S6063 7.05% (s6063-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: S6063 7.05% (s6063-il) Reynolds number: 200,000 Max Cl/Cd: 61.5 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s6063-il-200000.txt Download as CSV file: xf-s6063-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: S6063 7.05%
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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.5351 0.08514 0.08179 -0.0081 1.0000 0.0445
-7.750 -0.5381 0.08101 0.07772 -0.0117 1.0000 0.0458
-7.500 -0.5383 0.07522 0.07194 -0.0208 1.0000 0.0472
-7.250 -0.4961 0.05516 0.05195 -0.0307 1.0000 0.0490
-7.000 -0.4828 0.05188 0.04880 -0.0277 1.0000 0.0506
-6.750 -0.4753 0.04816 0.04507 -0.0281 1.0000 0.0521
-6.500 -0.4687 0.04367 0.04049 -0.0300 1.0000 0.0541
-6.250 -0.4607 0.03866 0.03533 -0.0326 1.0000 0.0571
-6.000 -0.4562 0.03175 0.02785 -0.0365 1.0000 0.0622
-5.750 -0.4418 0.02838 0.02458 -0.0361 1.0000 0.0640
-5.500 -0.4268 0.02546 0.02158 -0.0359 1.0000 0.0672
-5.250 -0.4138 0.02161 0.01725 -0.0363 1.0000 0.0760
-5.000 -0.3987 0.01920 0.01488 -0.0354 1.0000 0.0790
-4.750 -0.3922 0.02556 0.01948 -0.0337 1.0000 0.0389
-4.500 -0.3702 0.02218 0.01568 -0.0320 1.0000 0.0306
-4.250 -0.3471 0.01949 0.01234 -0.0301 1.0000 0.0268
-4.000 -0.3248 0.01812 0.01074 -0.0286 1.0000 0.0262
-3.750 -0.3030 0.01650 0.00895 -0.0273 1.0000 0.0263
-3.500 -0.2821 0.01516 0.00758 -0.0262 1.0000 0.0299
-3.250 -0.2603 0.01422 0.00658 -0.0250 1.0000 0.0317
-3.000 -0.2385 0.01333 0.00564 -0.0238 1.0000 0.0329
-2.750 -0.2164 0.01263 0.00487 -0.0227 1.0000 0.0352
-2.500 -0.1936 0.01187 0.00405 -0.0218 1.0000 0.0436
-2.250 -0.1707 0.01029 0.00343 -0.0217 1.0000 0.2513
-2.000 -0.1513 0.00915 0.00343 -0.0208 1.0000 0.5214
-1.750 -0.1364 0.00845 0.00360 -0.0180 0.9995 0.7393
-1.500 -0.0861 0.00805 0.00360 -0.0211 0.9984 1.0000
-1.250 -0.0406 0.00816 0.00350 -0.0251 0.9914 1.0000
-1.000 0.0062 0.00826 0.00343 -0.0293 0.9847 1.0000
-0.750 0.0503 0.00831 0.00336 -0.0328 0.9764 1.0000
-0.500 0.0997 0.00833 0.00327 -0.0374 0.9709 1.0000
-0.250 0.1432 0.00830 0.00318 -0.0407 0.9618 1.0000
0.000 0.1871 0.00825 0.00308 -0.0439 0.9530 1.0000
0.250 0.2287 0.00818 0.00298 -0.0465 0.9433 1.0000
0.500 0.2614 0.00813 0.00291 -0.0472 0.9295 1.0000
0.750 0.2879 0.00812 0.00287 -0.0465 0.9132 1.0000
1.000 0.3119 0.00811 0.00284 -0.0452 0.8957 1.0000
1.250 0.3351 0.00812 0.00283 -0.0437 0.8779 1.0000
1.500 0.3581 0.00812 0.00280 -0.0421 0.8600 1.0000
1.750 0.3810 0.00815 0.00281 -0.0406 0.8391 1.0000
2.000 0.4045 0.00818 0.00280 -0.0392 0.8184 1.0000
2.250 0.4285 0.00823 0.00283 -0.0380 0.7946 1.0000
2.500 0.4527 0.00830 0.00289 -0.0368 0.7695 1.0000
2.750 0.4772 0.00840 0.00294 -0.0357 0.7417 1.0000
3.000 0.5017 0.00852 0.00300 -0.0346 0.7105 1.0000
3.250 0.5261 0.00868 0.00308 -0.0335 0.6733 1.0000
3.500 0.5492 0.00893 0.00316 -0.0321 0.6169 1.0000
3.750 0.5716 0.00933 0.00325 -0.0307 0.5414 1.0000
4.000 0.5945 0.00982 0.00345 -0.0297 0.4674 1.0000
4.250 0.6175 0.01040 0.00373 -0.0289 0.3884 1.0000
4.500 0.6379 0.01144 0.00413 -0.0280 0.2567 1.0000
4.750 0.6543 0.01361 0.00513 -0.0270 0.0541 1.0000
5.000 0.6770 0.01483 0.00630 -0.0261 0.0355 1.0000
5.250 0.7012 0.01564 0.00726 -0.0253 0.0327 1.0000
5.500 0.7243 0.01665 0.00837 -0.0244 0.0308 1.0000
5.750 0.7469 0.01782 0.00962 -0.0235 0.0298 1.0000
6.000 0.7697 0.01921 0.01111 -0.0225 0.0293 1.0000
6.250 0.7931 0.02064 0.01260 -0.0216 0.0281 1.0000
6.500 0.8156 0.02277 0.01478 -0.0209 0.0262 1.0000
6.750 0.8396 0.02501 0.01722 -0.0201 0.0261 1.0000
7.000 0.8637 0.02703 0.01950 -0.0192 0.0264 1.0000
7.250 0.8873 0.02946 0.02240 -0.0179 0.0279 1.0000
7.500 0.9045 0.03464 0.02838 -0.0158 0.0323 1.0000
11.500 0.8056 0.13110 0.12769 -0.0471 0.0519 1.0000
11.750 0.8090 0.13531 0.13190 -0.0486 0.0504 1.0000
12.000 0.8161 0.13879 0.13540 -0.0489 0.0490 1.0000
14.250 0.6688 0.16714 0.16408 -0.0605 0.0428 1.0000
14.500 0.6719 0.17033 0.16728 -0.0622 0.0403 1.0000
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Polar data table (+)
Polar graphs
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