SD7062 (14%) (sd7062-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: SD7062 (14%) (sd7062-il) Reynolds number: 100,000 Max Cl/Cd: 52.15 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sd7062-il-100000-n5.txt Download as CSV file: xf-sd7062-il-100000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2942 0.09424 0.08918 -0.0455 1.0000 0.0367
-9.500 -0.2976 0.09057 0.08559 -0.0463 1.0000 0.0363
-9.250 -0.3045 0.08674 0.08185 -0.0471 1.0000 0.0358
-8.750 -0.4051 0.06005 0.05517 -0.0681 0.9838 0.0327
-8.500 -0.4084 0.05171 0.04641 -0.0793 0.9638 0.0326
-8.250 -0.4032 0.04560 0.03977 -0.0854 0.9490 0.0329
-8.000 -0.3759 0.04359 0.03771 -0.0880 0.9409 0.0337
-7.750 -0.3592 0.04053 0.03432 -0.0899 0.9281 0.0343
-7.500 -0.3409 0.03739 0.03078 -0.0914 0.9168 0.0348
-7.250 -0.3182 0.03437 0.02729 -0.0928 0.9076 0.0352
-7.000 -0.2979 0.03203 0.02456 -0.0928 0.8959 0.0356
-6.750 -0.2721 0.02987 0.02200 -0.0934 0.8874 0.0361
-6.500 -0.2483 0.02813 0.01992 -0.0931 0.8766 0.0368
-6.250 -0.2219 0.02656 0.01801 -0.0931 0.8677 0.0376
-6.000 -0.1965 0.02544 0.01681 -0.0928 0.8577 0.0387
-5.750 -0.1706 0.02457 0.01585 -0.0926 0.8482 0.0403
-5.500 -0.1444 0.02363 0.01475 -0.0922 0.8387 0.0424
-5.250 -0.1191 0.02272 0.01372 -0.0916 0.8289 0.0440
-5.000 -0.0933 0.02191 0.01288 -0.0912 0.8198 0.0456
-4.750 -0.0686 0.02121 0.01211 -0.0905 0.8096 0.0478
-4.500 -0.0425 0.02050 0.01129 -0.0900 0.8009 0.0507
-4.250 -0.0179 0.01995 0.01072 -0.0894 0.7904 0.0551
-4.000 0.0085 0.01934 0.01006 -0.0890 0.7821 0.0618
-3.750 0.0331 0.01877 0.00949 -0.0884 0.7714 0.0712
-3.500 0.0596 0.01814 0.00888 -0.0879 0.7632 0.0902
-3.250 0.0844 0.01759 0.00848 -0.0875 0.7525 0.1249
-3.000 0.1103 0.01702 0.00813 -0.0872 0.7439 0.1819
-2.750 0.1350 0.01651 0.00794 -0.0868 0.7336 0.2620
-2.500 0.1605 0.01610 0.00778 -0.0863 0.7246 0.3376
-2.250 0.1860 0.01585 0.00768 -0.0856 0.7147 0.4014
-2.000 0.2116 0.01567 0.00759 -0.0849 0.7052 0.4594
-1.750 0.2374 0.01551 0.00752 -0.0841 0.6958 0.5114
-1.500 0.2628 0.01542 0.00748 -0.0832 0.6858 0.5573
-1.250 0.2884 0.01532 0.00740 -0.0822 0.6768 0.6004
-1.000 0.3131 0.01528 0.00740 -0.0812 0.6665 0.6409
-0.750 0.3388 0.01520 0.00729 -0.0801 0.6580 0.6800
-0.500 0.3627 0.01518 0.00732 -0.0788 0.6471 0.7169
-0.250 0.3873 0.01513 0.00725 -0.0775 0.6381 0.7534
0.000 0.4107 0.01510 0.00724 -0.0761 0.6278 0.7907
0.250 0.4346 0.01506 0.00720 -0.0746 0.6184 0.8302
0.500 0.4607 0.01502 0.00712 -0.0736 0.6085 0.8741
0.750 0.4946 0.01499 0.00706 -0.0743 0.5979 0.9228
1.000 0.5390 0.01497 0.00688 -0.0773 0.5876 0.9791
1.250 0.5683 0.01510 0.00689 -0.0779 0.5765 1.0000
1.500 0.5939 0.01526 0.00690 -0.0775 0.5667 1.0000
1.750 0.6198 0.01542 0.00692 -0.0771 0.5567 1.0000
2.000 0.6454 0.01562 0.00702 -0.0768 0.5463 1.0000
2.500 0.6971 0.01601 0.00719 -0.0760 0.5262 1.0000
2.750 0.7231 0.01622 0.00729 -0.0757 0.5166 1.0000
3.000 0.7487 0.01644 0.00742 -0.0752 0.5063 1.0000
3.250 0.7742 0.01669 0.00760 -0.0748 0.4963 1.0000
3.500 0.8000 0.01692 0.00772 -0.0744 0.4869 1.0000
3.750 0.8249 0.01719 0.00796 -0.0739 0.4762 1.0000
4.000 0.8504 0.01745 0.00813 -0.0735 0.4671 1.0000
