NASA SC(2)-0402 AIRFOIL (sc20402-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
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Airfoil: NASA SC(2)-0402 AIRFOIL (sc20402-il) Reynolds number: 1,000,000 Max Cl/Cd: 32.69 at α=-0.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc20402-il-1000000.txt Download as CSV file: xf-sc20402-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.5843 0.13426 0.13271 0.0303 1.0000 0.0019
-11.000 -0.5830 0.13064 0.12910 0.0294 1.0000 0.0019
-7.250 -0.6485 0.07947 0.07799 0.0098 1.0000 0.0023
-7.000 -0.6381 0.07520 0.07370 0.0062 1.0000 0.0026
-6.750 -0.6209 0.07026 0.06872 0.0005 1.0000 0.0028
-6.500 -0.6007 0.06503 0.06343 -0.0052 1.0000 0.0029
-6.250 -0.5785 0.05982 0.05813 -0.0104 1.0000 0.0029
-6.000 -0.5544 0.05471 0.05292 -0.0150 1.0000 0.0030
-5.750 -0.5288 0.04971 0.04778 -0.0188 1.0000 0.0030
-5.500 -0.5012 0.04467 0.04255 -0.0221 1.0000 0.0028
-5.250 -0.4680 0.03917 0.03664 -0.0245 1.0000 0.0023
-5.000 -0.4404 0.03498 0.03224 -0.0263 1.0000 0.0024
-4.750 -0.4123 0.03121 0.02826 -0.0278 1.0000 0.0025
-4.500 -0.3835 0.02779 0.02461 -0.0291 1.0000 0.0026
-4.250 -0.3540 0.02466 0.02124 -0.0300 1.0000 0.0028
-4.000 -0.3240 0.02183 0.01816 -0.0307 1.0000 0.0030
-3.750 -0.2936 0.01930 0.01536 -0.0312 1.0000 0.0034
-3.500 -0.2632 0.01705 0.01286 -0.0314 1.0000 0.0038
-3.250 -0.2330 0.01524 0.01083 -0.0315 1.0000 0.0046
-3.000 -0.2046 0.01530 0.01079 -0.0308 1.0000 0.0060
-2.750 -0.1738 0.01188 0.00704 -0.0320 1.0000 0.0099
-1.250 0.0031 0.00602 0.00053 -0.0321 1.0000 0.0057
-1.000 0.0360 0.00395 0.00036 -0.0346 1.0000 0.6490
-0.500 0.0707 0.00296 0.00041 -0.0292 1.0000 1.0000
-0.250 0.1131 0.00346 0.00037 -0.0323 0.7973 1.0000
0.000 0.1340 0.00624 0.00064 -0.0320 0.0057 1.0000
0.250 0.1626 0.00662 0.00117 -0.0319 0.0056 1.0000
0.500 0.1912 0.00709 0.00174 -0.0318 0.0079 1.0000
1.750 0.3304 0.01447 0.00965 -0.0300 0.0062 1.0000
2.000 0.3595 0.01520 0.01057 -0.0293 0.0048 1.0000
2.250 0.3880 0.01682 0.01239 -0.0288 0.0039 1.0000
2.500 0.4162 0.01884 0.01466 -0.0282 0.0034 1.0000
2.750 0.4439 0.02114 0.01720 -0.0277 0.0031 1.0000
3.000 0.4711 0.02367 0.01998 -0.0272 0.0028 1.0000
3.250 0.4976 0.02644 0.02299 -0.0269 0.0026 1.0000
3.500 0.5235 0.02950 0.02628 -0.0267 0.0025 1.0000
3.750 0.5488 0.03287 0.02987 -0.0266 0.0024 1.0000
4.000 0.5737 0.03670 0.03393 -0.0267 0.0023 1.0000
4.250 0.6026 0.04116 0.03879 -0.0266 0.0026 1.0000
4.500 0.6291 0.04591 0.04379 -0.0273 0.0029 1.0000
4.750 0.6534 0.05045 0.04849 -0.0286 0.0029 1.0000
5.000 0.6765 0.05509 0.05328 -0.0304 0.0028 1.0000
5.250 0.6985 0.05987 0.05818 -0.0328 0.0028 1.0000
5.500 0.7190 0.06477 0.06319 -0.0357 0.0027 1.0000
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Polar data table (+)
Polar graphs
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