S8064 (s8064-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: S8064 (s8064-il) Reynolds number: 50,000 Max Cl/Cd: 30.97 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s8064-il-50000.txt Download as CSV file: xf-s8064-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4325 0.10549 0.09866 -0.0255 1.0000 0.3235
-9.500 -0.5632 0.08416 0.07777 -0.0518 1.0000 0.1389
-9.250 -0.5721 0.07968 0.07332 -0.0508 1.0000 0.1294
-9.000 -0.6156 0.07722 0.07092 -0.0472 1.0000 0.1272
-8.750 -0.6673 0.07495 0.06859 -0.0424 1.0000 0.1247
-8.500 -0.6741 0.07123 0.06481 -0.0399 1.0000 0.1192
-8.250 -0.6929 0.06777 0.06124 -0.0366 1.0000 0.1156
-8.000 -0.7380 0.06449 0.05727 -0.0310 1.0000 0.1091
-7.750 -0.7321 0.06035 0.05311 -0.0290 1.0000 0.1071
-7.500 -0.7344 0.05667 0.04921 -0.0261 1.0000 0.1050
-7.250 -0.7365 0.05306 0.04525 -0.0231 1.0000 0.1030
-7.000 -0.7356 0.04949 0.04124 -0.0200 1.0000 0.1018
-6.750 -0.7302 0.04637 0.03768 -0.0172 1.0000 0.1031
-6.500 -0.7222 0.04351 0.03430 -0.0145 1.0000 0.1062
-6.250 -0.7111 0.04084 0.03096 -0.0118 1.0000 0.1089
-6.000 -0.6934 0.03788 0.02798 -0.0103 1.0000 0.1149
-5.750 -0.6767 0.03560 0.02523 -0.0082 1.0000 0.1247
-5.500 -0.6567 0.03344 0.02283 -0.0066 1.0000 0.1382
-5.250 -0.6352 0.03135 0.02085 -0.0053 1.0000 0.1586
-5.000 -0.6137 0.02947 0.01904 -0.0038 1.0000 0.1877
-4.750 -0.5928 0.02763 0.01745 -0.0021 1.0000 0.2303
-4.500 -0.5757 0.02562 0.01600 0.0000 1.0000 0.3009
-4.250 -0.5710 0.02304 0.01509 0.0047 1.0000 0.4766
-4.000 -0.5711 0.02345 0.01661 0.0151 1.0000 0.6929
-3.750 -0.5638 0.02476 0.01781 0.0233 1.0000 0.7782
-3.500 -0.5343 0.02660 0.01934 0.0286 1.0000 0.8428
-3.250 -0.3126 0.03118 0.02244 0.0021 1.0000 0.9318
-3.000 -0.1726 0.03085 0.02134 -0.0193 1.0000 0.9789
-2.750 -0.1016 0.02992 0.02001 -0.0302 1.0000 1.0000
-2.500 -0.1020 0.02944 0.01945 -0.0276 1.0000 1.0000
-2.250 -0.1023 0.02900 0.01893 -0.0250 1.0000 1.0000
-2.000 -0.1025 0.02860 0.01845 -0.0222 1.0000 1.0000
-1.750 -0.1026 0.02824 0.01801 -0.0194 1.0000 1.0000
-1.500 -0.1025 0.02792 0.01762 -0.0165 1.0000 1.0000
-1.250 -0.1023 0.02763 0.01724 -0.0136 1.0000 1.0000
-1.000 -0.1020 0.02737 0.01692 -0.0106 1.0000 1.0000
-0.750 -0.1017 0.02714 0.01662 -0.0075 1.0000 1.0000
-0.500 -0.1013 0.02693 0.01634 -0.0044 1.0000 1.0000
-0.250 -0.1010 0.02673 0.01609 -0.0013 1.0000 1.0000
0.000 -0.1005 0.02655 0.01585 0.0019 1.0000 1.0000
0.250 -0.0995 0.02640 0.01564 0.0050 1.0000 1.0000
