S9027 (8%) (s9027-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: S9027 (8%) (s9027-il) Reynolds number: 1,000,000 Max Cl/Cd: 71.83 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s9027-il-1000000.txt Download as CSV file: xf-s9027-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: S9027 (8%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.500 -1.0151 0.12439 0.12242 0.0248 1.0000 0.0066
-16.250 -1.0507 0.11189 0.10980 0.0175 1.0000 0.0065
-16.000 -1.0781 0.10191 0.09972 0.0117 1.0000 0.0063
-15.750 -1.1064 0.09214 0.08985 0.0060 1.0000 0.0062
-15.500 -1.1468 0.08039 0.07798 -0.0010 1.0000 0.0061
-15.250 -1.2183 0.06275 0.06013 -0.0123 1.0000 0.0058
-15.000 -1.2568 0.05074 0.04791 -0.0213 1.0000 0.0057
-14.750 -1.2906 0.04136 0.03827 -0.0286 1.0000 0.0055
-14.500 -1.2991 0.03756 0.03434 -0.0304 1.0000 0.0057
-14.250 -1.3081 0.03459 0.03123 -0.0304 1.0000 0.0058
-14.000 -1.3144 0.03243 0.02893 -0.0288 1.0000 0.0059
-13.750 -1.3194 0.03067 0.02704 -0.0261 1.0000 0.0059
-13.500 -1.3108 0.02970 0.02597 -0.0242 1.0000 0.0061
-13.250 -1.3117 0.02746 0.02353 -0.0219 1.0000 0.0063
-13.000 -1.3058 0.02556 0.02147 -0.0201 1.0000 0.0067
-12.750 -1.2901 0.02453 0.02037 -0.0190 1.0000 0.0071
-12.500 -1.2711 0.02381 0.01960 -0.0182 1.0000 0.0074
-12.250 -1.2513 0.02311 0.01884 -0.0175 1.0000 0.0078
-12.000 -1.2307 0.02247 0.01812 -0.0167 1.0000 0.0083
-11.750 -1.2097 0.02185 0.01741 -0.0160 1.0000 0.0087
-11.500 -1.1872 0.02137 0.01686 -0.0154 1.0000 0.0089
-11.250 -1.1733 0.01967 0.01499 -0.0141 1.0000 0.0098
-11.000 -1.1514 0.01904 0.01433 -0.0134 1.0000 0.0104
-10.750 -1.1276 0.01866 0.01393 -0.0130 1.0000 0.0110
-10.500 -1.1038 0.01826 0.01348 -0.0125 1.0000 0.0117
-10.250 -1.0795 0.01791 0.01309 -0.0121 1.0000 0.0123
-10.000 -1.0545 0.01767 0.01278 -0.0117 1.0000 0.0127
-9.750 -1.0353 0.01643 0.01139 -0.0107 1.0000 0.0135
-9.500 -1.0138 0.01554 0.01043 -0.0099 1.0000 0.0145
-9.250 -0.9894 0.01513 0.01000 -0.0094 1.0000 0.0153
-9.000 -0.9650 0.01470 0.00954 -0.0089 1.0000 0.0161
-8.750 -0.9406 0.01425 0.00903 -0.0084 1.0000 0.0168
-8.500 -0.9160 0.01383 0.00853 -0.0078 1.0000 0.0174
-8.250 -0.8908 0.01352 0.00819 -0.0074 1.0000 0.0178
-8.000 -0.8682 0.01273 0.00728 -0.0065 1.0000 0.0187
-7.750 -0.8450 0.01201 0.00650 -0.0057 1.0000 0.0202
-7.500 -0.8205 0.01158 0.00605 -0.0051 1.0000 0.0215
-7.250 -0.7955 0.01122 0.00565 -0.0045 1.0000 0.0227
