NASA SC(2)-0404 AIRFOIL (sc20404-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-0404 AIRFOIL (sc20404-il) Reynolds number: 200,000 Max Cl/Cd: 35.17 at α=1.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc20404-il-200000-n5.txt Download as CSV file: xf-sc20404-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0404 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
------ -------- --------- --------- -------- -------- --------
-7.250 -0.6239 0.07154 0.06807 -0.0091 1.0000 0.0093
-7.000 -0.6133 0.06550 0.06194 -0.0144 1.0000 0.0090
-6.750 -0.5993 0.05965 0.05596 -0.0190 1.0000 0.0086
-6.500 -0.5822 0.05398 0.05010 -0.0229 1.0000 0.0083
-6.250 -0.5623 0.04844 0.04432 -0.0261 1.0000 0.0080
-6.000 -0.5396 0.04307 0.03865 -0.0287 1.0000 0.0078
-5.750 -0.5145 0.03790 0.03311 -0.0308 1.0000 0.0076
-5.500 -0.4873 0.03295 0.02773 -0.0323 1.0000 0.0074
-5.250 -0.4583 0.02833 0.02259 -0.0334 1.0000 0.0075
-5.000 -0.4282 0.02420 0.01790 -0.0340 1.0000 0.0078
-4.750 -0.3984 0.02169 0.01480 -0.0341 1.0000 0.0096
-4.500 -0.3701 0.01905 0.01175 -0.0349 1.0000 0.0133
-4.250 -0.3413 0.01683 0.00918 -0.0347 1.0000 0.0138
-4.000 -0.3131 0.01510 0.00721 -0.0345 1.0000 0.0147
-3.750 -0.2851 0.01371 0.00568 -0.0345 1.0000 0.0168
-3.500 -0.2571 0.01292 0.00476 -0.0345 1.0000 0.0206
-3.250 -0.2285 0.01194 0.00369 -0.0350 1.0000 0.0250
-3.000 -0.1999 0.01130 0.00292 -0.0352 1.0000 0.0298
-2.750 -0.1711 0.01067 0.00230 -0.0355 1.0000 0.0549
-2.500 -0.1418 0.00962 0.00181 -0.0367 1.0000 0.2199
-2.250 -0.1153 0.00792 0.00187 -0.0373 1.0000 0.6695
-2.000 -0.0908 0.00778 0.00185 -0.0363 1.0000 0.7293
-1.750 -0.0676 0.00768 0.00186 -0.0349 1.0000 0.7803
-1.500 -0.0458 0.00759 0.00186 -0.0331 1.0000 0.8208
-1.250 -0.0229 0.00751 0.00182 -0.0318 1.0000 0.8439
-1.000 0.0009 0.00743 0.00175 -0.0307 1.0000 0.8609
-0.750 0.0248 0.00737 0.00170 -0.0298 1.0000 0.8769
-0.500 0.0483 0.00729 0.00166 -0.0288 1.0000 0.8922
-0.250 0.0714 0.00721 0.00163 -0.0276 1.0000 0.9097
0.000 0.0945 0.00712 0.00161 -0.0265 1.0000 0.9322
0.250 0.1185 0.00701 0.00160 -0.0257 1.0000 0.9744
0.500 0.1451 0.00703 0.00170 -0.0257 1.0000 1.0000
0.750 0.1738 0.00710 0.00183 -0.0261 1.0000 1.0000
1.000 0.2167 0.00711 0.00196 -0.0295 0.9846 1.0000
1.250 0.2719 0.00773 0.00174 -0.0335 0.6390 1.0000
1.500 0.2892 0.01039 0.00212 -0.0326 0.1060 1.0000
1.750 0.3170 0.01107 0.00253 -0.0329 0.0390 1.0000
2.000 0.3454 0.01167 0.00330 -0.0330 0.0263 1.0000
2.250 0.3734 0.01237 0.00412 -0.0330 0.0232 1.0000
2.500 0.4003 0.01356 0.00541 -0.0328 0.0212 1.0000
2.750 0.4280 0.01427 0.00622 -0.0327 0.0170 1.0000
3.000 0.4554 0.01571 0.00782 -0.0323 0.0146 1.0000
3.250 0.4834 0.01755 0.00991 -0.0318 0.0135 1.0000
3.500 0.5116 0.01984 0.01257 -0.0312 0.0129 1.0000
3.750 0.5371 0.02283 0.01599 -0.0310 0.0092 1.0000
4.000 0.5654 0.02454 0.01809 -0.0304 0.0075 1.0000
4.250 0.5921 0.02862 0.02286 -0.0295 0.0070 1.0000
4.500 0.6174 0.03296 0.02770 -0.0287 0.0069 1.0000
4.750 0.6414 0.03756 0.03274 -0.0282 0.0070 1.0000
5.000 0.6639 0.04239 0.03794 -0.0281 0.0071 1.0000
5.250 0.6850 0.04740 0.04328 -0.0284 0.0073 1.0000
5.500 0.7044 0.05259 0.04874 -0.0292 0.0076 1.0000
5.750 0.7218 0.05793 0.05431 -0.0305 0.0078 1.0000
6.000 0.7368 0.06343 0.06000 -0.0324 0.0081 1.0000
6.250 0.7489 0.06914 0.06586 -0.0348 0.0085 1.0000
6.500 0.7491 0.07611 0.07290 -0.0371 0.0094 1.0000
7.500 0.7957 0.09423 0.09130 -0.0506 0.0104 1.0000
7.750 0.7974 0.09949 0.09655 -0.0559 0.0106 1.0000
8.000 0.7977 0.10449 0.10151 -0.0600 0.0107 1.0000
8.250 0.7983 0.10924 0.10624 -0.0632 0.0108 1.0000
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Polar data table (+)
Polar graphs
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