NASA SC(2)-0404 AIRFOIL (sc20404-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-0404 AIRFOIL (sc20404-il) Reynolds number: 500,000 Max Cl/Cd: 41.53 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc20404-il-500000-n5.txt Download as CSV file: xf-sc20404-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.6756 0.11283 0.11056 0.0263 1.0000 0.0073
-9.250 -0.6723 0.10876 0.10650 0.0244 1.0000 0.0076
-9.000 -0.6691 0.10468 0.10243 0.0223 1.0000 0.0078
-8.750 -0.6655 0.10059 0.09835 0.0201 1.0000 0.0082
-8.500 -0.6581 0.09686 0.09465 0.0169 1.0000 0.0092
-8.250 -0.6525 0.09300 0.09080 0.0142 1.0000 0.0095
-8.000 -0.6486 0.08883 0.08665 0.0112 1.0000 0.0096
-7.750 -0.6430 0.08415 0.08199 0.0066 1.0000 0.0096
-7.500 -0.6320 0.07834 0.07618 -0.0011 1.0000 0.0097
-7.250 -0.6189 0.07236 0.07016 -0.0083 1.0000 0.0097
-7.000 -0.6147 0.06478 0.06250 -0.0147 1.0000 0.0086
-6.750 -0.5421 0.04789 0.04567 -0.0198 1.0000 0.0096
-6.250 -0.5563 0.04371 0.04081 -0.0277 1.0000 0.0037
-6.000 -0.5331 0.03747 0.03425 -0.0304 1.0000 0.0035
-5.750 -0.5069 0.03159 0.02798 -0.0323 1.0000 0.0034
-5.500 -0.4782 0.02582 0.02172 -0.0337 1.0000 0.0033
-5.250 -0.4476 0.02037 0.01568 -0.0348 1.0000 0.0033
-5.000 -0.4169 0.01635 0.01106 -0.0354 1.0000 0.0034
-4.750 -0.3875 0.01397 0.00828 -0.0356 1.0000 0.0037
-4.500 -0.3586 0.01198 0.00594 -0.0360 1.0000 0.0051
-4.250 -0.3312 0.01169 0.00562 -0.0361 1.0000 0.0067
-4.000 -0.3035 0.01127 0.00514 -0.0362 1.0000 0.0086
-3.750 -0.2746 0.01024 0.00397 -0.0364 1.0000 0.0094
-3.500 -0.2457 0.00949 0.00312 -0.0368 1.0000 0.0110
-3.250 -0.2166 0.00882 0.00233 -0.0372 1.0000 0.0142
-3.000 -0.1886 0.00852 0.00199 -0.0373 1.0000 0.0177
-2.750 -0.1605 0.00824 0.00154 -0.0374 1.0000 0.0209
-2.500 -0.1325 0.00794 0.00132 -0.0375 1.0000 0.0425
-2.250 -0.1048 0.00764 0.00116 -0.0377 1.0000 0.0828
-2.000 -0.0765 0.00720 0.00101 -0.0382 1.0000 0.1719
-1.750 -0.0456 0.00592 0.00085 -0.0400 1.0000 0.4960
-1.500 -0.0177 0.00544 0.00091 -0.0403 1.0000 0.6540
-1.250 0.0090 0.00531 0.00094 -0.0400 1.0000 0.7028
-1.000 0.0353 0.00522 0.00100 -0.0396 1.0000 0.7450
-0.750 0.0616 0.00518 0.00104 -0.0393 1.0000 0.7676
-0.500 0.0881 0.00516 0.00108 -0.0389 1.0000 0.7841
0.000 0.1536 0.00507 0.00114 -0.0412 0.9878 0.8108
0.250 0.1956 0.00524 0.00106 -0.0435 0.8401 0.8196
0.500 0.2120 0.00729 0.00121 -0.0414 0.3422 0.8289
0.750 0.2379 0.00806 0.00136 -0.0415 0.1536 0.8391
1.000 0.2645 0.00846 0.00151 -0.0414 0.0716 0.8494
1.250 0.2911 0.00873 0.00168 -0.0412 0.0330 0.8595
1.500 0.3179 0.00895 0.00191 -0.0409 0.0187 0.8708
1.750 0.3444 0.00918 0.00233 -0.0404 0.0164 0.8835
2.000 0.3702 0.00951 0.00281 -0.0398 0.0156 0.8980
2.250 0.3951 0.00976 0.00315 -0.0390 0.0132 0.9151
2.500 0.4182 0.01038 0.00392 -0.0378 0.0105 0.9388
2.750 0.4435 0.01132 0.00502 -0.0370 0.0088 1.0000
3.000 0.4712 0.01215 0.00596 -0.0369 0.0077 1.0000
3.250 0.4994 0.01217 0.00598 -0.0372 0.0053 1.0000
3.500 0.5270 0.01269 0.00654 -0.0372 0.0042 1.0000
3.750 0.5534 0.01502 0.00929 -0.0366 0.0032 1.0000
4.000 0.5803 0.01797 0.01273 -0.0358 0.0030 1.0000
4.250 0.6063 0.02247 0.01786 -0.0345 0.0029 1.0000
4.500 0.6309 0.02773 0.02367 -0.0333 0.0030 1.0000
4.750 0.6542 0.03306 0.02944 -0.0324 0.0031 1.0000
5.000 0.6760 0.03852 0.03528 -0.0319 0.0032 1.0000
5.250 0.6962 0.04422 0.04130 -0.0319 0.0033 1.0000
7.250 0.8047 0.09205 0.09018 -0.0556 0.0076 1.0000
7.500 0.8067 0.09714 0.09527 -0.0607 0.0075 1.0000
7.750 0.8062 0.10179 0.09991 -0.0643 0.0074 1.0000
8.000 0.8067 0.10631 0.10441 -0.0672 0.0072 1.0000
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Polar data table (+)
Polar graphs
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