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NASA SC(2)-0414 AIRFOIL (sc20414-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NASA SC(2)-0414 AIRFOIL (sc20414-il)
Reynolds number: 50,000
Max Cl/Cd: 21.48 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sc20414-il-50000-n5.txt
Download as CSV file: xf-sc20414-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA SC(2)-0414 AIRFOIL                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.6899   0.09937   0.09043  -0.0402   1.0000   0.0841
 -12.250  -0.7360   0.08764   0.07857  -0.0473   1.0000   0.0837
 -12.000  -0.7770   0.07897   0.06972  -0.0517   1.0000   0.0834
 -11.750  -0.8111   0.07248   0.06303  -0.0539   1.0000   0.0834
 -11.500  -0.8398   0.06739   0.05771  -0.0545   1.0000   0.0837
 -11.250  -0.8651   0.06331   0.05338  -0.0536   1.0000   0.0841
 -11.000  -0.8859   0.05969   0.04947  -0.0525   1.0000   0.0847
 -10.750  -0.8750   0.05780   0.04761  -0.0517   1.0000   0.0864
 -10.500  -0.8702   0.05565   0.04537  -0.0508   1.0000   0.0882
 -10.250  -0.8672   0.05329   0.04284  -0.0497   1.0000   0.0900
 -10.000  -0.8638   0.05078   0.04008  -0.0484   1.0000   0.0918
  -9.750  -0.8589   0.04827   0.03722  -0.0472   1.0000   0.0939
  -9.500  -0.8496   0.04610   0.03481  -0.0459   1.0000   0.0964
  -9.250  -0.8334   0.04466   0.03340  -0.0449   1.0000   0.0991
  -9.000  -0.8186   0.04307   0.03170  -0.0437   1.0000   0.1022
  -8.750  -0.8035   0.04138   0.02976  -0.0425   1.0000   0.1057
  -8.500  -0.7863   0.03990   0.02817  -0.0413   1.0000   0.1093
  -8.250  -0.7679   0.03877   0.02708  -0.0401   1.0000   0.1132
  -8.000  -0.7492   0.03759   0.02579  -0.0388   1.0000   0.1177
  -7.750  -0.7298   0.03648   0.02461  -0.0373   1.0000   0.1225
  -7.500  -0.7107   0.03559   0.02380  -0.0358   1.0000   0.1278
  -7.250  -0.6909   0.03474   0.02279  -0.0342   1.0000   0.1342
  -7.000  -0.6720   0.03396   0.02213  -0.0324   1.0000   0.1405
  -6.750  -0.6543   0.03322   0.02137  -0.0307   1.0000   0.1483
  -6.500  -0.6380   0.03246   0.02071  -0.0288   1.0000   0.1560
  -6.250  -0.6222   0.03174   0.01995  -0.0269   1.0000   0.1663
  -6.000  -0.6082   0.03090   0.01929  -0.0251   1.0000   0.1769
  -5.750  -0.5942   0.03005   0.01857  -0.0235   1.0000   0.1906
  -5.500  -0.5802   0.02911   0.01781  -0.0221   1.0000   0.2082
  -5.250  -0.5656   0.02809   0.01698  -0.0210   1.0000   0.2332
  -5.000  -0.5506   0.02683   0.01613  -0.0205   1.0000   0.2712
  -4.750  -0.5346   0.02553   0.01550  -0.0200   1.0000   0.3421
  -4.500  -0.5247   0.02585   0.01672  -0.0148   1.0000   0.4370
  -4.250  -0.5132   0.02736   0.01857  -0.0085   1.0000   0.5098
  -4.000  -0.4934   0.02787   0.01896  -0.0070   1.0000   0.5640
  -3.750  -0.4731   0.02838   0.01934  -0.0058   1.0000   0.5995
  -3.500  -0.4522   0.02884   0.01965  -0.0047   1.0000   0.6278
  -3.250  -0.4353   0.02958   0.02031  -0.0019   1.0000   0.6473
  -3.000  -0.4187   0.03026   0.02091   0.0009   1.0000   0.6657
  -2.750  -0.4024   0.03085   0.02144   0.0037   1.0000   0.6833
  -2.500  -0.3869   0.03144   0.02197   0.0067   1.0000   0.7011
  -2.250  -0.3730   0.03201   0.02250   0.0101   1.0000   0.7188
  -2.000  -0.3615   0.03252   0.02301   0.0145   1.0000   0.7337
  -1.750  -0.3450   0.03282   0.02327   0.0173   0.9988   0.7484
  -1.500  -0.3151   0.03296   0.02334   0.0168   0.9936   0.7610
  -1.250  -0.2839   0.03290   0.02319   0.0154   0.9880   0.7698
