S6062 8% (s6062-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: S6062 8% (s6062-il) Reynolds number: 200,000 Max Cl/Cd: 65.25 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s6062-il-200000.txt Download as CSV file: xf-s6062-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5256 0.09278 0.08940 -0.0169 1.0000 0.0441
-8.500 -0.5288 0.08819 0.08486 -0.0221 1.0000 0.0443
-8.250 -0.5342 0.08303 0.07969 -0.0279 1.0000 0.0444
-8.000 -0.5361 0.07836 0.07493 -0.0319 1.0000 0.0445
-7.750 -0.5328 0.07277 0.06951 -0.0292 1.0000 0.0460
-7.500 -0.5249 0.06999 0.06675 -0.0287 1.0000 0.0472
-7.250 -0.5188 0.06629 0.06303 -0.0304 1.0000 0.0486
-7.000 -0.5126 0.06208 0.05875 -0.0328 1.0000 0.0504
-6.750 -0.5053 0.05744 0.05399 -0.0356 1.0000 0.0529
-6.500 -0.5031 0.05234 0.04815 -0.0394 1.0000 0.0574
-6.250 -0.4914 0.04730 0.04330 -0.0392 1.0000 0.0591
-6.000 -0.4776 0.04468 0.04069 -0.0385 1.0000 0.0611
-5.750 -0.4649 0.04196 0.03783 -0.0378 1.0000 0.0646
-5.500 -0.4563 0.03847 0.03385 -0.0368 1.0000 0.0720
-5.000 -0.4234 0.02796 0.02189 -0.0310 1.0000 0.0331
-4.750 -0.4089 0.02367 0.01733 -0.0294 1.0000 0.0294
-4.500 -0.3902 0.02094 0.01415 -0.0275 1.0000 0.0273
-4.250 -0.3697 0.01890 0.01174 -0.0258 1.0000 0.0264
-4.000 -0.3490 0.01750 0.01014 -0.0244 1.0000 0.0270
-3.750 -0.3285 0.01668 0.00922 -0.0231 1.0000 0.0294
-3.500 -0.3074 0.01578 0.00821 -0.0219 1.0000 0.0312
-3.250 -0.2729 0.01465 0.00697 -0.0232 0.9966 0.0324
-3.000 -0.2352 0.01331 0.00560 -0.0254 0.9917 0.0372
-2.750 -0.1972 0.01179 0.00451 -0.0277 0.9864 0.1274
-2.500 -0.1624 0.01041 0.00431 -0.0303 0.9809 0.3936
-2.250 -0.1332 0.00931 0.00437 -0.0306 0.9739 0.6771
-2.000 -0.1029 0.00902 0.00452 -0.0299 0.9675 0.8301
-1.750 -0.0657 0.00899 0.00454 -0.0307 0.9617 0.9118
-1.500 -0.0082 0.00902 0.00445 -0.0360 0.9609 0.9603
-1.250 0.0568 0.00897 0.00423 -0.0433 0.9613 0.9859
-1.000 0.1180 0.00884 0.00397 -0.0502 0.9599 1.0000
-0.750 0.1574 0.00873 0.00376 -0.0527 0.9499 1.0000
-0.500 0.1932 0.00862 0.00357 -0.0544 0.9386 1.0000
-0.250 0.2222 0.00854 0.00343 -0.0545 0.9251 1.0000
0.000 0.2456 0.00850 0.00332 -0.0535 0.9101 1.0000
0.250 0.2666 0.00849 0.00324 -0.0518 0.8948 1.0000
0.500 0.2872 0.00848 0.00318 -0.0501 0.8797 1.0000
0.750 0.3079 0.00849 0.00313 -0.0483 0.8645 1.0000
1.000 0.3291 0.00851 0.00309 -0.0466 0.8493 1.0000
1.250 0.3509 0.00853 0.00307 -0.0450 0.8337 1.0000
1.500 0.3734 0.00855 0.00304 -0.0436 0.8179 1.0000
1.750 0.3965 0.00859 0.00303 -0.0423 0.8015 1.0000
2.000 0.4202 0.00865 0.00305 -0.0412 0.7833 1.0000
2.250 0.4443 0.00870 0.00309 -0.0401 0.7650 1.0000
2.500 0.4687 0.00877 0.00311 -0.0391 0.7467 1.0000
2.750 0.4935 0.00886 0.00318 -0.0382 0.7254 1.0000
3.000 0.5182 0.00896 0.00322 -0.0373 0.7044 1.0000
3.250 0.5432 0.00907 0.00331 -0.0364 0.6797 1.0000
3.500 0.5681 0.00921 0.00345 -0.0356 0.6535 1.0000
3.750 0.5931 0.00937 0.00357 -0.0348 0.6257 1.0000
4.000 0.6179 0.00957 0.00372 -0.0340 0.5952 1.0000
4.250 0.6414 0.00983 0.00383 -0.0330 0.5471 1.0000
4.500 0.6632 0.01025 0.00398 -0.0317 0.4731 1.0000
4.750 0.6861 0.01074 0.00424 -0.0308 0.4123 1.0000
5.000 0.7084 0.01135 0.00459 -0.0300 0.3430 1.0000
5.250 0.7294 0.01219 0.00505 -0.0292 0.2573 1.0000
5.500 0.7484 0.01347 0.00573 -0.0283 0.1430 1.0000
5.750 0.7639 0.01559 0.00715 -0.0268 0.0430 1.0000
6.000 0.7861 0.01655 0.00820 -0.0259 0.0365 1.0000
6.250 0.8056 0.01793 0.00965 -0.0246 0.0333 1.0000
6.500 0.8271 0.01905 0.01087 -0.0235 0.0320 1.0000
6.750 0.8484 0.02037 0.01229 -0.0224 0.0309 1.0000
7.000 0.8705 0.02192 0.01396 -0.0214 0.0303 1.0000
7.250 0.8935 0.02352 0.01568 -0.0205 0.0293 1.0000
7.500 0.9163 0.02494 0.01723 -0.0197 0.0276 1.0000
7.750 0.9389 0.02694 0.01942 -0.0188 0.0270 1.0000
8.000 0.9609 0.02948 0.02228 -0.0178 0.0272 1.0000
8.250 0.9798 0.03288 0.02616 -0.0163 0.0281 1.0000
8.500 0.9932 0.03728 0.03114 -0.0143 0.0299 1.0000
8.750 1.0012 0.04235 0.03667 -0.0126 0.0320 1.0000
11.000 0.8252 0.10932 0.10603 -0.0306 0.0642 1.0000
11.250 0.8190 0.11552 0.11220 -0.0342 0.0623 1.0000
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Polar data table (+)
Polar graphs
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