SD7062 (14%) (sd7062-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD7062 (14%) (sd7062-il) Reynolds number: 100,000 Max Cl/Cd: 47.63 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd7062-il-100000.txt Download as CSV file: xf-sd7062-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: SD7062 (14%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2591 0.10158 0.09693 -0.0384 1.0000 0.1255
-8.750 -0.3090 0.10178 0.09738 -0.0404 1.0000 0.1277
-8.500 -0.3489 0.10218 0.09797 -0.0369 1.0000 0.1279
-8.250 -0.2988 0.09633 0.09207 -0.0331 1.0000 0.1307
-8.000 -0.3110 0.09579 0.09163 -0.0287 1.0000 0.1321
-7.750 -0.3284 0.09542 0.09137 -0.0247 1.0000 0.1335
-7.500 -0.3340 0.09387 0.08989 -0.0243 0.9978 0.1370
-7.250 -0.3436 0.08773 0.08380 -0.0403 0.9828 0.1447
-7.000 -0.2961 0.08505 0.08108 -0.0372 0.9807 0.1508
-6.750 -0.2988 0.07857 0.07462 -0.0523 0.9632 0.1612
-6.500 -0.2597 0.07624 0.07228 -0.0505 0.9593 0.1672
-6.250 -0.2500 0.07024 0.06624 -0.0618 0.9454 0.1790
-6.000 -0.2723 0.04442 0.03870 -0.0853 0.9278 0.0852
-5.750 -0.2499 0.03836 0.03147 -0.0875 0.9183 0.0758
-5.500 -0.2141 0.03496 0.02774 -0.0901 0.9112 0.0748
-5.250 -0.1682 0.03185 0.02413 -0.0938 0.9071 0.0745
-5.000 -0.1431 0.03032 0.02218 -0.0934 0.8957 0.0757
-4.750 -0.1000 0.02814 0.01988 -0.0962 0.8907 0.0790
-4.500 -0.0730 0.02701 0.01864 -0.0959 0.8800 0.0818
-4.250 -0.0321 0.02548 0.01689 -0.0974 0.8738 0.0857
-4.000 -0.0050 0.02435 0.01579 -0.0970 0.8636 0.0908
-3.750 0.0304 0.02320 0.01466 -0.0977 0.8562 0.1019
-3.500 0.0556 0.02231 0.01389 -0.0969 0.8458 0.1174
-3.250 0.0859 0.02093 0.01284 -0.0969 0.8380 0.1682
-3.000 0.1073 0.01990 0.01242 -0.0959 0.8269 0.2762
-2.750 0.1359 0.01914 0.01219 -0.0955 0.8192 0.4062
-2.500 0.1566 0.01904 0.01236 -0.0937 0.8075 0.4904
-2.250 0.1856 0.01873 0.01218 -0.0925 0.8003 0.5607
-2.000 0.2055 0.01879 0.01235 -0.0904 0.7882 0.6132
-1.750 0.2331 0.01855 0.01214 -0.0887 0.7811 0.6660
-1.500 0.2518 0.01862 0.01228 -0.0862 0.7688 0.7099
-1.250 0.2739 0.01853 0.01221 -0.0837 0.7598 0.7539
-1.000 0.2936 0.01843 0.01214 -0.0808 0.7497 0.7958
-0.750 0.3119 0.01840 0.01212 -0.0777 0.7396 0.8400
-0.500 0.3355 0.01815 0.01184 -0.0751 0.7308 0.8850
-0.250 0.3727 0.01806 0.01169 -0.0758 0.7197 0.9327
0.000 0.4413 0.01765 0.01102 -0.0823 0.7111 0.9723
0.250 0.5035 0.01752 0.01071 -0.0894 0.6978 1.0000
0.500 0.5127 0.01764 0.01069 -0.0870 0.6876 1.0000
0.750 0.5329 0.01767 0.01053 -0.0858 0.6778 1.0000
1.000 0.5539 0.01792 0.01065 -0.0849 0.6663 1.0000
1.250 0.5831 0.01786 0.01037 -0.0846 0.6581 1.0000
1.500 0.6055 0.01816 0.01059 -0.0838 0.6456 1.0000
1.750 0.6314 0.01833 0.01063 -0.0833 0.6352 1.0000
2.000 0.6593 0.01840 0.01054 -0.0830 0.6254 1.0000
2.250 0.6834 0.01870 0.01077 -0.0824 0.6137 1.0000
2.500 0.7127 0.01875 0.01065 -0.0821 0.6048 1.0000
2.750 0.7371 0.01902 0.01088 -0.0815 0.5929 1.0000
3.000 0.7627 0.01929 0.01106 -0.0810 0.5822 1.0000
