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NASA SC(2)-0712 AIRFOIL (sc20712-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NASA SC(2)-0712 AIRFOIL (sc20712-il)
Reynolds number: 50,000
Max Cl/Cd: 23.7 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sc20712-il-50000-n5.txt
Download as CSV file: xf-sc20712-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA SC(2)-0712 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
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.6858   0.08008   0.07144  -0.0578   1.0000   0.0713
 -11.500  -0.7139   0.07496   0.06626  -0.0588   1.0000   0.0712
 -11.250  -0.7420   0.07094   0.06218  -0.0580   1.0000   0.0711
 -11.000  -0.7669   0.06679   0.05788  -0.0578   1.0000   0.0712
 -10.750  -0.7792   0.06313   0.05407  -0.0575   1.0000   0.0718
 -10.500  -0.7753   0.06076   0.05169  -0.0566   1.0000   0.0731
 -10.250  -0.7738   0.05808   0.04889  -0.0559   1.0000   0.0743
 -10.000  -0.7724   0.05503   0.04560  -0.0555   1.0000   0.0755
  -9.750  -0.7682   0.05185   0.04213  -0.0552   1.0000   0.0767
  -9.500  -0.7599   0.04881   0.03876  -0.0550   1.0000   0.0783
  -9.250  -0.7485   0.04587   0.03536  -0.0550   1.0000   0.0809
  -9.000  -0.7333   0.04328   0.03241  -0.0550   1.0000   0.0835
  -8.750  -0.7154   0.04153   0.03062  -0.0543   1.0000   0.0859
  -8.500  -0.6965   0.03970   0.02861  -0.0538   1.0000   0.0886
  -8.250  -0.6766   0.03798   0.02661  -0.0534   1.0000   0.0925
  -8.000  -0.6559   0.03633   0.02471  -0.0528   1.0000   0.0965
  -7.750  -0.6359   0.03507   0.02350  -0.0517   1.0000   0.1001
  -7.500  -0.6151   0.03391   0.02221  -0.0506   1.0000   0.1048
  -7.250  -0.5941   0.03283   0.02096  -0.0494   1.0000   0.1105
  -7.000  -0.5744   0.03191   0.02015  -0.0479   1.0000   0.1159
  -6.750  -0.5537   0.03111   0.01923  -0.0464   1.0000   0.1230
  -6.500  -0.5338   0.03029   0.01848  -0.0451   1.0000   0.1306
  -6.250  -0.5127   0.02956   0.01765  -0.0440   1.0000   0.1406
  -6.000  -0.4917   0.02871   0.01695  -0.0433   1.0000   0.1522
  -5.750  -0.4693   0.02784   0.01617  -0.0430   1.0000   0.1677
  -5.500  -0.4451   0.02688   0.01538  -0.0432   1.0000   0.1898
  -5.250  -0.4176   0.02564   0.01451  -0.0448   1.0000   0.2278
  -5.000  -0.3868   0.02407   0.01371  -0.0475   1.0000   0.3207
  -4.750  -0.3760   0.02408   0.01479  -0.0427   1.0000   0.4477
  -4.250  -0.3411   0.02565   0.01645  -0.0362   1.0000   0.5930
  -4.000  -0.3207   0.02637   0.01705  -0.0340   1.0000   0.6268
  -3.750  -0.3012   0.02705   0.01760  -0.0317   1.0000   0.6537
  -3.500  -0.2882   0.02781   0.01831  -0.0274   1.0000   0.6756
  -3.250  -0.2748   0.02848   0.01894  -0.0234   1.0000   0.6983
  -3.000  -0.2583   0.02902   0.01941  -0.0205   1.0000   0.7216
  -2.750  -0.2447   0.02936   0.01970  -0.0169   1.0000   0.7395
  -2.500  -0.2295   0.02952   0.01980  -0.0139   1.0000   0.7545
  -2.250  -0.2138   0.02951   0.01976  -0.0113   1.0000   0.7663
  -2.000  -0.1933   0.02946   0.01964  -0.0102   1.0000   0.7775
  -1.750  -0.1685   0.02944   0.01954  -0.0104   1.0000   0.7881
  -1.500  -0.1507   0.02929   0.01936  -0.0087   1.0000   0.7958
