NASA SC(2)-0404 AIRFOIL (sc20404-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA SC(2)-0404 AIRFOIL (sc20404-il) Reynolds number: 500,000 Max Cl/Cd: 52.03 at α=1° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc20404-il-500000.txt Download as CSV file: xf-sc20404-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5576 0.09600 0.09386 0.0081 1.0000 0.0091
-9.000 -0.5599 0.09109 0.08897 0.0067 1.0000 0.0092
-8.750 -0.5621 0.08628 0.08417 0.0053 1.0000 0.0094
-8.500 -0.5640 0.08157 0.07948 0.0037 1.0000 0.0095
-8.250 -0.5664 0.07690 0.07482 0.0019 1.0000 0.0096
-8.000 -0.5696 0.07213 0.07008 -0.0003 1.0000 0.0097
-7.750 -0.5739 0.06727 0.06524 -0.0032 1.0000 0.0097
-7.500 -0.5748 0.06092 0.05889 -0.0108 1.0000 0.0097
-7.250 -0.5717 0.05463 0.05253 -0.0162 1.0000 0.0097
-7.000 -0.5653 0.04891 0.04671 -0.0200 1.0000 0.0099
-6.750 -0.5559 0.04347 0.04118 -0.0230 1.0000 0.0101
-6.500 -0.5435 0.03824 0.03581 -0.0256 1.0000 0.0104
-6.250 -0.5284 0.03340 0.03081 -0.0277 1.0000 0.0108
-6.000 -0.5106 0.02869 0.02591 -0.0295 1.0000 0.0113
-5.750 -0.4903 0.02437 0.02137 -0.0311 1.0000 0.0119
-5.500 -0.4678 0.02035 0.01709 -0.0323 1.0000 0.0128
-5.250 -0.4432 0.01675 0.01317 -0.0333 1.0000 0.0141
-5.000 -0.4164 0.01395 0.01003 -0.0338 1.0000 0.0160
-4.750 -0.3870 0.01377 0.00954 -0.0328 1.0000 0.0182
-4.500 -0.3653 0.01727 0.01191 -0.0364 1.0000 0.0122
-4.250 -0.3355 0.01514 0.00947 -0.0365 1.0000 0.0140
-4.000 -0.3075 0.01469 0.00891 -0.0364 1.0000 0.0173
-3.750 -0.2782 0.01229 0.00626 -0.0364 1.0000 0.0161
-3.500 -0.2492 0.01074 0.00458 -0.0365 1.0000 0.0159
-3.250 -0.2197 0.00968 0.00340 -0.0367 1.0000 0.0171
-3.000 -0.1897 0.00875 0.00234 -0.0373 1.0000 0.0211
-2.750 -0.1611 0.00833 0.00182 -0.0375 1.0000 0.0298
-2.500 -0.1293 0.00687 0.00124 -0.0393 1.0000 0.2730
-2.250 -0.0991 0.00564 0.00110 -0.0408 1.0000 0.5900
-2.000 -0.0724 0.00533 0.00115 -0.0405 1.0000 0.7062
-1.750 -0.0463 0.00524 0.00119 -0.0399 1.0000 0.7577
-1.500 -0.0201 0.00519 0.00118 -0.0395 1.0000 0.7784
-1.250 0.0055 0.00514 0.00122 -0.0388 1.0000 0.8065
-1.000 0.0302 0.00510 0.00126 -0.0379 1.0000 0.8365
-0.750 0.0552 0.00506 0.00128 -0.0372 1.0000 0.8529
-0.500 0.0803 0.00502 0.00130 -0.0365 1.0000 0.8675
-0.250 0.1052 0.00498 0.00133 -0.0358 1.0000 0.8819
0.000 0.1298 0.00494 0.00137 -0.0350 1.0000 0.8967
0.250 0.1540 0.00490 0.00142 -0.0341 1.0000 0.9122
0.500 0.1769 0.00483 0.00147 -0.0329 1.0000 0.9317
0.750 0.1964 0.00471 0.00148 -0.0310 1.0000 0.9769
1.000 0.2539 0.00488 0.00120 -0.0363 0.7872 0.9701
1.250 0.2746 0.00680 0.00139 -0.0354 0.3444 1.0000
1.500 0.3015 0.00819 0.00172 -0.0362 0.0599 1.0000
1.750 0.3307 0.00894 0.00242 -0.0364 0.0245 1.0000
2.000 0.3595 0.00951 0.00308 -0.0366 0.0186 1.0000
2.250 0.3871 0.01069 0.00437 -0.0364 0.0158 1.0000
2.500 0.4150 0.01191 0.00571 -0.0361 0.0148 1.0000
2.750 0.4429 0.01377 0.00773 -0.0357 0.0151 1.0000
3.000 0.4714 0.01586 0.00999 -0.0352 0.0178 1.0000
4.250 0.6075 0.03142 0.02757 -0.0312 0.0132 1.0000
4.500 0.6326 0.03510 0.03156 -0.0307 0.0117 1.0000
4.750 0.6560 0.03902 0.03575 -0.0305 0.0108 1.0000
5.000 0.6781 0.04308 0.04005 -0.0305 0.0101 1.0000
5.250 0.6987 0.04723 0.04442 -0.0309 0.0096 1.0000
5.500 0.7175 0.05147 0.04883 -0.0316 0.0092 1.0000
5.750 0.7345 0.05587 0.05339 -0.0325 0.0088 1.0000
6.000 0.7494 0.06063 0.05830 -0.0338 0.0085 1.0000
6.250 0.7619 0.06613 0.06393 -0.0357 0.0083 1.0000
6.500 0.7714 0.07229 0.07020 -0.0384 0.0081 1.0000
6.750 0.7769 0.07939 0.07740 -0.0420 0.0079 1.0000
7.000 0.7134 0.07275 0.07097 -0.0365 0.0084 1.0000
7.250 0.7090 0.07837 0.07662 -0.0399 0.0084 1.0000
7.500 0.7002 0.08351 0.08175 -0.0438 0.0084 1.0000
7.750 0.6942 0.08849 0.08671 -0.0463 0.0084 1.0000
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Polar data table (+)
Polar graphs
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