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NASA SC(2)-0012 AIRFOIL (sc20012-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NASA SC(2)-0012 AIRFOIL (sc20012-il)
Reynolds number: 100,000
Max Cl/Cd: 29.67 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sc20012-il-100000-n5.txt
Download as CSV file: xf-sc20012-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA SC(2)-0012 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.8509   0.07995   0.07399  -0.0256   1.0000   0.0396
 -12.250  -0.8938   0.07036   0.06414  -0.0311   1.0000   0.0392
 -12.000  -0.9261   0.06384   0.05734  -0.0330   1.0000   0.0392
 -11.750  -0.9515   0.05890   0.05211  -0.0328   1.0000   0.0394
 -11.500  -0.9727   0.05487   0.04776  -0.0310   1.0000   0.0398
 -11.250  -0.9908   0.05139   0.04392  -0.0279   1.0000   0.0403
 -11.000  -1.0027   0.04774   0.03978  -0.0250   1.0000   0.0410
 -10.750  -0.9993   0.04523   0.03702  -0.0231   1.0000   0.0418
 -10.500  -0.9879   0.04353   0.03522  -0.0218   1.0000   0.0425
 -10.250  -0.9765   0.04168   0.03321  -0.0205   1.0000   0.0435
 -10.000  -0.9644   0.03969   0.03097  -0.0191   1.0000   0.0446
  -9.750  -0.9514   0.03761   0.02856  -0.0176   1.0000   0.0463
  -9.500  -0.9366   0.03568   0.02630  -0.0163   1.0000   0.0482
  -9.250  -0.9178   0.03458   0.02521  -0.0156   1.0000   0.0499
  -9.000  -0.8990   0.03329   0.02376  -0.0147   1.0000   0.0520
  -8.750  -0.8795   0.03176   0.02192  -0.0137   1.0000   0.0546
  -8.500  -0.8590   0.03055   0.02070  -0.0130   1.0000   0.0568
  -8.250  -0.8381   0.02958   0.01969  -0.0122   1.0000   0.0594
  -8.000  -0.8165   0.02847   0.01836  -0.0114   1.0000   0.0627
  -7.750  -0.7950   0.02741   0.01730  -0.0107   1.0000   0.0655
  -7.500  -0.7734   0.02654   0.01643  -0.0100   1.0000   0.0687
  -7.250  -0.7512   0.02568   0.01541  -0.0092   1.0000   0.0725
  -7.000  -0.7300   0.02476   0.01454  -0.0083   1.0000   0.0758
  -6.750  -0.7089   0.02401   0.01380  -0.0074   1.0000   0.0795
  -6.500  -0.6875   0.02331   0.01301  -0.0064   1.0000   0.0838
  -6.250  -0.6683   0.02253   0.01230  -0.0051   1.0000   0.0876
  -6.000  -0.6494   0.02191   0.01170  -0.0038   1.0000   0.0921
  -5.750  -0.6314   0.02134   0.01111  -0.0022   1.0000   0.0971
  -5.500  -0.6156   0.02075   0.01059  -0.0003   1.0000   0.1021
  -5.250  -0.6003   0.02031   0.01013   0.0017   1.0000   0.1082
  -5.000  -0.5814   0.01976   0.00967   0.0028   0.9980   0.1156
  -4.750  -0.5485   0.01912   0.00908   0.0012   0.9912   0.1280
  -4.500  -0.5157   0.01848   0.00853  -0.0004   0.9843   0.1459
  -4.250  -0.4838   0.01782   0.00804  -0.0018   0.9773   0.1740
  -4.000  -0.4520   0.01708   0.00759  -0.0033   0.9711   0.2240
  -3.750  -0.4240   0.01619   0.00715  -0.0041   0.9641   0.3091
  -3.500  -0.3994   0.01510   0.00683  -0.0042   0.9572   0.4490
  -3.250  -0.3739   0.01470   0.00723  -0.0031   0.9516   0.6030
  -3.000  -0.3460   0.01476   0.00733  -0.0028   0.9443   0.6699
  -2.750  -0.3154   0.01485   0.00741  -0.0029   0.9388   0.7098
  -2.500  -0.2870   0.01498   0.00756  -0.0025   0.9325   0.7388
  -2.250  -0.2589   0.01511   0.00767  -0.0020   0.9259   0.7617
  -2.000  -0.2287   0.01522   0.00777  -0.0019   0.9209   0.7812
  -1.750  -0.2017   0.01540   0.00794  -0.0010   0.9151   0.8014
  -1.500  -0.1754   0.01559   0.00815   0.0001   0.9092   0.8200
  -1.250  -0.1459   0.01575   0.00830   0.0005   0.9043   0.8353
  -1.000  -0.1161   0.01583   0.00834   0.0006   0.8995   0.8479
  -0.750  -0.0890   0.01593   0.00844   0.0010   0.8932   0.8579