4.250 0.8751 0.01774 0.00838 -0.0730 0.4567 1.0000
4.500 0.9000 0.01804 0.00862 -0.0725 0.4473 1.0000
4.750 0.9247 0.01834 0.00887 -0.0720 0.4377 1.0000
5.000 0.9489 0.01867 0.00918 -0.0714 0.4279 1.0000
5.250 0.9734 0.01899 0.00942 -0.0709 0.4192 1.0000
5.500 0.9969 0.01935 0.00981 -0.0702 0.4091 1.0000
5.750 1.0208 0.01971 0.01009 -0.0696 0.4006 1.0000
6.000 1.0438 0.02009 0.01050 -0.0689 0.3908 1.0000
6.250 1.0670 0.02048 0.01085 -0.0683 0.3821 1.0000
6.500 1.0895 0.02089 0.01127 -0.0675 0.3728 1.0000
6.750 1.1119 0.02132 0.01169 -0.0668 0.3643 1.0000
7.000 1.1337 0.02176 0.01213 -0.0659 0.3554 1.0000
7.250 1.1551 0.02223 0.01261 -0.0651 0.3468 1.0000
7.500 1.1761 0.02270 0.01307 -0.0642 0.3385 1.0000
7.750 1.1964 0.02321 0.01362 -0.0632 0.3301 1.0000
8.000 1.2163 0.02372 0.01412 -0.0622 0.3220 1.0000
8.250 1.2356 0.02428 0.01472 -0.0611 0.3140 1.0000
8.500 1.2540 0.02483 0.01528 -0.0599 0.3062 1.0000
8.750 1.2718 0.02544 0.01594 -0.0587 0.2984 1.0000
9.000 1.2887 0.02605 0.01658 -0.0574 0.2909 1.0000
9.250 1.3050 0.02671 0.01726 -0.0560 0.2838 1.0000
9.500 1.3186 0.02738 0.01800 -0.0542 0.2764 1.0000
9.750 1.3327 0.02807 0.01867 -0.0526 0.2702 1.0000
10.000 1.3443 0.02887 0.01958 -0.0507 0.2630 1.0000
10.250 1.3568 0.02966 0.02034 -0.0490 0.2569 1.0000
10.500 1.3674 0.03059 0.02140 -0.0473 0.2502 1.0000
10.750 1.3777 0.03153 0.02239 -0.0457 0.2440 1.0000
11.000 1.3882 0.03254 0.02342 -0.0441 0.2382 1.0000
11.250 1.3962 0.03370 0.02471 -0.0425 0.2318 1.0000
11.500 1.4058 0.03481 0.02582 -0.0412 0.2265 1.0000
11.750 1.4128 0.03616 0.02730 -0.0398 0.2206 1.0000
12.000 1.4191 0.03757 0.02880 -0.0385 0.2149 1.0000
12.250 1.4278 0.03888 0.03007 -0.0373 0.2101 1.0000
12.500 1.4313 0.04067 0.03205 -0.0362 0.2044 1.0000
12.750 1.4360 0.04237 0.03384 -0.0352 0.1992 1.0000
13.000 1.4423 0.04401 0.03547 -0.0344 0.1946 1.0000
13.250 1.4431 0.04624 0.03789 -0.0336 0.1893 1.0000
13.500 1.4458 0.04830 0.04003 -0.0330 0.1846 1.0000
13.750 1.4506 0.05023 0.04196 -0.0324 0.1803 1.0000
14.000 1.4480 0.05304 0.04498 -0.0322 0.1755 1.0000
14.250 1.4480 0.05560 0.04764 -0.0320 0.1711 1.0000
14.500 1.4536 0.05755 0.04957 -0.0316 0.1672 1.0000
14.750 1.4463 0.06119 0.05344 -0.0320 0.1628 1.0000
15.000 1.4426 0.06448 0.05686 -0.0323 0.1586 1.0000
15.250 1.4439 0.06715 0.05955 -0.0325 0.1548 1.0000
15.500 1.4397 0.07073 0.06326 -0.0332 0.1510 1.0000
15.750 1.4301 0.07519 0.06793 -0.0343 0.1471 1.0000
16.000 1.4261 0.07891 0.07174 -0.0353 0.1433 1.0000
16.250 1.4316 0.08122 0.07402 -0.0356 0.1399 1.0000
16.500 1.4128 0.08754 0.08061 -0.0379 0.1364 1.0000
16.750 1.3998 0.09308 0.08633 -0.0401 0.1329 1.0000
17.000 1.3979 0.09682 0.09011 -0.0414 0.1294 1.0000
17.250 1.3963 0.10054 0.09388 -0.0427 0.1263 1.0000
17.500 1.3658 0.10965 0.10327 -0.0471 0.1230 1.0000
17.750 1.3453 0.11715 0.11094 -0.0508 0.1196 1.0000
18.000 1.3540 0.11914 0.11291 -0.0515 0.1165 1.0000
18.250 1.3368 0.12623 0.12014 -0.0551 0.1135 1.0000
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Polar data table (+)
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