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NASA SC(2)-0614 AIRFOIL (sc20614-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NASA SC(2)-0614 AIRFOIL (sc20614-il)
Reynolds number: 200,000
Max Cl/Cd: 38.9 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sc20614-il-200000.txt
Download as CSV file: xf-sc20614-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA SC(2)-0614 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.000  -0.9101   0.06446   0.05895  -0.0721   1.0000   0.0549
 -13.750  -0.9336   0.05999   0.05429  -0.0723   1.0000   0.0549
 -13.500  -0.9565   0.05625   0.05034  -0.0714   1.0000   0.0549
 -13.250  -0.9794   0.05328   0.04719  -0.0690   1.0000   0.0549
 -13.000  -1.0022   0.05090   0.04465  -0.0656   1.0000   0.0549
 -12.750  -1.0133   0.04785   0.04141  -0.0638   1.0000   0.0552
 -12.500  -1.0120   0.04534   0.03881  -0.0622   1.0000   0.0557
 -12.250  -1.0066   0.04355   0.03696  -0.0607   1.0000   0.0562
 -12.000  -0.9993   0.04204   0.03540  -0.0591   1.0000   0.0569
 -11.750  -0.9907   0.04069   0.03399  -0.0575   1.0000   0.0577
 -11.500  -0.9831   0.03922   0.03240  -0.0560   1.0000   0.0587
 -11.250  -0.9753   0.03754   0.03052  -0.0546   1.0000   0.0598
 -11.000  -0.9660   0.03578   0.02849  -0.0533   1.0000   0.0610
 -10.750  -0.9545   0.03419   0.02656  -0.0522   1.0000   0.0621
 -10.500  -0.9390   0.03234   0.02464  -0.0510   1.0000   0.0632
 -10.250  -0.9217   0.03128   0.02361  -0.0500   1.0000   0.0645
 -10.000  -0.9041   0.03031   0.02259  -0.0491   1.0000   0.0659
  -9.750  -0.8858   0.02935   0.02153  -0.0482   1.0000   0.0677
  -9.500  -0.8665   0.02844   0.02042  -0.0476   1.0000   0.0699
  -9.250  -0.8477   0.02721   0.01917  -0.0466   1.0000   0.0719
  -9.000  -0.8278   0.02648   0.01849  -0.0459   1.0000   0.0741
  -8.750  -0.8069   0.02577   0.01773  -0.0453   1.0000   0.0766
  -8.500  -0.7848   0.02511   0.01693  -0.0449   1.0000   0.0793
  -8.250  -0.7641   0.02415   0.01602  -0.0441   1.0000   0.0821
  -8.000  -0.7417   0.02361   0.01553  -0.0438   1.0000   0.0854
  -7.750  -0.7182   0.02313   0.01498  -0.0437   1.0000   0.0891
  -7.500  -0.6958   0.02236   0.01425  -0.0432   1.0000   0.0927
  -7.250  -0.6721   0.02186   0.01381  -0.0432   1.0000   0.0966
  -7.000  -0.6474   0.02148   0.01337  -0.0433   1.0000   0.1011
  -6.750  -0.6229   0.02081   0.01279  -0.0434   1.0000   0.1060
  -6.500  -0.5972   0.02042   0.01244  -0.0438   1.0000   0.1115
  -6.250  -0.5702   0.01994   0.01199  -0.0444   0.9999   0.1176
  -6.000  -0.5326   0.01949   0.01162  -0.0471   0.9978   0.1264
  -5.750  -0.4945   0.01893   0.01116  -0.0500   0.9959   0.1373
  -5.500  -0.4549   0.01838   0.01073  -0.0533   0.9944   0.1533
  -5.250  -0.4124   0.01767   0.01025  -0.0575   0.9933   0.1832
  -5.000  -0.3612   0.01624   0.00953  -0.0647   0.9934   0.2955
  -4.750  -0.3129   0.01528   0.00987  -0.0704   0.9936   0.5282
  -4.500  -0.2791   0.01573   0.01035  -0.0714   0.9905   0.5809
  -4.250  -0.2485   0.01628   0.01091  -0.0716   0.9864   0.6038
  -4.000  -0.2152   0.01687   0.01149  -0.0722   0.9831   0.6202
  -3.750  -0.1800   0.01750   0.01208  -0.0732   0.9806   0.6334
  -3.500  -0.1526   0.01792   0.01245  -0.0730   0.9754   0.6459
  -3.250  -0.1296   0.01873   0.01334  -0.0708   0.9709   0.6519
  -3.000  -0.0935   0.01924   0.01380  -0.0721   0.9683   0.6630
  -2.750  -0.0753   0.01986   0.01448  -0.0693   0.9623   0.6672
  -2.500  -0.0432   0.02027   0.01486  -0.0701   0.9583   0.6780
  -2.250  -0.0223   0.02114   0.01581  -0.0669   0.9546   0.6825
  -2.000   0.0107   0.02146   0.01609  -0.0681   0.9503   0.6934
  -1.750   0.0258   0.02205   0.01676  -0.0640   0.9433   0.6968
  -1.500   0.0554   0.02260   0.01734  -0.0629   0.9393   0.7053
  -1.250   0.0760   0.02294   0.01770  -0.0606   0.9316   0.7129
