S2062 8% (s2062-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: S2062 8% (s2062-il) Reynolds number: 200,000 Max Cl/Cd: 61.85 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s2062-il-200000-n5.txt Download as CSV file: xf-s2062-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S2062 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5245 0.07884 0.07533 -0.0277 1.0000 0.0114
-8.750 -0.5326 0.07347 0.07003 -0.0307 1.0000 0.0113
-8.500 -0.5454 0.06761 0.06425 -0.0343 1.0000 0.0112
-8.250 -0.5572 0.06067 0.05733 -0.0405 1.0000 0.0110
-8.000 -0.5688 0.05217 0.04869 -0.0451 1.0000 0.0108
-7.750 -0.5782 0.04551 0.04177 -0.0466 1.0000 0.0106
-7.500 -0.5827 0.03965 0.03551 -0.0467 1.0000 0.0105
-7.250 -0.5812 0.03468 0.03005 -0.0458 1.0000 0.0104
-7.000 -0.5740 0.03049 0.02534 -0.0445 1.0000 0.0104
-6.750 -0.5620 0.02719 0.02152 -0.0430 1.0000 0.0104
-6.500 -0.5465 0.02457 0.01846 -0.0416 1.0000 0.0105
-6.250 -0.5288 0.02247 0.01597 -0.0403 1.0000 0.0106
-6.000 -0.5097 0.02073 0.01393 -0.0390 1.0000 0.0108
-5.750 -0.4896 0.01928 0.01218 -0.0378 1.0000 0.0111
-5.500 -0.4664 0.01804 0.01073 -0.0371 0.9994 0.0114
-5.250 -0.4347 0.01666 0.00918 -0.0383 0.9964 0.0121
-5.000 -0.4024 0.01574 0.00815 -0.0397 0.9933 0.0139
-4.750 -0.3702 0.01507 0.00736 -0.0409 0.9896 0.0162
-4.500 -0.3371 0.01424 0.00639 -0.0422 0.9861 0.0193
-4.250 -0.3028 0.01349 0.00561 -0.0437 0.9832 0.0291
-4.000 -0.2721 0.01293 0.00510 -0.0445 0.9784 0.0517
-3.750 -0.2393 0.01250 0.00481 -0.0459 0.9742 0.0849
-3.500 -0.2045 0.01209 0.00451 -0.0476 0.9709 0.1165
-3.250 -0.1732 0.01173 0.00419 -0.0485 0.9658 0.1461
-3.000 -0.1404 0.01139 0.00393 -0.0498 0.9610 0.1814
-2.750 -0.1051 0.01101 0.00370 -0.0516 0.9574 0.2317
-2.500 -0.0739 0.01064 0.00350 -0.0525 0.9516 0.2867
-2.250 -0.0418 0.01024 0.00331 -0.0535 0.9460 0.3573
-2.000 -0.0090 0.00981 0.00316 -0.0547 0.9410 0.4413
-1.750 0.0190 0.00938 0.00307 -0.0547 0.9332 0.5348
-1.500 0.0491 0.00895 0.00301 -0.0550 0.9274 0.6400
-1.250 0.0747 0.00870 0.00302 -0.0540 0.9185 0.7266
-1.000 0.1023 0.00854 0.00299 -0.0534 0.9105 0.7875
-0.750 0.1301 0.00841 0.00294 -0.0528 0.9017 0.8329
-0.500 0.1567 0.00832 0.00288 -0.0519 0.8911 0.8701
-0.250 0.1864 0.00824 0.00281 -0.0517 0.8809 0.9033
0.000 0.2209 0.00816 0.00271 -0.0526 0.8706 0.9332
0.250 0.2590 0.00809 0.00261 -0.0544 0.8586 0.9593
0.500 0.2986 0.00803 0.00251 -0.0567 0.8447 0.9814
0.750 0.3365 0.00799 0.00242 -0.0587 0.8285 1.0000
