S6062 8% (s6062-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: S6062 8% (s6062-il) Reynolds number: 100,000 Max Cl/Cd: 50.44 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s6062-il-100000.txt Download as CSV file: xf-s6062-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: S6062 8%
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5270 0.11791 0.11292 0.0005 1.0000 0.0805
-9.750 -0.5375 0.11541 0.11051 -0.0050 1.0000 0.0826
-9.500 -0.5490 0.11270 0.10789 -0.0107 1.0000 0.0831
-9.250 -0.5219 0.10634 0.10148 -0.0054 1.0000 0.0859
-9.000 -0.5129 0.10281 0.09796 -0.0054 1.0000 0.0894
-8.750 -0.5116 0.09939 0.09458 -0.0075 1.0000 0.0929
-8.500 -0.5278 0.09635 0.09167 -0.0144 1.0000 0.0960
-8.250 -0.4269 0.08244 0.07806 -0.0149 1.0000 0.1081
-8.000 -0.4543 0.07871 0.07445 -0.0215 1.0000 0.1099
-7.750 -0.4814 0.07409 0.06985 -0.0289 1.0000 0.1103
-7.500 -0.4281 0.07000 0.06573 -0.0180 1.0000 0.1179
-7.250 -0.5207 0.07537 0.07088 -0.0259 1.0000 0.1123
-7.000 -0.5080 0.07238 0.06792 -0.0241 1.0000 0.1167
-6.750 -0.5147 0.06721 0.06259 -0.0323 1.0000 0.1251
-6.500 -0.4985 0.06408 0.05954 -0.0293 1.0000 0.1290
-6.250 -0.4946 0.05984 0.05515 -0.0327 1.0000 0.1399
-6.000 -0.4866 0.05663 0.05178 -0.0341 1.0000 0.1528
-5.750 -0.4757 0.05363 0.04875 -0.0336 1.0000 0.1669
-5.250 -0.4402 0.03877 0.03275 -0.0364 1.0000 0.0887
-5.000 -0.4198 0.03191 0.02442 -0.0342 1.0000 0.0578
-4.750 -0.4006 0.02918 0.02142 -0.0327 1.0000 0.0556
-4.500 -0.3814 0.02632 0.01822 -0.0312 1.0000 0.0537
-4.250 -0.3605 0.02397 0.01550 -0.0297 1.0000 0.0527
-4.000 -0.3387 0.02200 0.01320 -0.0281 1.0000 0.0529
-3.750 -0.3166 0.02040 0.01138 -0.0267 1.0000 0.0542
-3.500 -0.2946 0.01912 0.00991 -0.0252 1.0000 0.0567
-3.250 -0.2743 0.01772 0.00861 -0.0240 1.0000 0.0654
-3.000 -0.2537 0.01655 0.00748 -0.0226 1.0000 0.0816
-2.750 -0.2348 0.01378 0.00608 -0.0215 1.0000 0.2900
-2.500 -0.2252 0.01207 0.00625 -0.0175 1.0000 0.6751
-2.250 -0.2115 0.01182 0.00646 -0.0123 1.0000 0.8837
-2.000 -0.1301 0.01178 0.00594 -0.0220 1.0000 1.0000
-1.750 -0.1216 0.01181 0.00575 -0.0195 1.0000 1.0000
-1.500 -0.1077 0.01191 0.00563 -0.0179 1.0000 1.0000
-1.250 -0.0913 0.01206 0.00558 -0.0168 1.0000 1.0000
-1.000 -0.0738 0.01225 0.00559 -0.0158 1.0000 1.0000
-0.750 -0.0556 0.01248 0.00564 -0.0151 1.0000 1.0000
-0.500 -0.0107 0.01288 0.00586 -0.0194 0.9913 1.0000
-0.250 0.0390 0.01329 0.00612 -0.0244 0.9812 1.0000
0.000 0.0896 0.01364 0.00634 -0.0295 0.9709 1.0000
0.250 0.1364 0.01389 0.00652 -0.0337 0.9591 1.0000
0.500 0.1831 0.01410 0.00668 -0.0378 0.9471 1.0000
0.750 0.2309 0.01424 0.00680 -0.0419 0.9354 1.0000
1.000 0.2809 0.01429 0.00687 -0.0463 0.9240 1.0000
1.250 0.3269 0.01429 0.00691 -0.0496 0.9117 1.0000
1.500 0.3672 0.01427 0.00694 -0.0517 0.8977 1.0000
1.750 0.4016 0.01424 0.00695 -0.0524 0.8819 1.0000
2.000 0.4325 0.01420 0.00695 -0.0522 0.8653 1.0000
2.250 0.4609 0.01412 0.00696 -0.0514 0.8483 1.0000
2.500 0.4875 0.01404 0.00690 -0.0501 0.8313 1.0000
2.750 0.5102 0.01404 0.00696 -0.0483 0.8108 1.0000
3.000 0.5342 0.01398 0.00692 -0.0465 0.7912 1.0000
3.250 0.5573 0.01395 0.00694 -0.0446 0.7697 1.0000
3.500 0.5810 0.01388 0.00694 -0.0427 0.7476 1.0000
3.750 0.6041 0.01388 0.00698 -0.0409 0.7219 1.0000
4.000 0.6274 0.01388 0.00701 -0.0391 0.6943 1.0000
4.250 0.6508 0.01390 0.00705 -0.0373 0.6643 1.0000
4.500 0.6740 0.01399 0.00719 -0.0356 0.6302 1.0000
4.750 0.6970 0.01413 0.00731 -0.0339 0.5925 1.0000
5.000 0.7183 0.01430 0.00741 -0.0319 0.5393 1.0000
5.250 0.7375 0.01462 0.00748 -0.0298 0.4652 1.0000
5.500 0.7554 0.01529 0.00776 -0.0279 0.3716 1.0000
5.750 0.7721 0.01642 0.00838 -0.0263 0.2604 1.0000
6.000 0.7793 0.01959 0.01022 -0.0238 0.0931 1.0000
6.250 0.7960 0.02151 0.01200 -0.0220 0.0706 1.0000
6.500 0.8158 0.02308 0.01360 -0.0205 0.0616 1.0000
6.750 0.8361 0.02496 0.01539 -0.0194 0.0553 1.0000
7.000 0.8605 0.02680 0.01738 -0.0184 0.0524 1.0000
7.250 0.8858 0.02898 0.01976 -0.0175 0.0506 1.0000
7.500 0.9106 0.03150 0.02254 -0.0167 0.0497 1.0000
7.750 0.9333 0.03449 0.02593 -0.0155 0.0497 1.0000
8.000 0.9523 0.03799 0.02998 -0.0141 0.0507 1.0000
8.250 0.9672 0.04182 0.03435 -0.0125 0.0516 1.0000
8.500 0.9780 0.04561 0.03864 -0.0109 0.0515 1.0000
8.750 0.9845 0.04977 0.04328 -0.0093 0.0518 1.0000
9.000 0.9872 0.05451 0.04843 -0.0079 0.0534 1.0000
9.250 0.9908 0.05989 0.05399 -0.0070 0.0555 1.0000
9.500 0.9611 0.06648 0.06141 -0.0051 0.0636 1.0000
9.750 0.9388 0.07296 0.06820 -0.0047 0.0726 1.0000
10.000 0.8991 0.07942 0.07482 -0.0068 0.0757 1.0000
10.250 0.8085 0.07385 0.06947 -0.0033 0.0655 1.0000
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Polar data table (+)
Polar graphs
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