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NASA SC(2)-0402 AIRFOIL (sc20402-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NASA SC(2)-0402 AIRFOIL (sc20402-il)
Reynolds number: 200,000
Max Cl/Cd: 40.11 at α=2.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sc20402-il-200000-n5.txt
Download as CSV file: xf-sc20402-il-200000-n5.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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.7033   0.12422   0.12080   0.0401   1.0000   0.0105
  -9.500  -0.6994   0.12038   0.11698   0.0385   1.0000   0.0110
  -9.250  -0.6956   0.11652   0.11314   0.0369   1.0000   0.0113
  -9.000  -0.6917   0.11267   0.10931   0.0352   1.0000   0.0116
  -8.750  -0.6878   0.10884   0.10551   0.0334   1.0000   0.0119
  -8.500  -0.6839   0.10502   0.10172   0.0314   1.0000   0.0122
  -8.250  -0.6799   0.10121   0.09794   0.0294   1.0000   0.0125
  -8.000  -0.6759   0.09740   0.09416   0.0271   1.0000   0.0128
  -7.750  -0.6713   0.09353   0.09032   0.0244   1.0000   0.0130
  -7.500  -0.6629   0.08923   0.08604   0.0201   1.0000   0.0134
  -7.250  -0.6512   0.08456   0.08137   0.0146   1.0000   0.0138
  -7.000  -0.6362   0.07963   0.07642   0.0084   1.0000   0.0142
  -6.750  -0.6174   0.07460   0.07134   0.0020   1.0000   0.0147
  -6.500  -0.5940   0.06969   0.06633  -0.0044   1.0000   0.0153
  -6.250  -0.5674   0.06520   0.06167  -0.0099   1.0000   0.0158
  -6.000  -0.5425   0.06097   0.05726  -0.0135   1.0000   0.0161
  -5.750  -0.5170   0.05673   0.05234  -0.0166   1.0000   0.0163
  -5.500  -0.4921   0.05261   0.04798  -0.0190   1.0000   0.0164
  -5.250  -0.4739   0.04468   0.03986  -0.0229   1.0000   0.0175
  -5.000  -0.4532   0.04035   0.03542  -0.0249   1.0000   0.0193
  -4.750  -0.4267   0.03675   0.03157  -0.0266   1.0000   0.0216
  -4.500  -0.3970   0.03342   0.02791  -0.0280   1.0000   0.0247
  -4.250  -0.3615   0.03356   0.02740  -0.0275   1.0000   0.0288
  -4.000  -0.3362   0.02691   0.02059  -0.0302   1.0000   0.0322
  -3.750  -0.3069   0.02431   0.01770  -0.0308   1.0000   0.0355
  -3.500  -0.2746   0.02174   0.01468  -0.0305   1.0000   0.0251
  -3.250  -0.2428   0.01906   0.01158  -0.0300   1.0000   0.0130
  -3.000  -0.2128   0.01682   0.00898  -0.0298   1.0000   0.0102
  -2.750  -0.1834   0.01505   0.00690  -0.0293   1.0000   0.0083
  -2.500  -0.1551   0.01394   0.00563  -0.0289   1.0000   0.0072
  -2.250  -0.1273   0.01298   0.00459  -0.0287   1.0000   0.0070
  -1.500  -0.0398   0.00990   0.00105  -0.0291   1.0000   0.0086
  -1.250  -0.0296   0.00668   0.00100  -0.0255   1.0000   0.8860
  -1.000  -0.0077   0.00641   0.00073  -0.0236   1.0000   1.0000
  -0.750   0.0202   0.00642   0.00065  -0.0237   1.0000   1.0000
  -0.500   0.0478   0.00643   0.00062  -0.0238   1.0000   1.0000
  -0.250   0.0754   0.00644   0.00064  -0.0238   1.0000   1.0000
   0.250   0.1513   0.00769   0.00084  -0.0274   0.5534   1.0000
   0.500   0.1729   0.01019   0.00142  -0.0271   0.0074   1.0000
   1.250   0.2555   0.01347   0.00505  -0.0261   0.0069   1.0000
   1.500   0.2833   0.01443   0.00610  -0.0258   0.0074   1.0000
   1.750   0.3118   0.01574   0.00760  -0.0252   0.0087   1.0000
   2.000   0.3409   0.01765   0.00984  -0.0245   0.0109   1.0000
   2.250   0.3696   0.02004   0.01258  -0.0239   0.0139   1.0000
   2.750   0.4123   0.01028   0.00408  -0.0189   0.0356   1.0000
   4.000   0.5325   0.02413   0.01957  -0.0180   0.0198   1.0000
   4.250   0.5507   0.02819   0.02378  -0.0185   0.0180   1.0000
   4.500   0.5973   0.05219   0.04754  -0.0245   0.0163   1.0000
   6.750   0.7782   0.09252   0.08967  -0.0538   0.0123   1.0000
   7.000   0.7864   0.09732   0.09447  -0.0584   0.0121   1.0000
   7.250   0.7907   0.10174   0.09887  -0.0623   0.0119   1.0000
   7.500   0.7931   0.10592   0.10303  -0.0651   0.0116   1.0000
   7.750   0.7954   0.11004   0.10712  -0.0675   0.0114   1.0000
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