S6063 7.05% (s6063-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: S6063 7.05% (s6063-il) Reynolds number: 500,000 Max Cl/Cd: 60.19 at α=2° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s6063-il-500000-n5.txt Download as CSV file: xf-s6063-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.5591 0.07473 0.07260 -0.0108 1.0000 0.0066
-7.750 -0.5634 0.06900 0.06690 -0.0168 1.0000 0.0063
-7.500 -0.5601 0.06246 0.06032 -0.0233 1.0000 0.0063
-7.250 -0.5545 0.05541 0.05315 -0.0286 1.0000 0.0063
-7.000 -0.5457 0.04878 0.04636 -0.0322 1.0000 0.0064
-6.000 -0.4882 0.02799 0.02431 -0.0351 1.0000 0.0067
-5.750 -0.4714 0.02402 0.01989 -0.0343 1.0000 0.0064
-5.500 -0.4523 0.02110 0.01658 -0.0333 0.9997 0.0063
-5.250 -0.4213 0.01834 0.01338 -0.0345 0.9931 0.0061
-5.000 -0.3897 0.01627 0.01093 -0.0355 0.9870 0.0061
-4.750 -0.3580 0.01465 0.00904 -0.0363 0.9810 0.0061
-4.500 -0.3267 0.01336 0.00754 -0.0371 0.9741 0.0061
-4.250 -0.2961 0.01231 0.00634 -0.0377 0.9666 0.0063
-4.000 -0.2659 0.01147 0.00539 -0.0381 0.9584 0.0065
-3.750 -0.2378 0.01083 0.00463 -0.0381 0.9484 0.0068
-3.500 -0.2103 0.01036 0.00409 -0.0379 0.9379 0.0071
-3.250 -0.1842 0.00968 0.00329 -0.0375 0.9270 0.0077
-3.000 -0.1582 0.00923 0.00275 -0.0370 0.9161 0.0095
-2.750 -0.1318 0.00896 0.00238 -0.0365 0.9047 0.0102
-2.500 -0.1052 0.00874 0.00206 -0.0361 0.8934 0.0109
-2.250 -0.0786 0.00856 0.00180 -0.0356 0.8816 0.0123
-2.000 -0.0522 0.00829 0.00157 -0.0352 0.8692 0.0351
-1.750 -0.0264 0.00782 0.00137 -0.0349 0.8561 0.1164
-1.500 -0.0007 0.00735 0.00122 -0.0347 0.8426 0.2213
-1.250 0.0251 0.00690 0.00112 -0.0344 0.8287 0.3366
-1.000 0.0491 0.00615 0.00106 -0.0340 0.8141 0.5450
-0.750 0.0747 0.00589 0.00102 -0.0335 0.7983 0.6296
-0.500 0.1000 0.00568 0.00099 -0.0328 0.7814 0.7047
-0.250 0.1249 0.00552 0.00098 -0.0320 0.7636 0.7711
0.000 0.1494 0.00542 0.00098 -0.0309 0.7450 0.8276
0.250 0.1733 0.00535 0.00098 -0.0297 0.7250 0.8795
0.500 0.1991 0.00535 0.00098 -0.0289 0.7035 0.9264
0.750 0.2323 0.00541 0.00096 -0.0298 0.6780 0.9609
1.000 0.2685 0.00551 0.00095 -0.0316 0.6491 0.9858
1.250 0.3013 0.00564 0.00095 -0.0328 0.6192 1.0000
1.500 0.3273 0.00580 0.00100 -0.0324 0.5902 1.0000
1.750 0.3534 0.00597 0.00105 -0.0320 0.5603 1.0000
2.000 0.3786 0.00629 0.00112 -0.0316 0.5020 1.0000
2.250 0.4027 0.00684 0.00123 -0.0311 0.4044 1.0000
2.500 0.4281 0.00722 0.00138 -0.0308 0.3451 1.0000
2.750 0.4537 0.00762 0.00154 -0.0306 0.2866 1.0000
3.000 0.4788 0.00812 0.00174 -0.0303 0.2173 1.0000
3.250 0.5033 0.00878 0.00201 -0.0300 0.1322 1.0000
3.500 0.5269 0.00966 0.00244 -0.0297 0.0360 1.0000
3.750 0.5529 0.01008 0.00275 -0.0294 0.0137 1.0000
4.000 0.5796 0.01033 0.00303 -0.0292 0.0120 1.0000
4.250 0.6061 0.01061 0.00336 -0.0290 0.0111 1.0000
4.500 0.6325 0.01094 0.00377 -0.0287 0.0105 1.0000
4.750 0.6587 0.01131 0.00421 -0.0284 0.0100 1.0000
5.000 0.6846 0.01174 0.00471 -0.0281 0.0097 1.0000
5.250 0.7101 0.01224 0.00528 -0.0277 0.0095 1.0000
5.500 0.7353 0.01281 0.00592 -0.0273 0.0092 1.0000
5.750 0.7600 0.01345 0.00665 -0.0269 0.0086 1.0000
6.000 0.7836 0.01430 0.00758 -0.0263 0.0080 1.0000
6.250 0.8065 0.01529 0.00866 -0.0256 0.0077 1.0000
6.500 0.8283 0.01660 0.01009 -0.0248 0.0075 1.0000
6.750 0.8499 0.01812 0.01175 -0.0239 0.0072 1.0000
7.000 0.8734 0.01909 0.01285 -0.0233 0.0071 1.0000
7.250 0.8966 0.02015 0.01405 -0.0227 0.0069 1.0000
7.500 0.9190 0.02145 0.01552 -0.0219 0.0068 1.0000
7.750 0.9404 0.02301 0.01731 -0.0211 0.0067 1.0000
8.000 0.9607 0.02481 0.01936 -0.0202 0.0066 1.0000
8.250 0.9793 0.02691 0.02173 -0.0192 0.0065 1.0000
8.500 0.9957 0.02932 0.02446 -0.0180 0.0065 1.0000
8.750 1.0092 0.03208 0.02756 -0.0167 0.0065 1.0000
9.000 1.0193 0.03514 0.03097 -0.0153 0.0065 1.0000
9.250 1.0280 0.03796 0.03409 -0.0139 0.0064 1.0000
9.500 1.0317 0.04121 0.03766 -0.0123 0.0063 1.0000
9.750 1.0323 0.04438 0.04110 -0.0107 0.0061 1.0000
10.000 1.0266 0.04767 0.04464 -0.0089 0.0059 1.0000
10.250 1.0098 0.05105 0.04822 -0.0066 0.0059 1.0000
10.500 0.9905 0.05516 0.05252 -0.0063 0.0060 1.0000
10.750 0.9698 0.06051 0.05803 -0.0087 0.0060 1.0000
11.000 0.9495 0.06745 0.06512 -0.0138 0.0061 1.0000
11.250 0.9245 0.07821 0.07604 -0.0229 0.0062 1.0000
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Polar data table (+)
Polar graphs
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