SD7062 (14%) (sd7062-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD7062 (14%) (sd7062-il) Reynolds number: 200,000 Max Cl/Cd: 70.04 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd7062-il-200000.txt Download as CSV file: xf-sd7062-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.1905 0.08919 0.08618 -0.0444 0.9909 0.0697
-9.000 -0.1772 0.08453 0.08152 -0.0484 0.9860 0.0722
-8.750 -0.2248 0.07231 0.06932 -0.0676 0.9765 0.0762
-8.500 -0.2907 0.08857 0.08547 -0.0399 0.9974 0.0698
-8.250 -0.2727 0.08337 0.08027 -0.0476 0.9892 0.0736
-8.000 -0.2757 0.07225 0.06918 -0.0665 0.9741 0.0773
-7.750 -0.2430 0.07037 0.06729 -0.0669 0.9710 0.0788
-7.500 -0.2212 0.06606 0.06297 -0.0732 0.9604 0.0815
-7.250 -0.2806 0.03690 0.03173 -0.1006 0.9280 0.0500
-7.000 -0.2520 0.03534 0.03054 -0.1015 0.9201 0.0526
-6.750 -0.2438 0.02832 0.02200 -0.1006 0.9078 0.0435
-6.500 -0.2228 0.02621 0.01965 -0.0997 0.8964 0.0432
-6.250 -0.1984 0.02461 0.01769 -0.0991 0.8875 0.0435
-6.000 -0.1760 0.02282 0.01580 -0.0984 0.8765 0.0445
-5.750 -0.1513 0.02174 0.01463 -0.0977 0.8670 0.0455
-5.500 -0.1264 0.02063 0.01337 -0.0969 0.8569 0.0461
-5.250 -0.1014 0.01964 0.01223 -0.0960 0.8470 0.0469
-5.000 -0.0757 0.01873 0.01118 -0.0952 0.8376 0.0479
-4.750 -0.0505 0.01798 0.01032 -0.0943 0.8273 0.0491
-4.500 -0.0249 0.01714 0.00939 -0.0935 0.8186 0.0508
-4.250 -0.0003 0.01651 0.00883 -0.0928 0.8078 0.0536
-4.000 0.0264 0.01606 0.00824 -0.0921 0.7996 0.0576
-3.750 0.0507 0.01537 0.00764 -0.0914 0.7885 0.0624
-3.500 0.0766 0.01477 0.00701 -0.0908 0.7801 0.0709
-3.250 0.1016 0.01398 0.00639 -0.0902 0.7695 0.1024
-3.000 0.1266 0.01316 0.00597 -0.0899 0.7607 0.1942
-2.750 0.1522 0.01270 0.00577 -0.0895 0.7504 0.2741
-2.500 0.1783 0.01238 0.00566 -0.0891 0.7410 0.3492
-2.250 0.2040 0.01208 0.00561 -0.0885 0.7314 0.4328
-2.000 0.2296 0.01191 0.00563 -0.0878 0.7215 0.5029
-1.750 0.2561 0.01180 0.00556 -0.0871 0.7123 0.5529
-1.500 0.2820 0.01172 0.00556 -0.0863 0.7018 0.5948
-1.250 0.3085 0.01166 0.00549 -0.0855 0.6932 0.6356
-1.000 0.3338 0.01160 0.00551 -0.0846 0.6822 0.6741
-0.750 0.3595 0.01155 0.00547 -0.0836 0.6731 0.7108
-0.500 0.3842 0.01150 0.00547 -0.0825 0.6627 0.7469
-0.250 0.4084 0.01146 0.00547 -0.0811 0.6530 0.7835
0.000 0.4316 0.01141 0.00543 -0.0795 0.6433 0.8208
0.250 0.4536 0.01138 0.00543 -0.0777 0.6332 0.8592
0.500 0.4771 0.01132 0.00534 -0.0760 0.6242 0.9007
0.750 0.5113 0.01127 0.00528 -0.0767 0.6128 0.9457
1.000 0.5609 0.01127 0.00515 -0.0809 0.6016 0.9860
1.250 0.5935 0.01135 0.00507 -0.0821 0.5909 1.0000
1.500 0.6182 0.01149 0.00511 -0.0817 0.5802 1.0000
1.750 0.6448 0.01165 0.00509 -0.0814 0.5707 1.0000
2.000 0.6706 0.01178 0.00517 -0.0811 0.5595 1.0000
2.250 0.6972 0.01195 0.00523 -0.0808 0.5493 1.0000
2.500 0.7238 0.01212 0.00528 -0.0805 0.5392 1.0000
2.750 0.7500 0.01229 0.00540 -0.0802 0.5283 1.0000
3.000 0.7768 0.01250 0.00547 -0.0799 0.5187 1.0000
3.250 0.8028 0.01267 0.00561 -0.0795 0.5077 1.0000
3.500 0.8291 0.01289 0.00575 -0.0792 0.4976 1.0000
3.750 0.8554 0.01311 0.00587 -0.0789 0.4876 1.0000
4.000 0.8811 0.01332 0.00606 -0.0785 0.4769 1.0000
4.250 0.9073 0.01358 0.00621 -0.0781 0.4674 1.0000
