NASA SC(2)-0402 AIRFOIL (sc20402-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-0402 AIRFOIL (sc20402-il) Reynolds number: 200,000 Max Cl/Cd: 40.11 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc20402-il-200000-n5.txt Download as CSV file: xf-sc20402-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0402 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.7033 0.12422 0.12080 0.0401 1.0000 0.0105
-9.500 -0.6994 0.12038 0.11698 0.0385 1.0000 0.0110
-9.250 -0.6956 0.11652 0.11314 0.0369 1.0000 0.0113
-9.000 -0.6917 0.11267 0.10931 0.0352 1.0000 0.0116
-8.750 -0.6878 0.10884 0.10551 0.0334 1.0000 0.0119
-8.500 -0.6839 0.10502 0.10172 0.0314 1.0000 0.0122
-8.250 -0.6799 0.10121 0.09794 0.0294 1.0000 0.0125
-8.000 -0.6759 0.09740 0.09416 0.0271 1.0000 0.0128
-7.750 -0.6713 0.09353 0.09032 0.0244 1.0000 0.0130
-7.500 -0.6629 0.08923 0.08604 0.0201 1.0000 0.0134
-7.250 -0.6512 0.08456 0.08137 0.0146 1.0000 0.0138
-7.000 -0.6362 0.07963 0.07642 0.0084 1.0000 0.0142
-6.750 -0.6174 0.07460 0.07134 0.0020 1.0000 0.0147
-6.500 -0.5940 0.06969 0.06633 -0.0044 1.0000 0.0153
-6.250 -0.5674 0.06520 0.06167 -0.0099 1.0000 0.0158
-6.000 -0.5425 0.06097 0.05726 -0.0135 1.0000 0.0161
-5.750 -0.5170 0.05673 0.05234 -0.0166 1.0000 0.0163
-5.500 -0.4921 0.05261 0.04798 -0.0190 1.0000 0.0164
-5.250 -0.4739 0.04468 0.03986 -0.0229 1.0000 0.0175
-5.000 -0.4532 0.04035 0.03542 -0.0249 1.0000 0.0193
-4.750 -0.4267 0.03675 0.03157 -0.0266 1.0000 0.0216
-4.500 -0.3970 0.03342 0.02791 -0.0280 1.0000 0.0247
-4.250 -0.3615 0.03356 0.02740 -0.0275 1.0000 0.0288
-4.000 -0.3362 0.02691 0.02059 -0.0302 1.0000 0.0322
-3.750 -0.3069 0.02431 0.01770 -0.0308 1.0000 0.0355
-3.500 -0.2746 0.02174 0.01468 -0.0305 1.0000 0.0251
-3.250 -0.2428 0.01906 0.01158 -0.0300 1.0000 0.0130
-3.000 -0.2128 0.01682 0.00898 -0.0298 1.0000 0.0102
-2.750 -0.1834 0.01505 0.00690 -0.0293 1.0000 0.0083
-2.500 -0.1551 0.01394 0.00563 -0.0289 1.0000 0.0072
-2.250 -0.1273 0.01298 0.00459 -0.0287 1.0000 0.0070
-1.500 -0.0398 0.00990 0.00105 -0.0291 1.0000 0.0086
-1.250 -0.0296 0.00668 0.00100 -0.0255 1.0000 0.8860
-1.000 -0.0077 0.00641 0.00073 -0.0236 1.0000 1.0000
-0.750 0.0202 0.00642 0.00065 -0.0237 1.0000 1.0000
-0.500 0.0478 0.00643 0.00062 -0.0238 1.0000 1.0000
-0.250 0.0754 0.00644 0.00064 -0.0238 1.0000 1.0000
0.250 0.1513 0.00769 0.00084 -0.0274 0.5534 1.0000
0.500 0.1729 0.01019 0.00142 -0.0271 0.0074 1.0000
1.250 0.2555 0.01347 0.00505 -0.0261 0.0069 1.0000
1.500 0.2833 0.01443 0.00610 -0.0258 0.0074 1.0000
1.750 0.3118 0.01574 0.00760 -0.0252 0.0087 1.0000
2.000 0.3409 0.01765 0.00984 -0.0245 0.0109 1.0000
2.250 0.3696 0.02004 0.01258 -0.0239 0.0139 1.0000
2.750 0.4123 0.01028 0.00408 -0.0189 0.0356 1.0000
4.000 0.5325 0.02413 0.01957 -0.0180 0.0198 1.0000
4.250 0.5507 0.02819 0.02378 -0.0185 0.0180 1.0000
4.500 0.5973 0.05219 0.04754 -0.0245 0.0163 1.0000
6.750 0.7782 0.09252 0.08967 -0.0538 0.0123 1.0000
7.000 0.7864 0.09732 0.09447 -0.0584 0.0121 1.0000
7.250 0.7907 0.10174 0.09887 -0.0623 0.0119 1.0000
7.500 0.7931 0.10592 0.10303 -0.0651 0.0116 1.0000
7.750 0.7954 0.11004 0.10712 -0.0675 0.0114 1.0000
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Polar data table (+)
Polar graphs
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