0.500 -0.0970 0.02629 0.01547 0.0079 1.0000 1.0000
0.750 -0.0923 0.02627 0.01537 0.0104 1.0000 1.0000
1.000 -0.0854 0.02634 0.01537 0.0126 1.0000 1.0000
1.250 -0.0762 0.02652 0.01547 0.0144 1.0000 1.0000
1.500 -0.0649 0.02679 0.01567 0.0158 1.0000 1.0000
1.750 -0.0522 0.02715 0.01598 0.0169 1.0000 1.0000
2.000 -0.0386 0.02758 0.01636 0.0179 1.0000 1.0000
2.250 -0.0242 0.02808 0.01682 0.0186 1.0000 1.0000
2.500 -0.0095 0.02864 0.01736 0.0193 1.0000 1.0000
2.750 0.0056 0.02926 0.01796 0.0198 1.0000 1.0000
3.000 0.0208 0.02994 0.01864 0.0202 1.0000 1.0000
3.250 0.0360 0.03068 0.01939 0.0205 1.0000 1.0000
3.500 0.0762 0.03241 0.02119 0.0159 0.9882 1.0000
3.750 0.1322 0.03463 0.02353 0.0085 0.9642 1.0000
4.000 0.1818 0.03653 0.02557 0.0027 0.9411 1.0000
4.250 0.2263 0.03808 0.02726 -0.0017 0.9180 1.0000
4.500 0.2632 0.03930 0.02862 -0.0046 0.8946 1.0000
4.750 0.3078 0.04058 0.03012 -0.0083 0.8705 1.0000
5.000 0.3506 0.04156 0.03130 -0.0114 0.8457 1.0000
5.250 0.3857 0.04222 0.03219 -0.0130 0.8200 1.0000
5.500 0.4278 0.04260 0.03283 -0.0150 0.7929 1.0000
5.750 0.4764 0.04240 0.03295 -0.0171 0.7637 1.0000
6.000 0.5462 0.04070 0.03175 -0.0201 0.7315 1.0000
6.250 0.6049 0.03792 0.02945 -0.0201 0.6937 1.0000
6.500 0.7178 0.02957 0.02203 -0.0208 0.6416 1.0000
6.750 0.7706 0.02488 0.01729 -0.0153 0.5065 1.0000
7.000 0.7725 0.02628 0.01713 -0.0087 0.3532 1.0000
7.250 0.7847 0.02865 0.01867 -0.0058 0.2714 1.0000
7.500 0.8194 0.03111 0.02070 -0.0064 0.2183 1.0000
7.750 0.8527 0.03343 0.02287 -0.0069 0.1858 1.0000
8.000 0.8882 0.03622 0.02559 -0.0077 0.1645 1.0000
8.250 0.9130 0.03889 0.02849 -0.0070 0.1496 1.0000
8.500 0.9357 0.04179 0.03148 -0.0062 0.1372 1.0000
8.750 0.9477 0.04445 0.03464 -0.0037 0.1292 1.0000
9.000 0.9619 0.04776 0.03818 -0.0020 0.1221 1.0000
9.250 0.9648 0.05071 0.04162 0.0013 0.1171 1.0000
9.500 0.9735 0.05414 0.04531 0.0034 0.1134 1.0000
9.750 0.9837 0.05838 0.04966 0.0049 0.1102 1.0000
10.000 0.9735 0.06174 0.05349 0.0087 0.1093 1.0000
10.250 0.9612 0.06529 0.05741 0.0122 0.1089 1.0000
10.500 0.9478 0.06911 0.06150 0.0152 0.1091 1.0000
10.750 0.9326 0.07291 0.06551 0.0181 0.1095 1.0000
11.000 0.9175 0.07696 0.06970 0.0204 0.1100 1.0000
11.250 0.8404 0.08238 0.07549 0.0225 0.1200 1.0000
11.500 0.8186 0.08819 0.08135 0.0215 0.1221 1.0000
11.750 0.8088 0.09399 0.08717 0.0203 0.1237 1.0000
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Polar data table (+)
Polar graphs
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