4.500 0.9327 0.01380 0.00642 -0.0777 0.4568 1.0000
4.750 0.9583 0.01407 0.00663 -0.0773 0.4469 1.0000
5.000 0.9838 0.01433 0.00681 -0.0769 0.4372 1.0000
5.250 1.0087 0.01460 0.00709 -0.0764 0.4269 1.0000
5.500 1.0342 0.01492 0.00730 -0.0760 0.4179 1.0000
5.750 1.0584 0.01518 0.00759 -0.0754 0.4074 1.0000
6.000 1.0831 0.01552 0.00787 -0.0749 0.3983 1.0000
6.250 1.1073 0.01581 0.00815 -0.0743 0.3886 1.0000
6.500 1.1312 0.01616 0.00848 -0.0738 0.3792 1.0000
6.750 1.1552 0.01651 0.00877 -0.0732 0.3703 1.0000
7.000 1.1783 0.01686 0.00915 -0.0725 0.3607 1.0000
7.500 1.2239 0.01761 0.00989 -0.0710 0.3428 1.0000
7.750 1.2468 0.01806 0.01025 -0.0703 0.3346 1.0000
8.000 1.2680 0.01842 0.01069 -0.0694 0.3256 1.0000
8.250 1.2900 0.01891 0.01110 -0.0686 0.3176 1.0000
8.500 1.3102 0.01930 0.01157 -0.0675 0.3089 1.0000
8.750 1.3313 0.01983 0.01204 -0.0667 0.3013 1.0000
9.000 1.3502 0.02026 0.01254 -0.0654 0.2929 1.0000
9.250 1.3702 0.02082 0.01306 -0.0644 0.2855 1.0000
9.500 1.3875 0.02130 0.01362 -0.0630 0.2776 1.0000
9.750 1.4065 0.02192 0.01416 -0.0619 0.2706 1.0000
10.000 1.4212 0.02243 0.01479 -0.0601 0.2630 1.0000
10.250 1.4385 0.02308 0.01534 -0.0588 0.2564 1.0000
10.500 1.4491 0.02365 0.01606 -0.0564 0.2496 1.0000
10.750 1.4620 0.02430 0.01669 -0.0545 0.2432 1.0000
11.000 1.4742 0.02505 0.01749 -0.0527 0.2367 1.0000
11.250 1.4845 0.02578 0.01829 -0.0506 0.2304 1.0000
11.500 1.4985 0.02665 0.01909 -0.0492 0.2244 1.0000
11.750 1.5056 0.02753 0.02012 -0.0471 0.2182 1.0000
12.000 1.5161 0.02846 0.02103 -0.0455 0.2126 1.0000
12.250 1.5254 0.02953 0.02218 -0.0439 0.2069 1.0000
12.500 1.5322 0.03064 0.02338 -0.0422 0.2012 1.0000
12.750 1.5449 0.03174 0.02436 -0.0411 0.1956 1.0000
13.000 1.5480 0.03314 0.02598 -0.0394 0.1905 1.0000
13.250 1.5540 0.03450 0.02740 -0.0380 0.1854 1.0000
13.500 1.5641 0.03583 0.02867 -0.0370 0.1803 1.0000
13.750 1.5658 0.03758 0.03060 -0.0358 0.1755 1.0000
14.000 1.5701 0.03923 0.03230 -0.0348 0.1707 1.0000
14.250 1.5785 0.04079 0.03383 -0.0339 0.1660 1.0000
14.500 1.5783 0.04293 0.03615 -0.0331 0.1616 1.0000
14.750 1.5808 0.04492 0.03822 -0.0324 0.1573 1.0000
15.000 1.5895 0.04656 0.03978 -0.0318 0.1528 1.0000
15.250 1.5859 0.04926 0.04269 -0.0314 0.1490 1.0000
15.500 1.5861 0.05168 0.04521 -0.0311 0.1449 1.0000
15.750 1.5930 0.05353 0.04700 -0.0308 0.1408 1.0000
16.000 1.5897 0.05655 0.05020 -0.0308 0.1373 1.0000
16.250 1.5866 0.05962 0.05341 -0.0310 0.1336 1.0000
16.500 1.5871 0.06233 0.05615 -0.0313 0.1300 1.0000
16.750 1.5912 0.06473 0.05855 -0.0313 0.1263 1.0000
17.000 1.5832 0.06872 0.06276 -0.0321 0.1231 1.0000
17.250 1.5801 0.07218 0.06631 -0.0329 0.1197 1.0000
17.500 1.5843 0.07462 0.06873 -0.0333 0.1163 1.0000
17.750 1.5796 0.07846 0.07269 -0.0342 0.1133 1.0000
18.000 1.5701 0.08310 0.07753 -0.0358 0.1103 1.0000
18.250 1.5663 0.08694 0.08145 -0.0371 0.1073 1.0000
18.500 1.5757 0.08868 0.08308 -0.0372 0.1038 1.0000
18.750 1.5626 0.09415 0.08878 -0.0394 0.1015 1.0000
19.000 1.5500 0.09967 0.09450 -0.0418 0.0990 1.0000
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Polar data table (+)
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