0.00650 0.00090 -0.0947 0.6171 0.2978
0.000 0.4427 0.00640 0.00092 -0.0948 0.5964 0.3775
0.250 0.4702 0.00630 0.00097 -0.0948 0.5742 0.4583
0.500 0.4975 0.00628 0.00102 -0.0947 0.5521 0.5236
0.750 0.5250 0.00631 0.00108 -0.0946 0.5300 0.5695
1.000 0.5521 0.00635 0.00116 -0.0945 0.5065 0.6216
1.250 0.5791 0.00640 0.00124 -0.0943 0.4826 0.6733
1.500 0.6059 0.00648 0.00134 -0.0941 0.4585 0.7179
1.750 0.6324 0.00658 0.00144 -0.0938 0.4333 0.7617
2.000 0.6583 0.00667 0.00156 -0.0933 0.4079 0.8098
2.250 0.6831 0.00677 0.00168 -0.0926 0.3823 0.8590
2.500 0.7054 0.00683 0.00178 -0.0913 0.3584 0.9206
2.750 0.7350 0.00697 0.00187 -0.0917 0.3341 1.0000
3.000 0.7617 0.00723 0.00201 -0.0915 0.3096 1.0000
3.250 0.7884 0.00748 0.00214 -0.0913 0.2861 1.0000
3.500 0.8150 0.00774 0.00229 -0.0911 0.2650 1.0000
3.750 0.8417 0.00797 0.00244 -0.0909 0.2472 1.0000
4.000 0.8681 0.00825 0.00262 -0.0907 0.2273 1.0000
4.250 0.8945 0.00852 0.00279 -0.0905 0.2095 1.0000
4.500 0.9208 0.00878 0.00297 -0.0903 0.1926 1.0000
4.750 0.9471 0.00905 0.00317 -0.0901 0.1780 1.0000
5.000 0.9732 0.00932 0.00337 -0.0898 0.1635 1.0000
5.250 0.9990 0.00962 0.00359 -0.0895 0.1479 1.0000
5.500 1.0248 0.00991 0.00381 -0.0892 0.1354 1.0000
5.750 1.0506 0.01019 0.00405 -0.0889 0.1250 1.0000
6.000 1.0764 0.01046 0.00428 -0.0887 0.1157 1.0000
6.250 1.1020 0.01075 0.00453 -0.0883 0.1060 1.0000
6.500 1.1272 0.01107 0.00480 -0.0880 0.0970 1.0000
6.750 1.1525 0.01137 0.00507 -0.0876 0.0895 1.0000
7.000 1.1777 0.01167 0.00535 -0.0872 0.0829 1.0000
7.250 1.2022 0.01203 0.00567 -0.0868 0.0747 1.0000
7.500 1.2272 0.01233 0.00597 -0.0864 0.0694 1.0000
7.750 1.2513 0.01271 0.00631 -0.0859 0.0629 1.0000
8.000 1.2757 0.01303 0.00664 -0.0854 0.0581 1.0000
8.250 1.2993 0.01344 0.00701 -0.0848 0.0527 1.0000
8.500 1.3234 0.01377 0.00736 -0.0843 0.0494 1.0000
8.750 1.3466 0.01418 0.00776 -0.0837 0.0452 1.0000
9.000 1.3696 0.01458 0.00817 -0.0830 0.0416 1.0000
9.250 1.3928 0.01495 0.00856 -0.0824 0.0394 1.0000
9.500 1.4149 0.01540 0.00902 -0.0816 0.0364 1.0000
9.750 1.4367 0.01586 0.00948 -0.0808 0.0337 1.0000
10.000 1.4589 0.01626 0.00992 -0.0800 0.0323 1.0000
10.250 1.4802 0.01671 0.01040 -0.0791 0.0303 1.0000
10.500 1.5003 0.01724 0.01094 -0.0781 0.0282 1.0000
10.750 1.5203 0.01775 0.01148 -0.0771 0.0265 1.0000
11.000 1.5402 0.01821 0.01199 -0.0760 0.0253 1.0000
11.250 1.5587 0.01875 0.01255 -0.0748 0.0234 1.0000
11.500 1.5751 0.01938 0.01319 -0.0732 0.0214 1.0000
11.750 1.5904 0.01991 0.01377 -0.0714 0.0204 1.0000
12.000 1.6045 0.02049 0.01440 -0.0694 0.0191 1.0000
12.250 1.6173 0.02115 0.01509 -0.0674 0.0179 1.0000
12.500 1.6288 0.02192 0.01589 -0.0653 0.0165 1.0000
12.750 1.6413 0.02264 0.01667 -0.0634 0.0157 1.0000
13.000 1.6530 0.02344 0.01753 -0.0615 0.0148 1.0000
13.250 1.6635 0.02435 0.01848 -0.0596 0.0138 1.0000
13.500 1.6729 0.02537 0.01955 -0.0577 0.0129 1.0000
13.750 1.6826 0.02640 0.02066 -0.0560 0.0122 1.0000
14.000 1.6918 0.02750 0.02183 -0.0543 0.0115 1.0000
14.250 1.6994 0.02878 0.02317 -0.0526 0.0105 1.0000
14.500 1.7052 0.03025 0.02469 -0.0510 0.0097 1.0000
14.750 1.7119 0.03170 0.02622 -0.0495 0.0091 1.0000
15.000 1.7175 0.03330 0.02790 -0.0482 0.0084 1.0000
15.250 1.7213 0.03513 0.02980 -0.0469 0.0077 1.0000
15.500 1.7235 0.03720 0.03195 -0.0458 0.0071 1.0000
15.750 1.7258 0.03934 0.03418 -0.0448 0.0067 1.0000
16.000 1.7271 0.04168 0.03662 -0.0441 0.0063 1.0000
16.250 1.7262 0.04438 0.03942 -0.0436 0.0057 1.0000
16.500 1.7225 0.04753 0.04266 -0.0433 0.0051 1.0000
16.750 1.7199 0.05070 0.04595 -0.0434 0.0048 1.0000
17.000 1.7155 0.05430 0.04966 -0.0437 0.0044 1.0000
17.250 1.7087 0.05841 0.05388 -0.0445 0.0041 1.0000
17.500 1.6995 0.06308 0.05867 -0.0457 0.0037 1.0000
17.750 1.6890 0.06823 0.06394 -0.0474 0.0034 1.0000
18.000 1.6775 0.07373 0.06959 -0.0495 0.0033 1.0000
18.250 1.6641 0.07983 0.07582 -0.0521 0.0031 1.0000
18.500 1.6475 0.08675 0.08289 -0.0553 0.0030 1.0000
18.750 1.6291 0.09423 0.09052 -0.0589 0.0029 1.0000
19.000 1.6082 0.10247 0.09892 -0.0632 0.0029 1.0000
19.250 1.5854 0.11132 0.10794 -0.0680 0.0029 1.0000
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Polar data table (+)
Polar graphs
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