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NASA SC(2)-0714 AIRFOIL (sc20714-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NASA SC(2)-0714 AIRFOIL (sc20714-il)
Reynolds number: 100,000
Max Cl/Cd: 31.01 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sc20714-il-100000-n5.txt
Download as CSV file: xf-sc20714-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA SC(2)-0714 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
  ------ -------- --------- --------- -------- -------- --------
 -13.750  -0.8006   0.07178   0.06477  -0.0703   1.0000   0.0509
 -13.500  -0.8352   0.06590   0.05866  -0.0714   1.0000   0.0510
 -13.250  -0.8598   0.06173   0.05431  -0.0709   1.0000   0.0511
 -13.000  -0.8803   0.05839   0.05080  -0.0696   1.0000   0.0514
 -12.750  -0.8984   0.05561   0.04786  -0.0675   1.0000   0.0517
 -12.500  -0.9159   0.05328   0.04539  -0.0646   1.0000   0.0521
 -12.250  -0.9337   0.05129   0.04326  -0.0610   1.0000   0.0525
 -12.000  -0.9457   0.04916   0.04095  -0.0583   1.0000   0.0532
 -11.750  -0.9520   0.04682   0.03836  -0.0564   1.0000   0.0540
 -11.500  -0.9544   0.04437   0.03555  -0.0552   1.0000   0.0551
 -11.250  -0.9446   0.04290   0.03404  -0.0540   1.0000   0.0560
 -11.000  -0.9331   0.04163   0.03272  -0.0530   1.0000   0.0569
 -10.750  -0.9209   0.04027   0.03128  -0.0520   1.0000   0.0580
 -10.500  -0.9076   0.03883   0.02969  -0.0510   1.0000   0.0592
 -10.250  -0.8931   0.03736   0.02803  -0.0501   1.0000   0.0607
 -10.000  -0.8774   0.03594   0.02631  -0.0493   1.0000   0.0625
  -9.750  -0.8601   0.03491   0.02533  -0.0485   1.0000   0.0640
  -9.500  -0.8420   0.03399   0.02441  -0.0478   1.0000   0.0657
  -9.250  -0.8232   0.03302   0.02336  -0.0471   1.0000   0.0676
  -9.000  -0.8038   0.03203   0.02222  -0.0464   1.0000   0.0697
  -8.750  -0.7840   0.03112   0.02124  -0.0456   1.0000   0.0718
  -8.500  -0.7638   0.03035   0.02054  -0.0451   1.0000   0.0740
  -8.250  -0.7427   0.02963   0.01978  -0.0447   1.0000   0.0768
  -8.000  -0.7211   0.02892   0.01897  -0.0441   1.0000   0.0798
  -7.750  -0.6996   0.02820   0.01830  -0.0437   1.0000   0.0825
  -7.500  -0.6771   0.02757   0.01770  -0.0435   1.0000   0.0861
  -7.250  -0.6540   0.02700   0.01706  -0.0432   1.0000   0.0902
  -7.000  -0.6307   0.02634   0.01647  -0.0432   1.0000   0.0941
  -6.750  -0.6063   0.02579   0.01595  -0.0434   1.0000   0.0993
  -6.500  -0.5794   0.02524   0.01542  -0.0440   0.9994   0.1051
  -6.250  -0.5471   0.02471   0.01495  -0.0457   0.9976   0.1126
  -6.000  -0.5140   0.02420   0.01452  -0.0476   0.9958   0.1220
  -5.750  -0.4804   0.02376   0.01414  -0.0495   0.9941   0.1346
  -5.500  -0.4459   0.02330   0.01381  -0.0518   0.9928   0.1519
  -5.250  -0.4121   0.02280   0.01347  -0.0539   0.9908   0.1787
  -5.000  -0.3749   0.02209   0.01309  -0.0572   0.9892   0.2277
  -4.750  -0.3290   0.02084   0.01267  -0.0633   0.9890   0.3584
  -4.500  -0.3093   0.02132   0.01402  -0.0603   0.9857   0.4767
  -4.250  -0.2897   0.02248   0.01539  -0.0567   0.9819   0.5356
  -4.000  -0.2542   0.02280   0.01562  -0.0586   0.9792   0.5727
  -3.750  -0.2158   0.02297   0.01565  -0.0615   0.9763   0.6004
  -3.500  -0.1836   0.02349   0.01609  -0.0622   0.9727   0.6178
  -3.250  -0.1579   0.02429   0.01688  -0.0607   0.9692   0.6275
  -2.750  -0.1044   0.02542   0.01795  -0.0595   0.9609   0.6539
  -2.500  -0.0870   0.02639   0.01897  -0.0555   0.9562   0.6633
  -2.250  -0.0587   0.02701   0.01958  -0.0547   0.9527   0.6753
  -2.000  -0.0389   0.02730   0.01988  -0.0526   0.9462   0.6820
  -1.750   0.0036   0.02716   0.01967  -0.0568   0.9430   0.6902
  -1.500   0.0332   0.02728   0.01979  -0.0568   0.9394   0.6928
