Supermarine 371-II (tip) (supermarine371ii-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: Supermarine 371-II (tip) (supermarine371ii-il) Reynolds number: 100,000 Max Cl/Cd: 29.9 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-supermarine371ii-il-100000.txt Download as CSV file: xf-supermarine371ii-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: Supermarine 371-II (tip)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5428 0.09593 0.09127 -0.0198 1.0000 0.0752
-8.750 -0.5472 0.09197 0.08738 -0.0237 1.0000 0.0770
-8.500 -0.5601 0.08769 0.08318 -0.0294 1.0000 0.0781
-8.250 -0.5748 0.08456 0.08002 -0.0327 1.0000 0.0787
-8.000 -0.5883 0.08223 0.07753 -0.0351 1.0000 0.0793
-7.750 -0.5654 0.07552 0.07107 -0.0324 1.0000 0.0840
-7.500 -0.5654 0.07194 0.06745 -0.0333 1.0000 0.0884
-7.250 -0.5793 0.07065 0.06575 -0.0355 1.0000 0.0926
-7.000 -0.5667 0.06449 0.05985 -0.0346 1.0000 0.0962
-6.750 -0.5627 0.06163 0.05692 -0.0337 1.0000 0.1028
-6.500 -0.5695 0.05885 0.05399 -0.0318 1.0000 0.1083
-6.250 -0.5684 0.05635 0.05156 -0.0288 1.0000 0.1137
-5.750 -0.5770 0.05228 0.04726 -0.0224 1.0000 0.1297
-5.500 -0.5763 0.04965 0.04449 -0.0198 1.0000 0.1388
-5.250 -0.5734 0.04725 0.04198 -0.0175 1.0000 0.1528
-4.750 -0.5627 0.04259 0.03717 -0.0130 1.0000 0.1959
-4.250 -0.5544 0.03790 0.03269 -0.0071 1.0000 0.2865
-4.000 -0.5463 0.03543 0.03031 -0.0039 1.0000 0.3293
-3.750 -0.4620 0.02921 0.02102 -0.0067 1.0000 0.0755
-3.500 -0.4358 0.02678 0.01799 -0.0047 1.0000 0.0636
-3.250 -0.4111 0.02450 0.01538 -0.0035 1.0000 0.0603
-3.000 -0.3864 0.02275 0.01334 -0.0022 1.0000 0.0594
-2.750 -0.3637 0.02181 0.01215 -0.0010 1.0000 0.0649
-2.500 -0.3411 0.02021 0.01049 0.0001 1.0000 0.0691
-2.250 -0.1121 0.01659 0.00990 -0.0249 1.0000 1.0000
-2.000 -0.1125 0.01657 0.00977 -0.0213 1.0000 1.0000
-1.750 -0.1123 0.01651 0.00954 -0.0178 1.0000 1.0000
-1.500 -0.1120 0.01642 0.00934 -0.0143 1.0000 1.0000
-1.250 -0.1117 0.01629 0.00912 -0.0107 1.0000 1.0000
-1.000 -0.1116 0.01613 0.00886 -0.0070 1.0000 1.0000
-0.750 -0.1117 0.01593 0.00858 -0.0033 1.0000 1.0000
-0.500 -0.0948 0.01591 0.00844 -0.0027 0.9974 1.0000
-0.250 -0.0713 0.01604 0.00845 -0.0033 0.9938 1.0000
0.000 -0.0509 0.01610 0.00842 -0.0031 0.9899 1.0000
0.250 -0.0284 0.01627 0.00846 -0.0033 0.9863 1.0000
0.500 -0.0017 0.01657 0.00869 -0.0043 0.9830 1.0000
0.750 0.0211 0.01682 0.00887 -0.0045 0.9796 1.0000
1.000 0.0438 0.01707 0.00908 -0.0045 0.9759 1.0000
1.250 0.0707 0.01744 0.00942 -0.0054 0.9723 1.0000
1.500 0.1019 0.01793 0.00992 -0.0071 0.9691 1.0000
1.750 0.1240 0.01824 0.01024 -0.0070 0.9648 1.0000
2.000 0.1500 0.01864 0.01068 -0.0076 0.9604 1.0000
2.250 0.1829 0.01919 0.01130 -0.0095 0.9562 1.0000
2.500 0.2066 0.01960 0.01179 -0.0097 0.9508 1.0000
2.750 0.2372 0.02011 0.01247 -0.0111 0.9449 1.0000
3.000 0.2673 0.02066 0.01316 -0.0124 0.9386 1.0000
3.250 0.3033 0.02120 0.01391 -0.0147 0.9302 1.0000
3.500 0.4808 0.01608 0.00650 -0.0204 0.1146 1.0000
3.750 0.4921 0.01733 0.00759 -0.0172 0.0864 1.0000
4.000 0.5056 0.01851 0.00875 -0.0145 0.0740 1.0000
4.250 0.5225 0.01987 0.01004 -0.0124 0.0638 1.0000
4.500 0.5452 0.02156 0.01167 -0.0110 0.0593 1.0000
4.750 0.5732 0.02417 0.01425 -0.0104 0.0573 1.0000
5.000 0.5992 0.02602 0.01648 -0.0093 0.0545 1.0000
5.250 0.6246 0.02818 0.01901 -0.0080 0.0528 1.0000
5.500 0.6495 0.03170 0.02279 -0.0069 0.0556 1.0000
5.750 0.6758 0.03497 0.02672 -0.0047 0.0675 1.0000
8.500 0.7765 0.07896 0.07412 0.0095 0.0949 1.0000
8.750 0.7529 0.08180 0.07714 0.0094 0.0932 1.0000
9.000 0.7348 0.08553 0.08091 0.0087 0.0924 1.0000
9.250 0.7176 0.09024 0.08563 0.0057 0.0911 1.0000
9.500 0.7062 0.09566 0.09102 0.0015 0.0901 1.0000
9.750 0.7328 0.09931 0.09463 0.0074 0.0822 1.0000
10.000 0.7166 0.10435 0.09967 0.0026 0.0820 1.0000
10.250 0.7006 0.11027 0.10551 -0.0045 0.0812 1.0000
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Polar data table (+)
Polar graphs
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