dh4009sm (dh4009sm-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: dh4009sm (dh4009sm-il) Reynolds number: 200,000 Max Cl/Cd: 34.56 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-dh4009sm-il-200000-n5.txt Download as CSV file: xf-dh4009sm-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: dh4009sm
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-5.250 -0.5685 0.02926 0.02245 -0.0011 1.0000 0.0135
-5.000 -0.5496 0.02693 0.01982 0.0007 1.0000 0.0133
-4.750 -0.5292 0.02482 0.01743 0.0023 1.0000 0.0131
-4.500 -0.5076 0.02295 0.01530 0.0038 1.0000 0.0132
-4.250 -0.4853 0.02132 0.01340 0.0051 1.0000 0.0134
-4.000 -0.4629 0.02028 0.01218 0.0064 1.0000 0.0143
-3.750 -0.4411 0.01884 0.01057 0.0076 1.0000 0.0159
-3.500 -0.4195 0.01761 0.00927 0.0088 1.0000 0.0162
-3.250 -0.3883 0.01639 0.00799 0.0080 0.9973 0.0162
-3.000 -0.3571 0.01526 0.00684 0.0070 0.9912 0.0164
-2.750 -0.3275 0.01428 0.00580 0.0062 0.9824 0.0169
-2.500 -0.2971 0.01348 0.00495 0.0053 0.9745 0.0177
-2.250 -0.2641 0.01286 0.00423 0.0039 0.9682 0.0193
-2.000 -0.2316 0.01239 0.00364 0.0027 0.9609 0.0224
-1.750 -0.1971 0.01189 0.00309 0.0011 0.9552 0.0389
-1.500 -0.1861 0.00888 0.00278 0.0033 0.9461 0.7004
-1.250 -0.1576 0.00884 0.00308 0.0042 0.9403 0.8055
-1.000 -0.1247 0.00883 0.00306 0.0033 0.9325 0.8242
-0.750 -0.0872 0.00878 0.00292 0.0010 0.9265 0.8314
-0.500 -0.0528 0.00875 0.00283 -0.0005 0.9181 0.8377
-0.250 -0.0159 0.00872 0.00276 -0.0026 0.9112 0.8447
0.000 0.0179 0.00870 0.00274 -0.0040 0.9022 0.8511
0.250 0.0518 0.00870 0.00272 -0.0054 0.8935 0.8583
0.500 0.0863 0.00870 0.00273 -0.0069 0.8849 0.8644
0.750 0.1173 0.00872 0.00277 -0.0077 0.8738 0.8719
1.000 0.1488 0.00875 0.00281 -0.0084 0.8609 0.8784
1.250 0.1789 0.00878 0.00288 -0.0088 0.8472 0.8859
1.500 0.2088 0.00883 0.00297 -0.0092 0.8347 0.8927
1.750 0.2374 0.00888 0.00307 -0.0094 0.8223 0.9007
2.000 0.2668 0.00893 0.00314 -0.0094 0.7975 0.9073
2.250 0.2917 0.00901 0.00316 -0.0083 0.7535 0.9159
2.500 0.3173 0.00918 0.00314 -0.0074 0.6811 0.9228
2.750 0.3327 0.00989 0.00306 -0.0043 0.4884 0.9325
3.000 0.3413 0.01185 0.00352 -0.0014 0.1505 0.9442
3.250 0.3680 0.01285 0.00410 -0.0018 0.0517 0.9519
3.500 0.3978 0.01339 0.00464 -0.0025 0.0362 0.9596
3.750 0.4285 0.01401 0.00541 -0.0034 0.0300 0.9668
4.000 0.4589 0.01469 0.00619 -0.0042 0.0262 0.9740
4.250 0.4879 0.01571 0.00722 -0.0050 0.0218 0.9811
4.500 0.5192 0.01649 0.00810 -0.0061 0.0199 0.9877
4.750 0.5493 0.01762 0.00934 -0.0068 0.0185 0.9945
5.000 0.5803 0.01896 0.01084 -0.0078 0.0174 1.0000
5.250 0.5987 0.02017 0.01219 -0.0059 0.0168 1.0000
5.500 0.6180 0.02160 0.01379 -0.0043 0.0164 1.0000
5.750 0.6375 0.02328 0.01570 -0.0026 0.0161 1.0000
6.000 0.6561 0.02520 0.01790 -0.0008 0.0160 1.0000
6.250 0.6732 0.02657 0.01947 0.0009 0.0151 1.0000
6.500 0.6865 0.02887 0.02198 0.0028 0.0139 1.0000
6.750 0.6994 0.03150 0.02507 0.0053 0.0133 1.0000
7.000 0.7121 0.03421 0.02817 0.0078 0.0131 1.0000
7.250 0.7224 0.03737 0.03173 0.0104 0.0129 1.0000
7.500 0.7301 0.04089 0.03563 0.0130 0.0128 1.0000
7.750 0.7353 0.04466 0.03974 0.0155 0.0128 1.0000
8.000 0.7380 0.04859 0.04398 0.0178 0.0129 1.0000
8.250 0.7377 0.05263 0.04828 0.0198 0.0130 1.0000
8.500 0.7343 0.05675 0.05262 0.0216 0.0131 1.0000
8.750 0.7273 0.06091 0.05697 0.0231 0.0132 1.0000
9.250 0.6195 0.05548 0.05193 0.0324 0.0134 1.0000
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Polar data table (+)
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