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NASA SC(2)-0404 AIRFOIL (sc20404-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: NASA SC(2)-0404 AIRFOIL (sc20404-il)
Reynolds number: 1,000,000
Max Cl/Cd: 55.15 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sc20404-il-1000000-n5.txt
Download as CSV file: xf-sc20404-il-1000000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.6594   0.09545   0.09387   0.0179   1.0000   0.0038
  -8.250  -0.6570   0.09113   0.08957   0.0154   1.0000   0.0038
  -8.000  -0.6550   0.08671   0.08516   0.0124   1.0000   0.0038
  -7.750  -0.6497   0.08163   0.08010   0.0072   1.0000   0.0038
  -7.500  -0.6387   0.07513   0.07359  -0.0019   1.0000   0.0038
  -7.250  -0.6296   0.06724   0.06564  -0.0109   1.0000   0.0036
  -7.000  -0.6167   0.05997   0.05827  -0.0178   1.0000   0.0033
  -6.750  -0.5998   0.05339   0.05154  -0.0229   1.0000   0.0032
  -6.500  -0.5801   0.04714   0.04511  -0.0268   1.0000   0.0030
  -6.250  -0.5577   0.04107   0.03880  -0.0298   1.0000   0.0028
  -6.000  -0.5326   0.03504   0.03246  -0.0321   1.0000   0.0026
  -5.750  -0.5049   0.02881   0.02584  -0.0338   1.0000   0.0024
  -5.500  -0.4734   0.02111   0.01752  -0.0352   1.0000   0.0022
  -5.250  -0.4392   0.01332   0.00879  -0.0363   1.0000   0.0020
  -5.000  -0.4092   0.01073   0.00579  -0.0368   1.0000   0.0021
  -4.750  -0.3796   0.00940   0.00424  -0.0373   1.0000   0.0025
  -4.500  -0.3517   0.00916   0.00394  -0.0374   1.0000   0.0036
  -4.250  -0.3244   0.00914   0.00394  -0.0375   1.0000   0.0039
  -4.000  -0.2944   0.00810   0.00273  -0.0381   1.0000   0.0055
  -3.750  -0.2661   0.00778   0.00239  -0.0384   1.0000   0.0071
  -3.500  -0.2380   0.00755   0.00214  -0.0385   1.0000   0.0094
  -3.250  -0.2106   0.00748   0.00208  -0.0385   1.0000   0.0101
  -3.000  -0.1821   0.00714   0.00166  -0.0387   1.0000   0.0110
  -2.750  -0.1538   0.00686   0.00124  -0.0389   1.0000   0.0134
  -2.500  -0.1259   0.00667   0.00106  -0.0389   1.0000   0.0192
  -2.250  -0.0984   0.00650   0.00094  -0.0389   1.0000   0.0334
  -2.000  -0.0711   0.00632   0.00086  -0.0389   1.0000   0.0581
  -1.750  -0.0438   0.00611   0.00078  -0.0389   1.0000   0.0979
  -1.500  -0.0164   0.00584   0.00072  -0.0391   1.0000   0.1610
  -1.250   0.0152   0.00463   0.00061  -0.0410   1.0000   0.5046
  -1.000   0.0431   0.00430   0.00064  -0.0412   1.0000   0.6156
  -0.750   0.0818   0.00410   0.00064  -0.0438   0.9916   0.6751
  -0.500   0.1219   0.00407   0.00064  -0.0464   0.9344   0.7068
  -0.250   0.1412   0.00465   0.00065  -0.0440   0.7586   0.7218
   0.000   0.1646   0.00631   0.00080  -0.0438   0.3158   0.7370
   0.250   0.1915   0.00700   0.00091  -0.0441   0.1234   0.7530
   0.500   0.2192   0.00724   0.00100  -0.0442   0.0684   0.7665
   0.750   0.2470   0.00739   0.00110  -0.0442   0.0412   0.7787
   1.000   0.2747   0.00756   0.00122  -0.0442   0.0195   0.7888
   1.250   0.3026   0.00771   0.00135  -0.0442   0.0135   0.7977
   1.500   0.3305   0.00790   0.00164  -0.0441   0.0117   0.8066
   1.750   0.3582   0.00813   0.00203  -0.0440   0.0114   0.8159
   2.000   0.3857   0.00859   0.00264  -0.0438   0.0099   0.8254
   2.250   0.4130   0.00889   0.00303  -0.0437   0.0092   0.8345
   2.500   0.4405   0.00883   0.00296  -0.0437   0.0080   0.8435
   2.750   0.4679   0.00886   0.00298  -0.0437   0.0054   0.8541
   3.000   0.4944   0.00948   0.00373  -0.0434   0.0037   0.8664
   3.250   0.5211   0.00968   0.00399  -0.0431   0.0033   0.8798
   3.500   0.5476   0.00993   0.00435  -0.0428   0.0023   0.8932
   3.750   0.5728   0.01089   0.00552  -0.0421   0.0019   0.9079
   4.000   0.5965   0.01256   0.00754  -0.0407   0.0018   0.9284
   4.250   0.6176   0.01680   0.01251  -0.0382   0.0018   0.9770
   4.500   0.6412   0.02582   0.02245  -0.0355   0.0021   1.0000
   4.750   0.6644   0.03198   0.02908  -0.0341   0.0022   1.0000
   5.000   0.6865   0.03767   0.03512  -0.0334   0.0024   1.0000
   5.250   0.7075   0.04326   0.04098  -0.0333   0.0026   1.0000
   5.500   0.7269   0.04893   0.04688  -0.0337   0.0027   1.0000
   5.750   0.7445   0.05482   0.05296  -0.0349   0.0029   1.0000
   6.000   0.7596   0.06109   0.05940  -0.0370   0.0031   1.0000
   6.250   0.7675   0.06884   0.06729  -0.0403   0.0035   1.0000
   6.500   0.7793   0.07468   0.07321  -0.0435   0.0035   1.0000
   6.750   0.7897   0.08040   0.07900  -0.0473   0.0035   1.0000
   7.000   0.7983   0.08606   0.08471  -0.0517   0.0035   1.0000
   7.250   0.8048   0.09166   0.09033  -0.0567   0.0035   1.0000
   7.500   0.8071   0.09694   0.09562  -0.0619   0.0035   1.0000
   7.750   0.8060   0.10165   0.10031  -0.0656   0.0035   1.0000
   8.000   0.8059   0.10625   0.10490  -0.0684   0.0035   1.0000
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