NASA SC(2)-0403 AIRFOIL (sc20403-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA SC(2)-0403 AIRFOIL (sc20403-il) Reynolds number: 500,000 Max Cl/Cd: 42.42 at α=0.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc20403-il-500000.txt Download as CSV file: xf-sc20403-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0403 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.6730 0.09751 0.09533 0.0234 1.0000 0.0079
-8.000 -0.6698 0.09355 0.09134 0.0210 1.0000 0.0080
-7.750 -0.6665 0.08952 0.08734 0.0182 1.0000 0.0082
-7.500 -0.6591 0.08492 0.08275 0.0134 1.0000 0.0083
-7.250 -0.6478 0.07969 0.07752 0.0068 1.0000 0.0085
-7.000 -0.6335 0.07412 0.07193 -0.0002 1.0000 0.0087
-6.750 -0.6169 0.06857 0.06631 -0.0065 1.0000 0.0090
-6.500 -0.5981 0.06313 0.06079 -0.0120 1.0000 0.0093
-6.250 -0.5770 0.05787 0.05541 -0.0167 1.0000 0.0097
-6.000 -0.5533 0.05291 0.05030 -0.0205 1.0000 0.0103
-5.750 -0.5259 0.04873 0.04594 -0.0231 1.0000 0.0111
-5.500 -0.4971 0.04586 0.04288 -0.0243 1.0000 0.0118
-5.250 -0.4707 0.04217 0.03897 -0.0258 1.0000 0.0120
-5.000 -0.4442 0.03836 0.03491 -0.0272 1.0000 0.0121
-4.750 -0.4170 0.03466 0.03092 -0.0284 1.0000 0.0121
-3.000 -0.2095 0.01158 0.00545 -0.0330 1.0000 0.0090
-2.750 -0.1796 0.00988 0.00359 -0.0331 1.0000 0.0082
-2.500 -0.1493 0.00878 0.00236 -0.0335 1.0000 0.0090
-2.250 -0.1202 0.00821 0.00170 -0.0337 1.0000 0.0117
-2.000 -0.0851 0.00542 0.00099 -0.0370 1.0000 0.6240
-1.750 -0.0601 0.00497 0.00105 -0.0362 1.0000 0.7754
-1.500 -0.0350 0.00486 0.00103 -0.0354 1.0000 0.8196
-1.250 -0.0130 0.00473 0.00104 -0.0337 1.0000 0.8699
-1.000 0.0075 0.00462 0.00101 -0.0317 1.0000 0.9065
-0.750 0.0261 0.00448 0.00093 -0.0293 1.0000 0.9373
-0.500 0.0437 0.00429 0.00081 -0.0268 1.0000 1.0000
-0.250 0.0733 0.00431 0.00081 -0.0274 1.0000 1.0000
0.000 0.1024 0.00433 0.00085 -0.0278 1.0000 1.0000
0.250 0.1311 0.00436 0.00091 -0.0282 1.0000 1.0000
0.500 0.1596 0.00439 0.00100 -0.0284 1.0000 1.0000
0.750 0.1879 0.00443 0.00113 -0.0286 1.0000 1.0000
1.000 0.2357 0.00690 0.00120 -0.0331 0.2677 1.0000
1.250 0.2622 0.00857 0.00201 -0.0333 0.0109 1.0000
1.500 0.2906 0.00921 0.00273 -0.0332 0.0084 1.0000
1.750 0.3183 0.01034 0.00398 -0.0328 0.0078 1.0000
2.000 0.3461 0.01206 0.00586 -0.0322 0.0085 1.0000
2.250 0.3744 0.01488 0.00899 -0.0314 0.0107 1.0000
3.750 0.5332 0.03439 0.03055 -0.0287 0.0115 1.0000
4.000 0.5580 0.03792 0.03437 -0.0284 0.0115 1.0000
4.250 0.5824 0.04157 0.03828 -0.0283 0.0114 1.0000
4.500 0.6069 0.04524 0.04219 -0.0284 0.0113 1.0000
4.750 0.6333 0.04839 0.04555 -0.0286 0.0109 1.0000
5.000 0.6617 0.05156 0.04890 -0.0291 0.0100 1.0000
5.250 0.6859 0.05601 0.05353 -0.0305 0.0094 1.0000
5.500 0.7076 0.06086 0.05853 -0.0326 0.0088 1.0000
5.750 0.7273 0.06591 0.06371 -0.0354 0.0084 1.0000
6.000 0.7450 0.07111 0.06901 -0.0387 0.0081 1.0000
6.250 0.7608 0.07638 0.07435 -0.0427 0.0078 1.0000
6.500 0.7744 0.08167 0.07971 -0.0470 0.0076 1.0000
6.750 0.7858 0.08693 0.08500 -0.0518 0.0075 1.0000
7.000 0.7948 0.09209 0.09019 -0.0567 0.0073 1.0000
7.250 0.8012 0.09707 0.09522 -0.0616 0.0072 1.0000
7.500 0.8024 0.10149 0.09962 -0.0653 0.0071 1.0000
7.750 0.8034 0.10575 0.10386 -0.0680 0.0070 1.0000
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Polar data table (+)
Polar graphs
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