S8065 (11% version of S8064) (s8065-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: S8065 (11% version of S8064) (s8065-il) Reynolds number: 50,000 Max Cl/Cd: 31.82 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s8065-il-50000.txt Download as CSV file: xf-s8065-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: S8065 (11% version of S8064)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.6214 0.06927 0.06284 -0.0398 1.0000 0.1308
-7.750 -0.6544 0.06496 0.05818 -0.0369 1.0000 0.1193
-7.500 -0.6565 0.06125 0.05440 -0.0345 1.0000 0.1168
-7.250 -0.6632 0.05747 0.05039 -0.0318 1.0000 0.1132
-7.000 -0.6774 0.05353 0.04564 -0.0281 1.0000 0.1062
-6.750 -0.6724 0.04992 0.04176 -0.0257 1.0000 0.1054
-6.500 -0.6654 0.04642 0.03793 -0.0233 1.0000 0.1042
-6.250 -0.6566 0.04302 0.03407 -0.0208 1.0000 0.1037
-6.000 -0.6447 0.03999 0.03049 -0.0184 1.0000 0.1050
-5.750 -0.6298 0.03722 0.02748 -0.0166 1.0000 0.1107
-5.500 -0.6124 0.03485 0.02469 -0.0146 1.0000 0.1182
-5.250 -0.5933 0.03251 0.02218 -0.0130 1.0000 0.1298
-5.000 -0.5725 0.03033 0.01974 -0.0113 1.0000 0.1468
-4.750 -0.5509 0.02828 0.01773 -0.0098 1.0000 0.1725
-4.500 -0.5291 0.02639 0.01601 -0.0083 1.0000 0.2100
-4.250 -0.5090 0.02445 0.01449 -0.0065 1.0000 0.2716
-4.000 -0.4965 0.02193 0.01324 -0.0035 1.0000 0.4123
-3.750 -0.4996 0.02108 0.01408 0.0065 1.0000 0.6768
-3.500 -0.4939 0.02199 0.01502 0.0152 1.0000 0.7892
-3.250 -0.4548 0.02366 0.01629 0.0193 1.0000 0.8751
-3.000 -0.1396 0.02606 0.01669 -0.0269 1.0000 0.9876
-2.750 -0.0987 0.02523 0.01555 -0.0322 1.0000 1.0000
-2.500 -0.1016 0.02479 0.01502 -0.0291 1.0000 1.0000
-2.250 -0.1044 0.02438 0.01453 -0.0260 1.0000 1.0000
-2.000 -0.1071 0.02400 0.01407 -0.0228 1.0000 1.0000
-1.750 -0.1096 0.02366 0.01366 -0.0194 1.0000 1.0000
-1.500 -0.1118 0.02335 0.01327 -0.0160 1.0000 1.0000
-1.250 -0.1138 0.02307 0.01291 -0.0125 1.0000 1.0000
-1.000 -0.1154 0.02281 0.01257 -0.0090 1.0000 1.0000
-0.750 -0.1162 0.02259 0.01225 -0.0055 1.0000 1.0000
-0.500 -0.1152 0.02242 0.01198 -0.0022 1.0000 1.0000
-0.250 -0.1114 0.02233 0.01179 0.0006 1.0000 1.0000
0.000 -0.1047 0.02232 0.01167 0.0030 1.0000 1.0000
0.250 -0.0952 0.02241 0.01166 0.0050 1.0000 1.0000
0.500 -0.0835 0.02259 0.01173 0.0066 1.0000 1.0000
0.750 -0.0701 0.02284 0.01187 0.0079 1.0000 1.0000
1.000 -0.0556 0.02315 0.01209 0.0089 1.0000 1.0000
1.250 -0.0402 0.02351 0.01239 0.0099 1.0000 1.0000
1.500 -0.0245 0.02392 0.01275 0.0106 1.0000 1.0000
1.750 -0.0084 0.02439 0.01317 0.0113 1.0000 1.0000
2.000 0.0079 0.02490 0.01365 0.0119 1.0000 1.0000
2.250 0.0244 0.02547 0.01420 0.0124 1.0000 1.0000
2.500 0.0407 0.02608 0.01480 0.0128 1.0000 1.0000
2.750 0.0571 0.02675 0.01548 0.0132 1.0000 1.0000
3.000 0.0733 0.02747 0.01622 0.0134 1.0000 1.0000
3.250 0.1076 0.02882 0.01764 0.0101 0.9917 1.0000
3.500 0.1630 0.03082 0.01977 0.0029 0.9718 1.0000
3.750 0.2084 0.03233 0.02145 -0.0022 0.9507 1.0000
4.000 0.2607 0.03402 0.02331 -0.0081 0.9287 1.0000
4.250 0.3007 0.03515 0.02463 -0.0115 0.9048 1.0000
4.500 0.3437 0.03622 0.02595 -0.0149 0.8795 1.0000
4.750 0.3899 0.03707 0.02706 -0.0184 0.8524 1.0000
5.000 0.4383 0.03751 0.02780 -0.0214 0.8230 1.0000
5.250 0.4991 0.03711 0.02786 -0.0249 0.7899 1.0000
5.500 0.5630 0.03536 0.02660 -0.0269 0.7511 1.0000
5.750 0.6683 0.02929 0.02144 -0.0290 0.7010 1.0000
6.000 0.7250 0.02444 0.01707 -0.0245 0.6241 1.0000
6.250 0.7439 0.02338 0.01478 -0.0164 0.4153 1.0000
6.500 0.7464 0.02587 0.01598 -0.0117 0.2984 1.0000
6.750 0.7714 0.02830 0.01783 -0.0107 0.2344 1.0000
7.000 0.8038 0.03063 0.01995 -0.0108 0.1967 1.0000
7.250 0.8344 0.03306 0.02228 -0.0108 0.1715 1.0000
7.500 0.8621 0.03572 0.02518 -0.0103 0.1553 1.0000
7.750 0.8838 0.03837 0.02803 -0.0091 0.1413 1.0000
8.000 0.9061 0.04154 0.03134 -0.0082 0.1315 1.0000
8.250 0.9195 0.04428 0.03452 -0.0060 0.1228 1.0000
8.500 0.9330 0.04789 0.03842 -0.0042 0.1174 1.0000
8.750 0.9374 0.05150 0.04261 -0.0013 0.1152 1.0000
9.000 0.9384 0.05507 0.04665 0.0015 0.1127 1.0000
9.250 0.9402 0.05854 0.05042 0.0039 0.1095 1.0000
9.500 0.9356 0.06252 0.05475 0.0065 0.1091 1.0000
9.750 0.9173 0.06689 0.05953 0.0095 0.1113 1.0000
10.000 0.8979 0.07129 0.06419 0.0120 0.1136 1.0000
10.250 0.8783 0.07550 0.06854 0.0141 0.1155 1.0000
10.500 0.8647 0.08019 0.07330 0.0151 0.1175 1.0000
10.750 0.8411 0.08510 0.07834 0.0150 0.1208 1.0000
11.000 0.7881 0.09396 0.08724 0.0102 0.1310 1.0000
11.250 0.7935 0.09973 0.09304 0.0095 0.1333 1.0000
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Polar data table (+)
Polar graphs
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