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NASA SC(2)-0404 AIRFOIL (sc20404-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NASA SC(2)-0404 AIRFOIL (sc20404-il)
Reynolds number: 100,000
Max Cl/Cd: 37.59 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sc20404-il-100000.txt
Download as CSV file: xf-sc20404-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.6590   0.09820   0.09340   0.0134   1.0000   0.0634
  -8.000  -0.6580   0.09420   0.08946   0.0097   1.0000   0.0658
  -7.750  -0.6533   0.08894   0.08422  -0.0021   1.0000   0.0679
  -7.500  -0.6456   0.08415   0.07917  -0.0151   1.0000   0.0688
  -7.250  -0.6386   0.07854   0.07382  -0.0079   1.0000   0.0717
  -7.000  -0.6278   0.07441   0.06967  -0.0094   1.0000   0.0761
  -6.750  -0.6103   0.06929   0.06400  -0.0231   1.0000   0.0823
  -6.500  -0.6007   0.06406   0.05910  -0.0190   1.0000   0.0862
  -6.250  -0.5818   0.05910   0.05380  -0.0249   1.0000   0.0968
  -5.250  -0.5085   0.04398   0.03819  -0.0301   1.0000   0.1894
  -5.000  -0.4906   0.04072   0.03505  -0.0291   1.0000   0.2209
  -4.500  -0.3871   0.02764   0.01929  -0.0360   1.0000   0.0645
  -4.250  -0.3540   0.02473   0.01561  -0.0355   1.0000   0.0546
  -4.000  -0.3248   0.02188   0.01243  -0.0353   1.0000   0.0529
  -3.750  -0.2961   0.01979   0.01002  -0.0349   1.0000   0.0578
  -3.500  -0.2688   0.01806   0.00823  -0.0344   1.0000   0.0652
  -3.250  -0.2415   0.01639   0.00649  -0.0336   1.0000   0.0697
  -3.000  -0.2139   0.01471   0.00493  -0.0335   1.0000   0.0860
  -2.750  -0.2002   0.01086   0.00420  -0.0301   1.0000   0.7505
  -2.500  -0.2015   0.01070   0.00409  -0.0209   1.0000   0.8671
  -2.250  -0.1971   0.01019   0.00359  -0.0134   1.0000   0.9506
  -2.000  -0.1540   0.00987   0.00296  -0.0163   1.0000   1.0000
  -1.750  -0.1276   0.00974   0.00262  -0.0169   1.0000   1.0000
  -1.500  -0.0993   0.00966   0.00235  -0.0177   1.0000   1.0000
  -1.250  -0.0703   0.00961   0.00215  -0.0186   1.0000   1.0000
  -1.000  -0.0412   0.00958   0.00201  -0.0194   1.0000   1.0000
  -0.750  -0.0122   0.00957   0.00188  -0.0201   1.0000   1.0000
  -0.500   0.0166   0.00957   0.00183  -0.0207   1.0000   1.0000
  -0.250   0.0451   0.00959   0.00182  -0.0212   1.0000   1.0000
   0.000   0.0734   0.00963   0.00185  -0.0216   1.0000   1.0000
   0.250   0.1015   0.00967   0.00193  -0.0219   1.0000   1.0000
   0.500   0.1293   0.00973   0.00206  -0.0222   1.0000   1.0000
   0.750   0.1570   0.00980   0.00226  -0.0224   1.0000   1.0000
   1.000   0.1845   0.00988   0.00247  -0.0226   1.0000   1.0000
   1.250   0.2119   0.00997   0.00274  -0.0227   1.0000   1.0000
   1.500   0.2391   0.01009   0.00307  -0.0228   1.0000   1.0000
   1.750   0.2663   0.01021   0.00348  -0.0228   1.0000   1.0000
   2.000   0.2936   0.01036   0.00405  -0.0227   1.0000   1.0000
   2.250   0.3618   0.01597   0.00621  -0.0282   0.0699   1.0000
   2.500   0.3888   0.01778   0.00801  -0.0275   0.0638   1.0000
   2.750   0.4181   0.01969   0.01008  -0.0269   0.0615   1.0000
   3.000   0.4467   0.02178   0.01226  -0.0266   0.0556   1.0000
   3.250   0.4578   0.01218   0.00351  -0.0231   0.0527   1.0000
   3.500   0.4871   0.01397   0.00604  -0.0217   0.0596   1.0000
   3.750   0.5140   0.01713   0.00981  -0.0203   0.0783   1.0000
   4.500   0.6005   0.03009   0.02500  -0.0196   0.1743   1.0000
   4.750   0.6580   0.04894   0.04356  -0.0244   0.1395   1.0000
   5.000   0.6766   0.05281   0.04763  -0.0245   0.1226   1.0000
   5.500   0.7109   0.06110   0.05623  -0.0261   0.0957   1.0000
   5.750   0.7267   0.06560   0.06098  -0.0284   0.0843   1.0000
   6.000   0.7389   0.07062   0.06609  -0.0300   0.0775   1.0000
   6.250   0.7528   0.07480   0.07041  -0.0321   0.0700   1.0000
   6.500   0.7603   0.08228   0.07747  -0.0283   0.0669   1.0000
   6.750   0.7708   0.08542   0.08116  -0.0369   0.0653   1.0000
   7.000   0.7796   0.09051   0.08635  -0.0440   0.0620   1.0000
   7.250   0.7853   0.09536   0.09123  -0.0481   0.0595   1.0000
   7.500   0.7900   0.09989   0.09576  -0.0506   0.0573   1.0000
   7.750   0.7992   0.10657   0.10228  -0.0388   0.0539   1.0000
   8.000   0.8012   0.11099   0.10678  -0.0445   0.0537   1.0000
   8.250   0.8003   0.11537   0.11117  -0.0511   0.0535   1.0000
   8.500   0.7981   0.11944   0.11519  -0.0571   0.0533   1.0000
   8.750   0.7961   0.12318   0.11887  -0.0624   0.0528   1.0000
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