  -1.000   0.1070   0.02303   0.01782  -0.0603   0.9262   0.7175
  -0.750   0.1564   0.02271   0.01749  -0.0648   0.9235   0.7227
  -0.500   0.1884   0.02246   0.01725  -0.0656   0.9146   0.7272
  -0.250   0.2385   0.02181   0.01663  -0.0683   0.9086   0.7297
   0.000   0.2815   0.02123   0.01608  -0.0701   0.9011   0.7326
   0.250   0.3299   0.02041   0.01528  -0.0732   0.8937   0.7361
   0.500   0.3874   0.01938   0.01424  -0.0791   0.8847   0.7418
   0.750   0.4181   0.01879   0.01369  -0.0782   0.8751   0.7435
   1.000   0.4462   0.01834   0.01328  -0.0774   0.8627   0.7453
   1.250   0.4781   0.01778   0.01275  -0.0772   0.8483   0.7472
   1.500   0.5094   0.01729   0.01228  -0.0772   0.8305   0.7493
   1.750   0.5407   0.01690   0.01189  -0.0774   0.8088   0.7521
   2.000   0.5750   0.01653   0.01148  -0.0784   0.7796   0.7554
   2.250   0.6123   0.01624   0.01105  -0.0803   0.7317   0.7587
   2.500   0.6325   0.01626   0.01073  -0.0777   0.6350   0.7603
   2.750   0.6414   0.01730   0.01079  -0.0735   0.4628   0.7621
   3.000   0.6534   0.01845   0.01120  -0.0709   0.3268   0.7640
   3.250   0.6706   0.01946   0.01164  -0.0696   0.2312   0.7660
   3.500   0.6928   0.02023   0.01206  -0.0690   0.1807   0.7681
   3.750   0.7185   0.02085   0.01249  -0.0692   0.1539   0.7704
   4.000   0.7475   0.02147   0.01298  -0.0700   0.1376   0.7734
   4.250   0.7746   0.02208   0.01348  -0.0704   0.1268   0.7759
   4.500   0.7968   0.02247   0.01385  -0.0693   0.1190   0.7775
   4.750   0.8198   0.02304   0.01440  -0.0684   0.1126   0.7791
   5.000   0.8447   0.02347   0.01481  -0.0680   0.1068   0.7810
   5.250   0.8698   0.02425   0.01550  -0.0678   0.1017   0.7830
   5.500   0.8974   0.02470   0.01601  -0.0679   0.0971   0.7852
   5.750   0.9255   0.02533   0.01657  -0.0684   0.0929   0.7875
   6.000   0.9560   0.02626   0.01748  -0.0694   0.0890   0.7899
   6.250   0.9861   0.02684   0.01811  -0.0702   0.0851   0.7922
   6.500   1.0093   0.02747   0.01869  -0.0695   0.0819   0.7940
   6.750   1.0343   0.02852   0.01978  -0.0689   0.0791   0.7960
   7.000   1.0588   0.02923   0.02062  -0.0683   0.0763   0.7985
   7.250   1.0845   0.02997   0.02139  -0.0682   0.0736   0.8011
   7.500   1.1148   0.03152   0.02281  -0.0692   0.0708   0.8037
   7.750   1.1406   0.03230   0.02384  -0.0691   0.0685   0.8068
   8.000   1.1668   0.03333   0.02500  -0.0691   0.0663   0.8094
   8.250   1.1888   0.03425   0.02600  -0.0682   0.0646   0.8115
   8.500   1.2137   0.03557   0.02728  -0.0680   0.0631   0.8136
   8.750   1.2350   0.03736   0.02930  -0.0672   0.0617   0.8160
   9.000   1.2535   0.03882   0.03109  -0.0659   0.0602   0.8186
   9.250   1.2735   0.04031   0.03279  -0.0651   0.0586   0.8213
   9.500   1.2963   0.04167   0.03423  -0.0650   0.0573   0.8242
   9.750   1.3150   0.04304   0.03568  -0.0639   0.0564   0.8268
  10.000   1.3326   0.04495   0.03766  -0.0629   0.0555   0.8294
  10.250   1.3416   0.04782   0.04083  -0.0608   0.0549   0.8321
  10.500   1.3425   0.05049   0.04395  -0.0575   0.0544   0.8348
  10.750   1.3384   0.05363   0.04751  -0.0540   0.0540   0.8374
  11.000   1.3282   0.05703   0.05131  -0.0502   0.0537   0.8399
  11.250   1.3087   0.06018   0.05481  -0.0453   0.0534   0.8422
  11.500   1.2862   0.06388   0.05884  -0.0409   0.0533   0.8442
  11.750   1.2595   0.06821   0.06348  -0.0375   0.0533   0.8463
  12.000   1.2288   0.07334   0.06892  -0.0354   0.0534   0.8482
  12.250   1.1953   0.07943   0.07530  -0.0350   0.0536   0.8500
  12.500   1.1595   0.08668   0.08280  -0.0365   0.0539   0.8516
  12.750   1.1221   0.09536   0.09171  -0.0404   0.0543   0.8530
  13.000   1.0901   0.10480   0.10130  -0.0458   0.0547   0.8544
  13.250   1.0692   0.11366   0.11024  -0.0510   0.0551   0.8559
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