  -1.250   0.0584   0.02734   0.01986  -0.0561   0.9337   0.6959
  -1.000   0.0885   0.02731   0.01985  -0.0567   0.9279   0.6994
  -0.750   0.1280   0.02720   0.01973  -0.0593   0.9238   0.7036
  -0.500   0.1687   0.02698   0.01950  -0.0628   0.9176   0.7084
  -0.250   0.2027   0.02677   0.01932  -0.0640   0.9099   0.7110
   0.250   0.2645   0.02644   0.01910  -0.0647   0.8947   0.7154
   0.500   0.3108   0.02589   0.01861  -0.0676   0.8881   0.7178
   0.750   0.3486   0.02517   0.01793  -0.0687   0.8725   0.7206
   1.000   0.3901   0.02424   0.01706  -0.0703   0.8550   0.7238
   1.250   0.4325   0.02335   0.01621  -0.0724   0.8365   0.7271
   1.500   0.4607   0.02290   0.01582  -0.0723   0.8118   0.7293
   1.750   0.4923   0.02231   0.01530  -0.0720   0.7856   0.7306
   2.000   0.5245   0.02177   0.01476  -0.0718   0.7445   0.7322
   2.250   0.5977   0.02079   0.01324  -0.0782   0.6162   0.7335
   2.500   0.6251   0.02160   0.01310  -0.0776   0.4541   0.7352
   2.750   0.6438   0.02256   0.01341  -0.0762   0.3394   0.7369
   3.000   0.6650   0.02343   0.01376  -0.0755   0.2529   0.7387
   3.250   0.6893   0.02414   0.01414  -0.0754   0.1984   0.7405
   3.500   0.7153   0.02477   0.01455  -0.0756   0.1669   0.7428
   3.750   0.7427   0.02539   0.01502  -0.0761   0.1463   0.7454
   4.000   0.7714   0.02598   0.01553  -0.0769   0.1320   0.7476
   4.250   0.7939   0.02650   0.01604  -0.0760   0.1225   0.7488
   4.500   0.8159   0.02710   0.01658  -0.0752   0.1146   0.7500
   4.750   0.8395   0.02762   0.01715  -0.0745   0.1077   0.7514
   5.000   0.8624   0.02827   0.01775  -0.0739   0.1022   0.7529
   5.250   0.8865   0.02893   0.01844  -0.0734   0.0974   0.7545
   5.500   0.9109   0.02959   0.01911  -0.0730   0.0926   0.7565
   5.750   0.9353   0.03041   0.01987  -0.0728   0.0887   0.7586
   6.000   0.9625   0.03113   0.02071  -0.0730   0.0846   0.7608
   6.250   0.9893   0.03190   0.02147  -0.0733   0.0808   0.7628
   6.500   1.0173   0.03284   0.02239  -0.0740   0.0778   0.7646
   6.750   1.0430   0.03367   0.02336  -0.0738   0.0745   0.7661
   7.000   1.0657   0.03446   0.02419  -0.0732   0.0718   0.7674
   7.250   1.0891   0.03543   0.02511  -0.0728   0.0697   0.7688
   7.500   1.1136   0.03653   0.02642  -0.0723   0.0672   0.7704
   7.750   1.1366   0.03758   0.02762  -0.0718   0.0648   0.7723
   8.000   1.1588   0.03856   0.02865  -0.0713   0.0628   0.7744
   8.250   1.1823   0.03975   0.02981  -0.0711   0.0611   0.7767
   8.500   1.2051   0.04133   0.03172  -0.0706   0.0592   0.7789
   8.750   1.2271   0.04293   0.03355  -0.0703   0.0575   0.7809
   9.000   1.2478   0.04435   0.03512  -0.0698   0.0559   0.7828
   9.250   1.2645   0.04554   0.03638  -0.0685   0.0548   0.7842
   9.500   1.2802   0.04701   0.03795  -0.0672   0.0536   0.7857
   9.750   1.2881   0.04918   0.04056  -0.0647   0.0522   0.7873
  10.000   1.2954   0.05128   0.04299  -0.0623   0.0510   0.7891
  10.250   1.2999   0.05335   0.04533  -0.0597   0.0502   0.7910
  10.500   1.3013   0.05541   0.04763  -0.0568   0.0495   0.7932
  10.750   1.3038   0.05762   0.05004  -0.0544   0.0489   0.7955
  11.000   1.3064   0.05986   0.05246  -0.0524   0.0484   0.7978
  11.250   1.3093   0.06207   0.05480  -0.0506   0.0479   0.7999
  11.500   1.3094   0.06433   0.05717  -0.0485   0.0474   0.8015
  11.750   1.2860   0.06863   0.06192  -0.0454   0.0471   0.8027
  12.000   1.2585   0.07364   0.06735  -0.0432   0.0468   0.8039
  12.250   1.2280   0.07948   0.07358  -0.0425   0.0466   0.8049
  12.500   1.1926   0.08668   0.08113  -0.0438   0.0466   0.8058
  12.750   1.1511   0.09603   0.09083  -0.0480   0.0467   0.8064
  13.000   1.0968   0.11022   0.10536  -0.0577   0.0470   0.8065
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