1.000 0.3609 0.00802 0.00239 -0.0578 0.8099 1.0000
1.250 0.3859 0.00806 0.00237 -0.0570 0.7903 1.0000
1.500 0.4108 0.00812 0.00236 -0.0563 0.7687 1.0000
1.750 0.4360 0.00821 0.00237 -0.0555 0.7452 1.0000
2.000 0.4611 0.00832 0.00241 -0.0547 0.7187 1.0000
2.250 0.4859 0.00847 0.00245 -0.0539 0.6892 1.0000
2.500 0.5106 0.00865 0.00252 -0.0531 0.6564 1.0000
2.750 0.5348 0.00888 0.00261 -0.0522 0.6203 1.0000
3.000 0.5589 0.00914 0.00276 -0.0513 0.5808 1.0000
3.250 0.5826 0.00945 0.00291 -0.0504 0.5390 1.0000
3.500 0.6061 0.00980 0.00310 -0.0496 0.4961 1.0000
3.750 0.6295 0.01019 0.00333 -0.0487 0.4520 1.0000
4.250 0.6732 0.01132 0.00392 -0.0468 0.3235 1.0000
4.500 0.6951 0.01196 0.00427 -0.0459 0.2602 1.0000
4.750 0.7178 0.01258 0.00466 -0.0452 0.2074 1.0000
5.000 0.7391 0.01339 0.00512 -0.0445 0.1406 1.0000
5.250 0.7612 0.01417 0.00563 -0.0438 0.0911 1.0000
5.500 0.7833 0.01497 0.00627 -0.0430 0.0517 1.0000
5.750 0.8055 0.01579 0.00699 -0.0422 0.0306 1.0000
6.000 0.8285 0.01651 0.00773 -0.0414 0.0248 1.0000
6.250 0.8514 0.01724 0.00856 -0.0406 0.0226 1.0000
6.500 0.8740 0.01797 0.00944 -0.0397 0.0214 1.0000
6.750 0.8960 0.01878 0.01037 -0.0388 0.0203 1.0000
7.000 0.9177 0.01961 0.01128 -0.0379 0.0189 1.0000
7.250 0.9383 0.02056 0.01236 -0.0370 0.0174 1.0000
7.500 0.9569 0.02186 0.01375 -0.0357 0.0167 1.0000
7.750 0.9748 0.02349 0.01548 -0.0343 0.0161 1.0000
8.000 0.9951 0.02479 0.01693 -0.0333 0.0158 1.0000
8.250 1.0152 0.02627 0.01859 -0.0322 0.0155 1.0000
8.500 1.0349 0.02795 0.02048 -0.0311 0.0152 1.0000
8.750 1.0537 0.02984 0.02261 -0.0299 0.0149 1.0000
9.000 1.0712 0.03166 0.02474 -0.0287 0.0142 1.0000
9.250 1.0872 0.03341 0.02676 -0.0274 0.0134 1.0000
9.500 1.1008 0.03546 0.02908 -0.0259 0.0128 1.0000
9.750 1.1112 0.03790 0.03184 -0.0241 0.0124 1.0000
10.000 1.1179 0.04048 0.03475 -0.0221 0.0121 1.0000
10.250 1.1206 0.04324 0.03782 -0.0199 0.0119 1.0000
10.500 1.1180 0.04607 0.04095 -0.0173 0.0117 1.0000
10.750 1.1093 0.04886 0.04400 -0.0143 0.0116 1.0000
11.000 1.0970 0.05201 0.04740 -0.0119 0.0115 1.0000
11.250 1.0824 0.05556 0.05118 -0.0105 0.0114 1.0000
11.500 1.0650 0.05986 0.05572 -0.0103 0.0114 1.0000
11.750 1.0461 0.06497 0.06104 -0.0118 0.0114 1.0000
12.000 1.0253 0.07123 0.06751 -0.0151 0.0114 1.0000
12.250 0.9981 0.08017 0.07668 -0.0212 0.0117 1.0000
12.500 0.9623 0.09362 0.09036 -0.0313 0.0121 1.0000
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Polar data table (+)
Polar graphs
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