  -1.000  -0.2514   0.03284   0.02306   0.0139   0.9825   0.7769
  -0.750  -0.2211   0.03277   0.02293   0.0129   0.9765   0.7840
  -0.500  -0.1859   0.03270   0.02281   0.0103   0.9702   0.7912
  -0.250  -0.1554   0.03259   0.02268   0.0093   0.9634   0.7959
   0.000  -0.1211   0.03251   0.02257   0.0072   0.9564   0.8005
   0.250  -0.0867   0.03245   0.02249   0.0047   0.9493   0.8053
   0.500  -0.0522   0.03237   0.02242   0.0026   0.9415   0.8092
   0.750  -0.0210   0.03229   0.02237   0.0014   0.9332   0.8131
   1.000   0.0154   0.03223   0.02235  -0.0009   0.9247   0.8171
   1.250   0.0495   0.03215   0.02231  -0.0030   0.9137   0.8207
   1.500   0.0935   0.03205   0.02225  -0.0067   0.9031   0.8235
   1.750   0.1290   0.03181   0.02210  -0.0082   0.8900   0.8262
   2.000   0.1628   0.03156   0.02195  -0.0093   0.8755   0.8292
   2.250   0.2033   0.03115   0.02163  -0.0112   0.8587   0.8319
   2.500   0.2497   0.03046   0.02106  -0.0136   0.8384   0.8341
   2.750   0.2977   0.02951   0.02022  -0.0157   0.8158   0.8364
   3.000   0.3330   0.02879   0.01961  -0.0160   0.7899   0.8394
   3.250   0.3671   0.02794   0.01887  -0.0156   0.7607   0.8421
   3.500   0.3949   0.02722   0.01824  -0.0142   0.7247   0.8449
   3.750   0.4204   0.02664   0.01774  -0.0127   0.6767   0.8479
   4.000   0.4506   0.02608   0.01711  -0.0117   0.6051   0.8509
   4.250   0.4856   0.02589   0.01621  -0.0111   0.4753   0.8537
   4.500   0.5040   0.02682   0.01637  -0.0096   0.3671   0.8568
   4.750   0.5191   0.02771   0.01681  -0.0079   0.3011   0.8595
   5.000   0.5372   0.02860   0.01736  -0.0068   0.2574   0.8621
   5.250   0.5584   0.02941   0.01798  -0.0063   0.2269   0.8652
   5.500   0.5816   0.03027   0.01863  -0.0062   0.2051   0.8685
   5.750   0.6082   0.03111   0.01939  -0.0066   0.1871   0.8717
   6.000   0.6337   0.03184   0.02006  -0.0065   0.1732   0.8747
   6.250   0.6614   0.03255   0.02083  -0.0067   0.1609   0.8776
   6.500   0.6909   0.03340   0.02169  -0.0073   0.1510   0.8804
   6.750   0.7202   0.03432   0.02255  -0.0079   0.1422   0.8833
   7.000   0.7512   0.03537   0.02374  -0.0088   0.1342   0.8865
   7.250   0.7785   0.03634   0.02469  -0.0090   0.1277   0.8898
   7.500   0.8052   0.03750   0.02598  -0.0091   0.1219   0.8934
   7.750   0.8315   0.03871   0.02735  -0.0093   0.1164   0.8971
   8.000   0.8590   0.04001   0.02852  -0.0099   0.1120   0.9007
   8.250   0.8821   0.04163   0.03058  -0.0097   0.1074   0.9040
   8.500   0.9040   0.04312   0.03227  -0.0094   0.1035   0.9075
   8.750   0.9272   0.04449   0.03364  -0.0094   0.1002   0.9114
   9.000   0.9452   0.04663   0.03617  -0.0089   0.0969   0.9156
   9.250   0.9599   0.04882   0.03875  -0.0080   0.0942   0.9199
   9.500   0.9750   0.05075   0.04091  -0.0071   0.0915   0.9248
   9.750   0.9930   0.05246   0.04271  -0.0069   0.0892   0.9297
  10.000   1.0012   0.05497   0.04552  -0.0056   0.0872   0.9347
  10.250   0.9987   0.05833   0.04941  -0.0037   0.0857   0.9404
  10.500   0.9929   0.06184   0.05336  -0.0020   0.0845   0.9464
  10.750   0.9809   0.06537   0.05727   0.0000   0.0836   0.9536
  11.000   0.9633   0.06930   0.06154   0.0015   0.0829   0.9625
  11.250   0.9384   0.07417   0.06674   0.0017   0.0825   0.9762
  11.500   0.9011   0.08113   0.07404  -0.0006   0.0827   1.0000
  11.750   0.8471   0.09279   0.08601  -0.0079   0.0835   1.0000
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