-7.000 -0.7706 0.01087 0.00525 -0.0039 1.0000 0.0238
-6.750 -0.7453 0.01059 0.00493 -0.0033 1.0000 0.0246
-6.500 -0.7215 0.01004 0.00435 -0.0025 1.0000 0.0284
-6.250 -0.6967 0.00972 0.00404 -0.0018 1.0000 0.0320
-6.000 -0.6722 0.00936 0.00370 -0.0011 1.0000 0.0379
-5.750 -0.6472 0.00912 0.00346 -0.0005 1.0000 0.0433
-5.500 -0.6227 0.00880 0.00318 0.0003 1.0000 0.0513
-5.250 -0.5975 0.00861 0.00298 0.0009 1.0000 0.0558
-5.000 -0.5729 0.00833 0.00275 0.0016 1.0000 0.0644
-4.750 -0.5481 0.00811 0.00254 0.0023 1.0000 0.0727
-4.500 -0.5234 0.00788 0.00237 0.0030 1.0000 0.0836
-4.250 -0.4988 0.00765 0.00219 0.0038 1.0000 0.0969
-4.000 -0.4743 0.00743 0.00204 0.0045 1.0000 0.1109
-3.750 -0.4499 0.00721 0.00189 0.0053 1.0000 0.1273
-3.250 -0.4016 0.00676 0.00164 0.0069 1.0000 0.1741
-3.000 -0.3692 0.00656 0.00154 0.0059 0.9983 0.1980
-2.750 -0.3307 0.00636 0.00145 0.0036 0.9950 0.2267
-2.500 -0.2940 0.00613 0.00136 0.0016 0.9910 0.2620
-2.250 -0.2569 0.00590 0.00128 -0.0004 0.9858 0.2979
-2.000 -0.2201 0.00568 0.00119 -0.0023 0.9800 0.3352
-1.500 -0.1538 0.00520 0.00103 -0.0043 0.9470 0.4258
-1.250 -0.1251 0.00499 0.00095 -0.0042 0.9145 0.4804
-1.000 -0.1000 0.00491 0.00088 -0.0033 0.8764 0.5206
-0.750 -0.0751 0.00486 0.00084 -0.0024 0.8371 0.5615
-0.500 -0.0501 0.00482 0.00081 -0.0016 0.7971 0.6079
-0.250 -0.0248 0.00480 0.00079 -0.0008 0.7536 0.6520
0.000 0.0000 0.00481 0.00078 0.0000 0.6996 0.6990
0.250 0.0248 0.00480 0.00079 0.0008 0.6519 0.7534
0.500 0.0501 0.00481 0.00081 0.0016 0.6079 0.7972
0.750 0.0751 0.00486 0.00084 0.0024 0.5612 0.8373
1.000 0.1000 0.00491 0.00089 0.0033 0.5207 0.8765
1.250 0.1251 0.00499 0.00095 0.0042 0.4804 0.9148
1.500 0.1538 0.00520 0.00103 0.0043 0.4258 0.9470
2.000 0.2201 0.00568 0.00119 0.0023 0.3351 0.9802
2.250 0.2569 0.00590 0.00128 0.0004 0.2978 0.9859
2.500 0.2942 0.00613 0.00136 -0.0017 0.2615 0.9912
2.750 0.3309 0.00636 0.00145 -0.0036 0.2266 0.9951
3.000 0.3694 0.00656 0.00154 -0.0059 0.1979 0.9985
3.250 0.4011 0.00676 0.00164 -0.0068 0.1742 1.0000
3.500 0.4251 0.00699 0.00176 -0.0060 0.1493 1.0000
3.750 0.4494 0.00721 0.00189 -0.0052 0.1275 1.0000
4.000 0.4738 0.00743 0.00204 -0.0044 0.1113 1.0000
4.250 0.4982 0.00765 0.00219 -0.0037 0.0969 1.0000
4.500 0.5228 0.00788 0.00236 -0.0029 0.0835 1.0000
4.750 0.5475 0.00811 0.00254 -0.0022 0.0729 1.0000
5.000 0.5724 0.00833 0.00275 -0.0015 0.0646 1.0000
5.250 0.5970 0.00861 0.00298 -0.0008 0.0558 1.0000
