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NASA SC(2)-0714 AIRFOIL (sc20714-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NASA SC(2)-0714 AIRFOIL (sc20714-il)
Reynolds number: 200,000
Max Cl/Cd: 35.97 at α=2.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sc20714-il-200000.txt
Download as CSV file: xf-sc20714-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.000  -0.6533   0.10077   0.09631  -0.0563   1.0000   0.0630
 -13.750  -0.6452   0.09927   0.09484  -0.0553   1.0000   0.0634
 -13.500  -0.9131   0.06294   0.05746  -0.0711   1.0000   0.0552
 -13.250  -0.9388   0.05986   0.05426  -0.0684   1.0000   0.0551
 -13.000  -0.9661   0.05744   0.05172  -0.0644   1.0000   0.0551
 -12.750  -0.9909   0.05502   0.04916  -0.0606   1.0000   0.0551
 -12.500  -1.0085   0.05198   0.04589  -0.0587   1.0000   0.0551
 -12.250  -1.0183   0.04879   0.04243  -0.0573   1.0000   0.0553
 -12.000  -1.0158   0.04567   0.03917  -0.0561   1.0000   0.0558
 -11.750  -1.0069   0.04363   0.03706  -0.0551   1.0000   0.0564
 -11.500  -0.9947   0.04208   0.03546  -0.0541   1.0000   0.0571
 -11.250  -0.9821   0.04054   0.03385  -0.0532   1.0000   0.0579
 -11.000  -0.9689   0.03892   0.03207  -0.0526   1.0000   0.0590
 -10.750  -0.9547   0.03708   0.03000  -0.0523   1.0000   0.0603
 -10.500  -0.9384   0.03519   0.02779  -0.0522   1.0000   0.0616
 -10.250  -0.9194   0.03359   0.02582  -0.0524   1.0000   0.0627
 -10.000  -0.9009   0.03171   0.02397  -0.0515   1.0000   0.0639
  -9.750  -0.8802   0.03069   0.02294  -0.0510   1.0000   0.0653
  -9.500  -0.8586   0.02976   0.02195  -0.0508   1.0000   0.0670
  -9.250  -0.8359   0.02884   0.02090  -0.0506   1.0000   0.0691
  -9.000  -0.8115   0.02804   0.01985  -0.0509   1.0000   0.0710
  -8.750  -0.7911   0.02678   0.01868  -0.0499   1.0000   0.0730
  -8.500  -0.7682   0.02608   0.01801  -0.0495   1.0000   0.0751
  -8.250  -0.7443   0.02543   0.01731  -0.0494   1.0000   0.0776
  -8.000  -0.7190   0.02491   0.01663  -0.0495   1.0000   0.0803
  -7.750  -0.6972   0.02401   0.01586  -0.0488   1.0000   0.0832
  -7.500  -0.6726   0.02350   0.01538  -0.0487   1.0000   0.0864
  -7.250  -0.6471   0.02303   0.01485  -0.0488   1.0000   0.0898
  -7.000  -0.6228   0.02234   0.01423  -0.0486   1.0000   0.0936
  -6.750  -0.5966   0.02188   0.01383  -0.0490   1.0000   0.0982
  -6.500  -0.5694   0.02154   0.01342  -0.0494   1.0000   0.1030
  -6.250  -0.5413   0.02087   0.01292  -0.0503   1.0000   0.1095
  -6.000  -0.5122   0.02051   0.01256  -0.0512   1.0000   0.1170
  -5.750  -0.4805   0.01999   0.01216  -0.0530   1.0000   0.1274
  -5.500  -0.4466   0.01947   0.01177  -0.0553   1.0000   0.1421
  -5.250  -0.4080   0.01884   0.01135  -0.0588   1.0000   0.1673
  -5.000  -0.3495   0.01749   0.01068  -0.0676   1.0000   0.2701
  -4.750  -0.2973   0.01674   0.01149  -0.0739   1.0000   0.5416
  -4.500  -0.2757   0.01732   0.01209  -0.0725   1.0000   0.5849
  -4.250  -0.2559   0.01796   0.01272  -0.0707   1.0000   0.6061
  -4.000  -0.2365   0.01862   0.01335  -0.0688   1.0000   0.6213
  -3.750  -0.2109   0.01932   0.01401  -0.0681   0.9986   0.6357
  -3.500  -0.1873   0.02044   0.01518  -0.0658   0.9943   0.6422
  -3.250  -0.1535   0.02113   0.01581  -0.0667   0.9904   0.6540
  -3.000  -0.1314   0.02201   0.01674  -0.0643   0.9851   0.6580
  -2.750  -0.1025   0.02290   0.01763  -0.0635   0.9818   0.6648
  -2.500  -0.0749   0.02337   0.01808  -0.0632   0.9764   0.6736
  -2.250  -0.0542   0.02419   0.01894  -0.0602   0.9709   0.6778
  -2.000  -0.0133   0.02483   0.01955  -0.0626   0.9681   0.6909
  -1.750  -0.0073   0.02550   0.02030  -0.0562   0.9590   0.6951
  -1.500   0.0316   0.02619   0.02097  -0.0578   0.9548   0.7100
