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NASA SC(2)-0612 AIRFOIL (sc20612-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NASA SC(2)-0612 AIRFOIL (sc20612-il)
Reynolds number: 200,000
Max Cl/Cd: 40.53 at α=2.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sc20612-il-200000.txt
Download as CSV file: xf-sc20612-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA SC(2)-0612 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
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.5838   0.12573   0.12150  -0.0307   1.0000   0.0785
 -12.750  -0.7536   0.07520   0.07064  -0.0595   1.0000   0.0505
 -12.500  -0.7726   0.06947   0.06483  -0.0617   1.0000   0.0501
 -12.250  -0.7969   0.06411   0.05936  -0.0632   1.0000   0.0497
 -12.000  -0.8227   0.05958   0.05470  -0.0632   1.0000   0.0494
 -11.750  -0.8497   0.05610   0.05110  -0.0612   1.0000   0.0491
 -11.500  -0.8739   0.05273   0.04756  -0.0591   1.0000   0.0489
 -11.250  -0.8904   0.04891   0.04348  -0.0578   1.0000   0.0488
 -11.000  -0.8993   0.04518   0.03943  -0.0564   1.0000   0.0488
 -10.750  -0.9010   0.04170   0.03558  -0.0553   1.0000   0.0492
 -10.500  -0.8960   0.03871   0.03214  -0.0544   1.0000   0.0501
 -10.250  -0.8856   0.03604   0.02903  -0.0540   1.0000   0.0510
 -10.000  -0.8698   0.03372   0.02666  -0.0533   1.0000   0.0521
  -9.750  -0.8515   0.03236   0.02525  -0.0527   1.0000   0.0533
  -9.500  -0.8324   0.03090   0.02367  -0.0521   1.0000   0.0545
  -9.250  -0.8124   0.02937   0.02193  -0.0517   1.0000   0.0561
  -9.000  -0.7912   0.02798   0.02027  -0.0513   1.0000   0.0579
  -8.750  -0.7700   0.02639   0.01851  -0.0509   1.0000   0.0600
  -8.500  -0.7484   0.02547   0.01765  -0.0504   1.0000   0.0622
  -8.250  -0.7257   0.02462   0.01672  -0.0500   1.0000   0.0647
  -8.000  -0.7021   0.02376   0.01569  -0.0496   1.0000   0.0673
  -7.750  -0.6796   0.02255   0.01448  -0.0491   1.0000   0.0704
  -7.500  -0.6559   0.02194   0.01391  -0.0489   1.0000   0.0741
  -7.250  -0.6311   0.02138   0.01323  -0.0488   1.0000   0.0780
  -7.000  -0.6068   0.02038   0.01230  -0.0486   1.0000   0.0822
  -6.750  -0.5812   0.01990   0.01183  -0.0487   1.0000   0.0873
  -6.500  -0.5550   0.01928   0.01116  -0.0488   1.0000   0.0924
  -6.250  -0.5284   0.01869   0.01067  -0.0492   1.0000   0.0980
  -6.000  -0.5014   0.01838   0.01028  -0.0495   1.0000   0.1038
  -5.750  -0.4727   0.01767   0.00971  -0.0504   1.0000   0.1114
  -5.500  -0.4439   0.01725   0.00930  -0.0512   1.0000   0.1196
  -5.250  -0.4133   0.01674   0.00889  -0.0525   1.0000   0.1308
  -5.000  -0.3806   0.01620   0.00846  -0.0543   1.0000   0.1471
  -4.750  -0.3417   0.01535   0.00793  -0.0578   1.0000   0.1873
  -4.500  -0.2744   0.01315   0.00760  -0.0685   1.0000   0.5253
  -4.250  -0.2517   0.01357   0.00817  -0.0672   1.0000   0.5945
  -4.000  -0.2282   0.01400   0.00858  -0.0662   1.0000   0.6232
  -3.750  -0.2073   0.01450   0.00908  -0.0646   1.0000   0.6405
  -3.500  -0.1857   0.01501   0.00956  -0.0633   1.0000   0.6554
  -3.250  -0.1690   0.01560   0.01019  -0.0607   1.0000   0.6653
  -3.000  -0.1489   0.01610   0.01068  -0.0590   1.0000   0.6752
  -2.750  -0.1304   0.01663   0.01122  -0.0570   1.0000   0.6839
  -2.500  -0.1027   0.01717   0.01176  -0.0566   0.9973   0.6932
  -2.250  -0.0715   0.01791   0.01252  -0.0565   0.9937   0.7048
  -2.000  -0.0481   0.01859   0.01326  -0.0545   0.9881   0.7135