5.500 0.6222 0.00880 0.00318 -0.0002 0.0513 1.0000
5.750 0.6467 0.00912 0.00345 0.0006 0.0433 1.0000
6.000 0.6718 0.00936 0.00370 0.0012 0.0379 1.0000
6.250 0.6963 0.00972 0.00404 0.0019 0.0319 1.0000
6.500 0.7212 0.01004 0.00435 0.0026 0.0284 1.0000
6.750 0.7451 0.01059 0.00492 0.0034 0.0246 1.0000
7.000 0.7704 0.01087 0.00525 0.0040 0.0238 1.0000
7.250 0.7955 0.01122 0.00565 0.0045 0.0227 1.0000
7.500 0.8205 0.01158 0.00605 0.0051 0.0215 1.0000
7.750 0.8452 0.01201 0.00649 0.0057 0.0202 1.0000
8.000 0.8684 0.01273 0.00728 0.0065 0.0187 1.0000
8.250 0.8912 0.01351 0.00817 0.0073 0.0178 1.0000
8.500 0.9165 0.01383 0.00853 0.0077 0.0174 1.0000
8.750 0.9411 0.01426 0.00904 0.0083 0.0168 1.0000
9.000 0.9656 0.01470 0.00953 0.0088 0.0161 1.0000
9.250 0.9901 0.01510 0.00997 0.0093 0.0153 1.0000
9.500 1.0144 0.01554 0.01044 0.0097 0.0145 1.0000
9.750 1.0358 0.01644 0.01140 0.0105 0.0134 1.0000
10.000 1.0554 0.01763 0.01274 0.0115 0.0127 1.0000
10.250 1.0802 0.01791 0.01309 0.0119 0.0123 1.0000
10.500 1.1047 0.01824 0.01346 0.0124 0.0117 1.0000
10.750 1.1283 0.01869 0.01396 0.0129 0.0110 1.0000
11.000 1.1521 0.01907 0.01436 0.0133 0.0104 1.0000
11.250 1.1741 0.01970 0.01501 0.0139 0.0097 1.0000
11.500 1.1879 0.02143 0.01692 0.0153 0.0089 1.0000
11.750 1.2108 0.02185 0.01741 0.0158 0.0087 1.0000
12.000 1.2321 0.02246 0.01810 0.0165 0.0083 1.0000
12.250 1.2518 0.02322 0.01896 0.0173 0.0079 1.0000
12.500 1.2723 0.02383 0.01962 0.0180 0.0074 1.0000
12.750 1.2910 0.02461 0.02045 0.0188 0.0071 1.0000
13.000 1.3070 0.02562 0.02153 0.0198 0.0067 1.0000
13.250 1.3052 0.02825 0.02439 0.0222 0.0061 1.0000
13.500 1.3160 0.02946 0.02571 0.0236 0.0060 1.0000
13.750 1.3241 0.03058 0.02694 0.0254 0.0059 1.0000
14.000 1.3210 0.03219 0.02867 0.0281 0.0058 1.0000
14.250 1.3156 0.03421 0.03083 0.0299 0.0057 1.0000
14.500 1.3000 0.03773 0.03451 0.0300 0.0057 1.0000
14.750 1.2907 0.04167 0.03860 0.0280 0.0056 1.0000
15.000 1.2646 0.04975 0.04689 0.0218 0.0057 1.0000
15.250 1.2251 0.06193 0.05930 0.0125 0.0058 1.0000
15.500 1.1455 0.08114 0.07874 0.0002 0.0061 1.0000
15.750 1.1038 0.09317 0.09089 -0.0070 0.0062 1.0000
16.000 1.0755 0.10301 0.10082 -0.0127 0.0063 1.0000
16.250 1.0520 0.11220 0.11012 -0.0180 0.0066 1.0000
16.500 1.0090 0.12646 0.12453 -0.0264 0.0069 1.0000
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Polar data table (+)
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