  -1.250  -0.1236   0.02929   0.01931  -0.0096   1.0000   0.8042
  -1.000  -0.1033   0.02916   0.01916  -0.0088   1.0000   0.8100
  -0.750  -0.0771   0.02916   0.01914  -0.0095   1.0000   0.8159
  -0.500  -0.0503   0.02920   0.01917  -0.0104   1.0000   0.8209
  -0.250  -0.0255   0.02921   0.01919  -0.0108   0.9991   0.8255
   0.000   0.0140   0.02945   0.01943  -0.0141   0.9933   0.8299
   0.250   0.0540   0.02970   0.01970  -0.0177   0.9863   0.8342
   0.500   0.0915   0.02985   0.01991  -0.0203   0.9786   0.8377
   0.750   0.1316   0.03006   0.02018  -0.0235   0.9704   0.8412
   1.000   0.1702   0.03021   0.02042  -0.0265   0.9600   0.8447
   1.250   0.2131   0.03039   0.02070  -0.0301   0.9485   0.8482
   1.500   0.2561   0.03041   0.02085  -0.0334   0.9350   0.8513
   1.750   0.2982   0.03021   0.02080  -0.0361   0.9180   0.8543
   2.000   0.3485   0.02962   0.02038  -0.0394   0.8948   0.8573
   2.250   0.3961   0.02860   0.01955  -0.0415   0.8641   0.8601
   2.500   0.4419   0.02742   0.01856  -0.0429   0.8309   0.8627
   2.750   0.4743   0.02650   0.01784  -0.0422   0.7933   0.8653
   3.000   0.4999   0.02570   0.01721  -0.0403   0.7438   0.8685
   3.250   0.5440   0.02442   0.01589  -0.0402   0.6368   0.8714
   3.500   0.5888   0.02495   0.01476  -0.0404   0.3781   0.8739
   3.750   0.6047   0.02645   0.01550  -0.0390   0.2713   0.8774
   4.000   0.6246   0.02762   0.01627  -0.0383   0.2176   0.8807
   4.250   0.6466   0.02862   0.01702  -0.0377   0.1868   0.8842
   4.500   0.6724   0.02955   0.01787  -0.0377   0.1640   0.8879
   4.750   0.7013   0.03054   0.01880  -0.0383   0.1474   0.8915
   5.000   0.7309   0.03146   0.01971  -0.0387   0.1347   0.8952
   5.250   0.7602   0.03243   0.02062  -0.0392   0.1244   0.8990
   5.500   0.7932   0.03352   0.02187  -0.0400   0.1154   0.9029
   5.750   0.8251   0.03484   0.02306  -0.0411   0.1083   0.9066
   6.000   0.8544   0.03605   0.02459  -0.0413   0.1018   0.9103
   6.250   0.8831   0.03743   0.02600  -0.0418   0.0969   0.9141
   6.500   0.9115   0.03910   0.02785  -0.0422   0.0923   0.9180
   6.750   0.9371   0.04080   0.02989  -0.0422   0.0879   0.9222
   7.000   0.9611   0.04252   0.03178  -0.0419   0.0849   0.9269
   7.250   0.9851   0.04441   0.03369  -0.0420   0.0820   0.9320
   7.500   1.0019   0.04678   0.03667  -0.0408   0.0789   0.9372
   7.750   1.0182   0.04928   0.03961  -0.0397   0.0765   0.9427
   8.000   1.0332   0.05188   0.04256  -0.0387   0.0747   0.9487
   8.250   1.0483   0.05412   0.04501  -0.0379   0.0728   0.9558
   8.500   1.0644   0.05645   0.04739  -0.0374   0.0710   0.9647
   8.750   1.0609   0.06028   0.05191  -0.0350   0.0696   0.9820
   9.000   1.0560   0.06448   0.05665  -0.0332   0.0685   1.0000
   9.250   1.0465   0.06889   0.06149  -0.0314   0.0679   1.0000
   9.500   1.0302   0.07332   0.06628  -0.0296   0.0677   1.0000
   9.750   1.0086   0.07830   0.07157  -0.0285   0.0677   1.0000
  10.000   0.9820   0.08421   0.07775  -0.0290   0.0679   1.0000
  10.250   0.9507   0.09161   0.08539  -0.0319   0.0683   1.0000
  10.500   0.9186   0.10094   0.09489  -0.0378   0.0688   1.0000
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