3.250 0.7916 0.01937 0.01099 -0.0807 0.5727 1.0000
3.500 0.8151 0.01974 0.01135 -0.0800 0.5608 1.0000
3.750 0.8424 0.01994 0.01145 -0.0797 0.5510 1.0000
4.000 0.8685 0.02018 0.01161 -0.0792 0.5402 1.0000
4.250 0.8928 0.02055 0.01196 -0.0785 0.5291 1.0000
4.500 0.9227 0.02068 0.01191 -0.0785 0.5202 1.0000
4.750 0.9446 0.02112 0.01241 -0.0776 0.5082 1.0000
5.000 0.9703 0.02147 0.01270 -0.0771 0.4981 1.0000
5.250 0.9972 0.02171 0.01285 -0.0767 0.4881 1.0000
5.500 1.0198 0.02219 0.01338 -0.0759 0.4770 1.0000
5.750 1.0484 0.02245 0.01348 -0.0758 0.4681 1.0000
6.000 1.0701 0.02292 0.01401 -0.0749 0.4568 1.0000
6.250 1.0945 0.02337 0.01446 -0.0743 0.4469 1.0000
6.500 1.1210 0.02369 0.01468 -0.0740 0.4373 1.0000
6.750 1.1418 0.02427 0.01534 -0.0730 0.4266 1.0000
7.000 1.1707 0.02458 0.01550 -0.0730 0.4180 1.0000
7.250 1.1894 0.02520 0.01625 -0.0717 0.4072 1.0000
7.500 1.2138 0.02570 0.01672 -0.0712 0.3980 1.0000
7.750 1.2370 0.02618 0.01720 -0.0705 0.3884 1.0000
8.000 1.2575 0.02685 0.01793 -0.0695 0.3789 1.0000
8.250 1.2843 0.02723 0.01819 -0.0693 0.3701 1.0000
8.500 1.3007 0.02804 0.01918 -0.0679 0.3605 1.0000
8.750 1.3308 0.02841 0.01934 -0.0681 0.3523 1.0000
9.000 1.3427 0.02931 0.02049 -0.0661 0.3426 1.0000
9.250 1.3700 0.02981 0.02087 -0.0660 0.3346 1.0000
9.500 1.3830 0.03068 0.02193 -0.0642 0.3255 1.0000
9.750 1.4081 0.03129 0.02246 -0.0639 0.3176 1.0000
10.000 1.4209 0.03219 0.02353 -0.0621 0.3091 1.0000
10.250 1.4449 0.03286 0.02413 -0.0616 0.3013 1.0000
10.500 1.4557 0.03383 0.02527 -0.0596 0.2932 1.0000
10.750 1.4805 0.03453 0.02589 -0.0594 0.2857 1.0000
11.000 1.4867 0.03567 0.02725 -0.0569 0.2781 1.0000
11.250 1.5153 0.03627 0.02770 -0.0571 0.2707 1.0000
11.500 1.5140 0.03769 0.02941 -0.0539 0.2638 1.0000
11.750 1.5485 0.03810 0.02960 -0.0548 0.2563 1.0000
12.000 1.5385 0.03981 0.03167 -0.0506 0.2504 1.0000
12.250 1.5533 0.04063 0.03250 -0.0493 0.2438 1.0000
12.500 1.5635 0.04188 0.03380 -0.0475 0.2378 1.0000
12.750 1.5543 0.04357 0.03570 -0.0438 0.2325 1.0000
13.000 1.5948 0.04386 0.03577 -0.0453 0.2250 1.0000
13.250 1.5693 0.04628 0.03853 -0.0405 0.2213 1.0000
13.500 1.5607 0.04831 0.04075 -0.0378 0.2165 1.0000
13.750 1.5978 0.04850 0.04074 -0.0385 0.2095 1.0000
14.000 1.5678 0.05183 0.04442 -0.0350 0.2063 1.0000
14.250 1.5509 0.05490 0.04770 -0.0330 0.2023 1.0000
14.500 1.5981 0.05414 0.04669 -0.0336 0.1950 1.0000
14.750 1.5594 0.05880 0.05173 -0.0312 0.1927 1.0000
15.000 1.5212 0.06438 0.05761 -0.0303 0.1901 1.0000
15.250 1.4892 0.07013 0.06359 -0.0305 0.1871 1.0000
15.500 1.5483 0.06705 0.06027 -0.0294 0.1799 1.0000
15.750 1.4832 0.07650 0.07012 -0.0307 0.1790 1.0000
16.500 1.4649 0.08775 0.08161 -0.0326 0.1670 1.0000
16.750 0.9443 0.20443 0.19842 -0.1011 0.2046 1.0000
17.000 0.9582 0.20698 0.20102 -0.1016 0.1989 1.0000
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Polar data table (+)
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