  -0.500  -0.0602   0.01594   0.00843   0.0008   0.8882   0.8657
  -0.250  -0.0277   0.01594   0.00842   0.0001   0.8837   0.8709
   0.000   0.0000   0.01595   0.00842   0.0000   0.8774   0.8774
   0.250   0.0277   0.01594   0.00842  -0.0001   0.8709   0.8838
   0.500   0.0602   0.01594   0.00843  -0.0008   0.8657   0.8882
   0.750   0.0890   0.01593   0.00844  -0.0010   0.8579   0.8932
   1.000   0.1161   0.01582   0.00834  -0.0006   0.8479   0.8995
   1.250   0.1459   0.01575   0.00830  -0.0005   0.8353   0.9043
   1.500   0.1754   0.01559   0.00815  -0.0001   0.8200   0.9092
   1.750   0.2017   0.01540   0.00794   0.0010   0.8013   0.9151
   2.000   0.2287   0.01522   0.00777   0.0019   0.7812   0.9210
   2.250   0.2589   0.01511   0.00767   0.0020   0.7617   0.9259
   2.500   0.2870   0.01498   0.00756   0.0025   0.7388   0.9325
   2.750   0.3154   0.01485   0.00740   0.0029   0.7099   0.9388
   3.000   0.3460   0.01476   0.00733   0.0028   0.6700   0.9443
   3.250   0.3739   0.01469   0.00723   0.0031   0.6030   0.9517
   3.500   0.3994   0.01510   0.00682   0.0042   0.4488   0.9572
   3.750   0.4240   0.01619   0.00715   0.0041   0.3090   0.9641
   4.000   0.4521   0.01708   0.00759   0.0033   0.2239   0.9711
   4.250   0.4839   0.01782   0.00804   0.0018   0.1740   0.9774
   4.500   0.5158   0.01848   0.00853   0.0004   0.1459   0.9843
   4.750   0.5486   0.01912   0.00907  -0.0012   0.1280   0.9912
   5.000   0.5815   0.01976   0.00966  -0.0028   0.1156   0.9980
   5.250   0.6002   0.02030   0.01013  -0.0016   0.1082   1.0000
   5.500   0.6156   0.02075   0.01059   0.0004   0.1021   1.0000
   5.750   0.6314   0.02134   0.01110   0.0022   0.0971   1.0000
   6.000   0.6494   0.02191   0.01170   0.0038   0.0921   1.0000
   6.250   0.6683   0.02253   0.01230   0.0052   0.0876   1.0000
   6.500   0.6875   0.02331   0.01300   0.0064   0.0838   1.0000
   6.750   0.7089   0.02401   0.01380   0.0074   0.0795   1.0000
   7.000   0.7300   0.02476   0.01454   0.0083   0.0758   1.0000
   7.250   0.7513   0.02568   0.01541   0.0092   0.0725   1.0000
   7.500   0.7735   0.02654   0.01643   0.0100   0.0687   1.0000
   7.750   0.7951   0.02741   0.01730   0.0107   0.0656   1.0000
   8.000   0.8166   0.02847   0.01836   0.0114   0.0627   1.0000
   8.250   0.8382   0.02958   0.01968   0.0122   0.0594   1.0000
   8.500   0.8591   0.03055   0.02069   0.0129   0.0568   1.0000
   8.750   0.8796   0.03177   0.02193   0.0136   0.0545   1.0000
   9.000   0.8991   0.03330   0.02377   0.0146   0.0520   1.0000
   9.250   0.9179   0.03458   0.02521   0.0155   0.0499   1.0000
   9.500   0.9367   0.03568   0.02629   0.0163   0.0482   1.0000
   9.750   0.9516   0.03761   0.02856   0.0176   0.0463   1.0000
  10.000   0.9646   0.03970   0.03097   0.0190   0.0446   1.0000
  10.250   0.9767   0.04169   0.03321   0.0204   0.0435   1.0000
  10.500   0.9881   0.04353   0.03523   0.0218   0.0425   1.0000
  10.750   0.9997   0.04523   0.03701   0.0230   0.0417   1.0000
  11.000   1.0030   0.04775   0.03979   0.0249   0.0410   1.0000
  11.250   0.9910   0.05142   0.04395   0.0278   0.0403   1.0000
  11.500   0.9729   0.05491   0.04780   0.0309   0.0398   1.0000
  11.750   0.9520   0.05894   0.05215   0.0327   0.0394   1.0000
  12.000   0.9265   0.06389   0.05739   0.0329   0.0392   1.0000
  12.250   0.8942   0.07045   0.06423   0.0309   0.0392   1.0000
  12.500   0.8513   0.08007   0.07412   0.0254   0.0397   1.0000
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