  -1.250   0.0432   0.02644   0.02128  -0.0528   0.9459   0.7137
  -1.000   0.0771   0.02649   0.02135  -0.0531   0.9404   0.7183
  -0.750   0.1163   0.02640   0.02125  -0.0555   0.9351   0.7235
  -0.500   0.1596   0.02619   0.02103  -0.0598   0.9288   0.7298
  -0.250   0.1994   0.02576   0.02064  -0.0609   0.9233   0.7321
   0.000   0.2337   0.02511   0.02002  -0.0609   0.9108   0.7349
   0.250   0.2960   0.02399   0.01892  -0.0661   0.9053   0.7377
   0.500   0.3302   0.02337   0.01833  -0.0670   0.8930   0.7412
   0.750   0.3983   0.02210   0.01710  -0.0741   0.8887   0.7446
   1.000   0.4406   0.02138   0.01641  -0.0771   0.8768   0.7481
   1.250   0.4907   0.02013   0.01522  -0.0797   0.8708   0.7498
   1.500   0.5187   0.01939   0.01454  -0.0785   0.8541   0.7518
   1.750   0.5465   0.01879   0.01399  -0.0776   0.8319   0.7541
   2.000   0.5836   0.01814   0.01333  -0.0785   0.7990   0.7565
   2.250   0.6320   0.01757   0.01247  -0.0816   0.7097   0.7589
   2.500   0.6544   0.01847   0.01230  -0.0802   0.5224   0.7620
   2.750   0.6694   0.01988   0.01278  -0.0789   0.3572   0.7647
   3.000   0.6839   0.02100   0.01318  -0.0772   0.2335   0.7659
   3.250   0.7002   0.02173   0.01352  -0.0753   0.1782   0.7670
   3.500   0.7204   0.02225   0.01388  -0.0740   0.1524   0.7683
   3.750   0.7410   0.02276   0.01429  -0.0727   0.1372   0.7700
   4.000   0.7633   0.02335   0.01478  -0.0718   0.1266   0.7718
   4.250   0.7898   0.02375   0.01516  -0.0719   0.1178   0.7732
   4.500   0.8163   0.02436   0.01572  -0.0721   0.1108   0.7744
   4.750   0.8444   0.02482   0.01615  -0.0725   0.1047   0.7758
   5.000   0.8730   0.02559   0.01685  -0.0732   0.0995   0.7772
   5.250   0.9031   0.02609   0.01737  -0.0740   0.0947   0.7787
   5.500   0.9349   0.02696   0.01812  -0.0755   0.0902   0.7808
   5.750   0.9700   0.02780   0.01901  -0.0774   0.0864   0.7827
   6.000   0.9942   0.02825   0.01950  -0.0768   0.0829   0.7837
   6.250   1.0200   0.02897   0.02015  -0.0767   0.0798   0.7848
   6.500   1.0471   0.02988   0.02114  -0.0767   0.0770   0.7860
   6.750   1.0734   0.03060   0.02197  -0.0765   0.0742   0.7872
   7.000   1.1001   0.03135   0.02271  -0.0766   0.0717   0.7886
   7.250   1.1302   0.03281   0.02414  -0.0775   0.0691   0.7900
   7.500   1.1549   0.03364   0.02520  -0.0770   0.0668   0.7916
   7.750   1.1814   0.03468   0.02634  -0.0771   0.0647   0.7936
   8.000   1.2088   0.03578   0.02749  -0.0775   0.0630   0.7958
   8.250   1.2418   0.03806   0.02969  -0.0793   0.0613   0.7976
   8.500   1.2629   0.03939   0.03141  -0.0786   0.0599   0.7992
   8.750   1.2808   0.04088   0.03322  -0.0771   0.0584   0.8004
   9.000   1.2979   0.04222   0.03475  -0.0756   0.0570   0.8016
   9.250   1.3171   0.04348   0.03609  -0.0745   0.0559   0.8030
   9.500   1.3365   0.04495   0.03763  -0.0737   0.0550   0.8045
   9.750   1.3557   0.04740   0.04015  -0.0732   0.0541   0.8061
  10.000   1.3609   0.05026   0.04340  -0.0704   0.0536   0.8076
  10.250   1.3597   0.05315   0.04674  -0.0668   0.0532   0.8093
  10.500   1.3522   0.05640   0.05043  -0.0626   0.0529   0.8112
  10.750   1.3375   0.05973   0.05414  -0.0579   0.0526   0.8130
  11.000   1.3171   0.06320   0.05795  -0.0530   0.0524   0.8145
  11.250   1.2942   0.06740   0.06248  -0.0491   0.0524   0.8157
  11.500   1.2664   0.07199   0.06739  -0.0457   0.0524   0.8166
  11.750   1.2363   0.07714   0.07282  -0.0434   0.0525   0.8173
  12.000   1.2039   0.08311   0.07906  -0.0427   0.0527   0.8180
  12.250   1.1699   0.09005   0.08623  -0.0439   0.0530   0.8186
  12.500   1.1393   0.09770   0.09407  -0.0469   0.0534   0.8192
  12.750   1.1127   0.10597   0.10248  -0.0512   0.0537   0.8198
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