  -1.750  -0.0129   0.01918   0.01384  -0.0555   0.9840   0.7269
  -1.500   0.0055   0.01978   0.01451  -0.0522   0.9777   0.7329
  -1.250   0.0420   0.02009   0.01481  -0.0538   0.9729   0.7434
  -1.000   0.0767   0.02022   0.01497  -0.0546   0.9679   0.7482
  -0.750   0.1077   0.02022   0.01499  -0.0549   0.9603   0.7518
  -0.500   0.1515   0.02015   0.01494  -0.0580   0.9564   0.7561
  -0.250   0.1952   0.01997   0.01474  -0.0619   0.9481   0.7630
   0.000   0.2413   0.01933   0.01416  -0.0640   0.9366   0.7654
   0.250   0.2945   0.01856   0.01343  -0.0677   0.9276   0.7677
   0.500   0.3385   0.01789   0.01281  -0.0699   0.9165   0.7702
   0.750   0.3873   0.01699   0.01195  -0.0729   0.9048   0.7731
   1.000   0.4328   0.01627   0.01128  -0.0756   0.8941   0.7768
   1.250   0.4755   0.01572   0.01076  -0.0785   0.8786   0.7802
   1.500   0.5023   0.01529   0.01038  -0.0774   0.8586   0.7818
   1.750   0.5332   0.01484   0.00995  -0.0770   0.8316   0.7836
   2.000   0.5615   0.01454   0.00960  -0.0761   0.7854   0.7856
   2.250   0.5893   0.01454   0.00920  -0.0750   0.6769   0.7879
   2.500   0.6004   0.01592   0.00931  -0.0715   0.4408   0.7909
   2.750   0.6154   0.01755   0.00987  -0.0700   0.2445   0.7942
   3.000   0.6409   0.01862   0.01040  -0.0704   0.1663   0.7974
   3.250   0.6613   0.01919   0.01079  -0.0689   0.1432   0.7993
   3.500   0.6847   0.01967   0.01121  -0.0681   0.1293   0.8012
   3.750   0.7095   0.02019   0.01169  -0.0676   0.1192   0.8033
   4.000   0.7344   0.02092   0.01229  -0.0674   0.1104   0.8056
   4.250   0.7631   0.02126   0.01269  -0.0677   0.1036   0.8080
   4.500   0.7910   0.02208   0.01339  -0.0682   0.0969   0.8105
   4.750   0.8228   0.02258   0.01396  -0.0693   0.0910   0.8133
   5.000   0.8464   0.02311   0.01445  -0.0685   0.0860   0.8155
   5.250   0.8705   0.02397   0.01535  -0.0678   0.0814   0.8177
   5.500   0.8960   0.02449   0.01592  -0.0673   0.0767   0.8202
   5.750   0.9228   0.02581   0.01712  -0.0675   0.0723   0.8229
   6.000   0.9510   0.02647   0.01797  -0.0676   0.0691   0.8259
   6.250   0.9804   0.02726   0.01880  -0.0682   0.0655   0.8285
   6.500   1.0088   0.02886   0.02030  -0.0688   0.0624   0.8306
   6.750   1.0323   0.02960   0.02130  -0.0678   0.0602   0.8327
   7.000   1.0567   0.03071   0.02259  -0.0672   0.0580   0.8350
   7.250   1.0811   0.03175   0.02372  -0.0667   0.0561   0.8379
   7.500   1.1071   0.03335   0.02528  -0.0670   0.0543   0.8410
   7.750   1.1300   0.03518   0.02747  -0.0664   0.0526   0.8439
   8.000   1.1514   0.03706   0.02971  -0.0656   0.0510   0.8463
   8.250   1.1686   0.03903   0.03200  -0.0639   0.0499   0.8485
   8.500   1.1852   0.04110   0.03433  -0.0624   0.0490   0.8510
   8.750   1.2017   0.04316   0.03662  -0.0611   0.0483   0.8538
   9.000   1.2201   0.04509   0.03865  -0.0603   0.0475   0.8567
   9.250   1.2361   0.04782   0.04150  -0.0596   0.0467   0.8599
   9.500   1.2382   0.05191   0.04596  -0.0570   0.0462   0.8625
   9.750   1.2312   0.05533   0.04990  -0.0529   0.0459   0.8651
  10.000   1.2200   0.05938   0.05439  -0.0491   0.0457   0.8678
  10.250   1.2063   0.06361   0.05896  -0.0456   0.0458   0.8705
  10.500   1.1896   0.06753   0.06312  -0.0420   0.0460   0.8732
  10.750   1.1741   0.07187   0.06763  -0.0394   0.0462   0.8760
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