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NASA SC(2)-0404 AIRFOIL (sc20404-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NASA SC(2)-0404 AIRFOIL (sc20404-il)
Reynolds number: 1,000,000
Max Cl/Cd: 49.7 at α=0.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sc20404-il-1000000.txt
Download as CSV file: xf-sc20404-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.6708   0.09484   0.09326   0.0183   1.0000   0.0054
  -8.250  -0.6686   0.09061   0.08904   0.0156   1.0000   0.0055
  -8.000  -0.6666   0.08628   0.08473   0.0125   1.0000   0.0056
  -7.750  -0.6603   0.08115   0.07962   0.0068   1.0000   0.0057
  -7.500  -0.6487   0.07477   0.07323  -0.0024   1.0000   0.0058
  -7.250  -0.6348   0.06840   0.06681  -0.0103   1.0000   0.0059
  -7.000  -0.6190   0.06238   0.06070  -0.0164   1.0000   0.0061
  -6.750  -0.6009   0.05663   0.05484  -0.0213   1.0000   0.0064
  -6.500  -0.5802   0.05120   0.04927  -0.0251   1.0000   0.0069
  -6.250  -0.5561   0.04653   0.04443  -0.0276   1.0000   0.0076
  -4.750  -0.3904   0.01727   0.01315  -0.0366   1.0000   0.0062
  -4.500  -0.3568   0.01224   0.00750  -0.0370   1.0000   0.0055
  -4.250  -0.3287   0.01191   0.00708  -0.0370   1.0000   0.0077
  -4.000  -0.3008   0.01151   0.00661  -0.0370   1.0000   0.0084
  -3.750  -0.2713   0.00951   0.00441  -0.0376   1.0000   0.0101
  -3.500  -0.2420   0.00863   0.00344  -0.0379   1.0000   0.0098
  -3.250  -0.2117   0.00769   0.00236  -0.0385   1.0000   0.0103
  -3.000  -0.1821   0.00713   0.00171  -0.0388   1.0000   0.0149
  -2.750  -0.1542   0.00694   0.00147  -0.0389   1.0000   0.0180
  -2.500  -0.1248   0.00638   0.00105  -0.0393   1.0000   0.0733
  -2.250  -0.0958   0.00582   0.00089  -0.0401   1.0000   0.1948
  -2.000  -0.0658   0.00492   0.00073  -0.0413   1.0000   0.4265
  -1.750  -0.0373   0.00438   0.00069  -0.0419   1.0000   0.5833
  -1.500  -0.0100   0.00416   0.00071  -0.0419   1.0000   0.6648
  -1.250   0.0169   0.00402   0.00075  -0.0417   1.0000   0.7198
  -1.000   0.0436   0.00398   0.00077  -0.0414   1.0000   0.7411
  -0.750   0.0702   0.00393   0.00083  -0.0411   1.0000   0.7736
  -0.500   0.0968   0.00390   0.00088  -0.0408   1.0000   0.7943
  -0.250   0.1237   0.00389   0.00093  -0.0405   1.0000   0.8080
   0.000   0.1576   0.00384   0.00095  -0.0419   0.9962   0.8206
   0.250   0.1998   0.00402   0.00090  -0.0445   0.8633   0.8304
   0.500   0.2207   0.00519   0.00099  -0.0430   0.5641   0.8414
   0.750   0.2462   0.00616   0.00113  -0.0431   0.3116   0.8522
   1.000   0.2725   0.00687   0.00129  -0.0432   0.1359   0.8631
   1.250   0.2991   0.00734   0.00146  -0.0430   0.0395   0.8747
   1.500   0.3261   0.00780   0.00198  -0.0426   0.0163   0.8869
   1.750   0.3527   0.00794   0.00223  -0.0423   0.0145   0.9004
   2.000   0.3787   0.00817   0.00254  -0.0418   0.0117   0.9156
   2.250   0.4027   0.00880   0.00333  -0.0406   0.0093   0.9361
   2.500   0.4253   0.00954   0.00426  -0.0391   0.0092   1.0000
   2.750   0.4532   0.01086   0.00571  -0.0387   0.0100   1.0000
   3.250   0.5077   0.01442   0.00967  -0.0382   0.0072   1.0000
   3.500   0.5359   0.01483   0.01015  -0.0381   0.0059   1.0000
   3.750   0.5637   0.01845   0.01427  -0.0369   0.0051   1.0000
   4.250   0.6075   0.03279   0.02987  -0.0342   0.0075   1.0000
   4.500   0.6305   0.03705   0.03439  -0.0337   0.0075   1.0000
   4.750   0.6529   0.04143   0.03900  -0.0334   0.0075   1.0000
   5.000   0.6747   0.04589   0.04366  -0.0334   0.0074   1.0000
   5.250   0.6961   0.05029   0.04824  -0.0337   0.0073   1.0000
   5.500   0.7200   0.05374   0.05182  -0.0342   0.0069   1.0000
   5.750   0.7430   0.05794   0.05615  -0.0351   0.0062   1.0000
   6.000   0.7614   0.06316   0.06150  -0.0371   0.0058   1.0000
   6.250   0.7773   0.06860   0.06704  -0.0397   0.0055   1.0000
   6.500   0.7909   0.07415   0.07269  -0.0431   0.0053   1.0000
   6.750   0.8023   0.07978   0.07837  -0.0472   0.0051   1.0000
   7.000   0.8114   0.08539   0.08403  -0.0518   0.0049   1.0000
   7.250   0.8179   0.09097   0.08965  -0.0570   0.0049   1.0000
   7.500   0.8204   0.09630   0.09497  -0.0624   0.0048   1.0000
   7.750   0.8186   0.10099   0.09965  -0.0662   0.0048   1.0000
   8.000   0.8181   0.10551   0.10416  -0.0690   0.0047   1.0000
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