S6063 7.05% (s6063-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: S6063 7.05% (s6063-il) Reynolds number: 200,000 Max Cl/Cd: 53.43 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s6063-il-200000-n5.txt Download as CSV file: xf-s6063-il-200000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.5425 0.06315 0.05978 -0.0260 1.0000 0.0182
-7.000 -0.5360 0.05801 0.05455 -0.0291 1.0000 0.0169
-6.750 -0.5290 0.05046 0.04677 -0.0329 1.0000 0.0150
-6.500 -0.5163 0.04247 0.03833 -0.0348 1.0000 0.0125
-6.250 -0.5030 0.03788 0.03342 -0.0355 1.0000 0.0122
-6.000 -0.4873 0.03359 0.02874 -0.0356 1.0000 0.0118
-5.750 -0.4695 0.02975 0.02447 -0.0353 1.0000 0.0115
-5.500 -0.4501 0.02648 0.02074 -0.0346 1.0000 0.0113
-5.250 -0.4296 0.02366 0.01742 -0.0336 1.0000 0.0111
-5.000 -0.4083 0.02135 0.01470 -0.0325 1.0000 0.0110
-4.750 -0.3866 0.01945 0.01245 -0.0313 1.0000 0.0110
-4.500 -0.3647 0.01788 0.01062 -0.0301 1.0000 0.0112
-4.250 -0.3429 0.01658 0.00912 -0.0289 1.0000 0.0114
-4.000 -0.3214 0.01551 0.00791 -0.0276 1.0000 0.0118
-3.750 -0.2938 0.01476 0.00704 -0.0277 0.9974 0.0129
-3.500 -0.2604 0.01355 0.00571 -0.0292 0.9916 0.0145
-3.250 -0.2252 0.01282 0.00486 -0.0308 0.9861 0.0154
-3.000 -0.1902 0.01227 0.00418 -0.0323 0.9801 0.0167
-2.750 -0.1552 0.01183 0.00362 -0.0338 0.9736 0.0193
-2.500 -0.1218 0.01121 0.00313 -0.0351 0.9660 0.0512
-2.250 -0.0897 0.01019 0.00284 -0.0367 0.9585 0.2153
-2.000 -0.0596 0.00957 0.00266 -0.0375 0.9490 0.3373
-1.750 -0.0335 0.00858 0.00262 -0.0375 0.9396 0.5742
-1.500 -0.0082 0.00806 0.00260 -0.0364 0.9300 0.7213
-1.250 0.0166 0.00784 0.00257 -0.0350 0.9185 0.8035
-1.000 0.0441 0.00770 0.00252 -0.0342 0.9073 0.8716
-0.750 0.0794 0.00762 0.00242 -0.0351 0.8968 0.9255
-0.500 0.1205 0.00755 0.00227 -0.0375 0.8858 0.9655
-0.250 0.1614 0.00749 0.00212 -0.0401 0.8732 0.9941
0.000 0.1893 0.00750 0.00204 -0.0400 0.8573 1.0000
0.250 0.2133 0.00753 0.00199 -0.0390 0.8402 1.0000
0.500 0.2376 0.00757 0.00194 -0.0381 0.8223 1.0000
0.750 0.2621 0.00762 0.00191 -0.0372 0.8040 1.0000
1.000 0.2870 0.00769 0.00190 -0.0364 0.7838 1.0000
1.250 0.3120 0.00777 0.00190 -0.0356 0.7629 1.0000
1.500 0.3372 0.00786 0.00193 -0.0348 0.7394 1.0000
1.750 0.3625 0.00797 0.00195 -0.0341 0.7138 1.0000
2.000 0.3878 0.00811 0.00200 -0.0334 0.6861 1.0000
2.250 0.4132 0.00827 0.00207 -0.0327 0.6564 1.0000
2.500 0.4385 0.00846 0.00218 -0.0321 0.6245 1.0000
2.750 0.4638 0.00868 0.00229 -0.0314 0.5881 1.0000
3.000 0.4866 0.00914 0.00238 -0.0304 0.5094 1.0000
3.250 0.5095 0.00970 0.00254 -0.0295 0.4226 1.0000
3.500 0.5342 0.01012 0.00280 -0.0291 0.3701 1.0000
3.750 0.5584 0.01066 0.00308 -0.0286 0.3043 1.0000
4.000 0.5811 0.01150 0.00345 -0.0281 0.2056 1.0000
4.250 0.6044 0.01233 0.00391 -0.0277 0.1252 1.0000
4.500 0.6257 0.01363 0.00465 -0.0272 0.0281 1.0000
4.750 0.6506 0.01425 0.00525 -0.0267 0.0192 1.0000
5.000 0.6759 0.01477 0.00588 -0.0263 0.0174 1.0000
5.250 0.7008 0.01537 0.00661 -0.0258 0.0163 1.0000
5.500 0.7254 0.01605 0.00742 -0.0253 0.0155 1.0000
5.750 0.7493 0.01684 0.00833 -0.0247 0.0149 1.0000
6.000 0.7724 0.01776 0.00941 -0.0240 0.0145 1.0000
6.250 0.7948 0.01882 0.01058 -0.0232 0.0142 1.0000
6.500 0.8168 0.02004 0.01190 -0.0224 0.0140 1.0000
6.750 0.8376 0.02168 0.01364 -0.0215 0.0132 1.0000
7.000 0.8592 0.02338 0.01550 -0.0207 0.0126 1.0000
7.250 0.8818 0.02480 0.01712 -0.0199 0.0122 1.0000
7.500 0.9034 0.02661 0.01919 -0.0191 0.0120 1.0000
7.750 0.9239 0.02870 0.02158 -0.0181 0.0119 1.0000
8.000 0.9427 0.03110 0.02439 -0.0171 0.0117 1.0000
8.250 0.9589 0.03386 0.02756 -0.0159 0.0116 1.0000
8.500 0.9721 0.03694 0.03106 -0.0146 0.0116 1.0000
8.750 0.9814 0.04038 0.03493 -0.0132 0.0117 1.0000
9.000 0.9863 0.04413 0.03910 -0.0117 0.0117 1.0000
9.250 0.9864 0.04807 0.04341 -0.0103 0.0118 1.0000
9.500 0.9810 0.05211 0.04778 -0.0089 0.0119 1.0000
9.750 0.9692 0.05597 0.05190 -0.0074 0.0120 1.0000
10.000 0.9524 0.05974 0.05586 -0.0065 0.0120 1.0000
10.250 0.9343 0.06427 0.06056 -0.0077 0.0121 1.0000
10.500 0.9156 0.07005 0.06649 -0.0114 0.0121 1.0000
10.750 0.8966 0.07764 0.07421 -0.0176 0.0122 1.0000
11.000 0.8776 0.08760 0.08427 -0.0257 0.0123 1.0000
11.250 0.8593 0.09916 0.09586 -0.0333 0.0125 1.0000
11.500 0.8479 0.10798 0.10465 -0.0379 0.0127 1.0000
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Polar data table (+)
Polar graphs
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