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NASA SC(2)-0012 AIRFOIL (sc20012-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NASA SC(2)-0012 AIRFOIL (sc20012-il)
Reynolds number: 50,000
Max Cl/Cd: 23.61 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sc20012-il-50000-n5.txt
Download as CSV file: xf-sc20012-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.7111   0.10060   0.09259  -0.0151   1.0000   0.0702
 -11.250  -0.7442   0.08936   0.08131  -0.0228   1.0000   0.0694
 -11.000  -0.7825   0.08028   0.07210  -0.0282   1.0000   0.0686
 -10.750  -0.8150   0.07383   0.06547  -0.0301   1.0000   0.0682
 -10.500  -0.8411   0.06907   0.06051  -0.0294   1.0000   0.0683
 -10.250  -0.8601   0.06509   0.05629  -0.0276   1.0000   0.0688
 -10.000  -0.8724   0.06121   0.05211  -0.0258   1.0000   0.0698
  -9.750  -0.8807   0.05740   0.04789  -0.0239   1.0000   0.0712
  -9.500  -0.8858   0.05356   0.04352  -0.0217   1.0000   0.0727
  -9.250  -0.8784   0.05061   0.04030  -0.0202   1.0000   0.0744
  -9.000  -0.8641   0.04852   0.03811  -0.0193   1.0000   0.0766
  -8.750  -0.8509   0.04631   0.03568  -0.0181   1.0000   0.0795
  -8.500  -0.8386   0.04372   0.03262  -0.0166   1.0000   0.0828
  -8.250  -0.8220   0.04142   0.03003  -0.0155   1.0000   0.0857
  -8.000  -0.8023   0.03982   0.02839  -0.0148   1.0000   0.0894
  -7.750  -0.7827   0.03800   0.02629  -0.0138   1.0000   0.0938
  -7.500  -0.7613   0.03620   0.02424  -0.0131   1.0000   0.0980
  -7.250  -0.7391   0.03485   0.02289  -0.0124   1.0000   0.1028
  -7.000  -0.7157   0.03341   0.02119  -0.0117   1.0000   0.1083
  -6.750  -0.6918   0.03210   0.01993  -0.0112   1.0000   0.1138
  -6.500  -0.6675   0.03096   0.01868  -0.0106   1.0000   0.1206
  -6.250  -0.6429   0.02984   0.01758  -0.0100   1.0000   0.1274
  -6.000  -0.6194   0.02889   0.01659  -0.0092   1.0000   0.1360
  -5.750  -0.5972   0.02793   0.01569  -0.0082   1.0000   0.1446
  -5.500  -0.5768   0.02706   0.01483  -0.0070   1.0000   0.1559
  -5.250  -0.5586   0.02620   0.01404  -0.0054   1.0000   0.1691
  -5.000  -0.5430   0.02533   0.01331  -0.0036   1.0000   0.1855
  -4.750  -0.5290   0.02445   0.01260  -0.0016   1.0000   0.2086
  -4.500  -0.5169   0.02350   0.01193   0.0007   1.0000   0.2424
  -4.250  -0.5073   0.02241   0.01129   0.0032   1.0000   0.2980
  -4.000  -0.5006   0.02121   0.01083   0.0064   1.0000   0.3998
  -3.750  -0.4907   0.02078   0.01152   0.0112   1.0000   0.5637
  -3.500  -0.4790   0.02103   0.01187   0.0152   1.0000   0.6649
  -3.250  -0.4667   0.02127   0.01207   0.0189   1.0000   0.7183
  -3.000  -0.4517   0.02160   0.01238   0.0224   1.0000   0.7587
  -2.750  -0.4351   0.02194   0.01266   0.0256   1.0000   0.7921
  -2.500  -0.4157   0.02230   0.01294   0.0283   1.0000   0.8220
  -2.250  -0.3895   0.02282   0.01339   0.0301   1.0000   0.8524
  -2.000  -0.3559   0.02341   0.01389   0.0305   1.0000   0.8844
  -1.750  -0.3017   0.02407   0.01440   0.0268   1.0000   0.9107
  -1.500  -0.2565   0.02432   0.01451   0.0234   1.0000   0.9273
  -1.250  -0.2187   0.02439   0.01447   0.0208   1.0000   0.9398
  -1.000  -0.1737   0.02442   0.01441   0.0166   0.9971   0.9489
  -0.750  -0.1292   0.02442   0.01432   0.0123   0.9921   0.9565
  -0.500  -0.0855   0.02440   0.01424   0.0081   0.9868   0.9629
  -0.250  -0.0430   0.02442   0.01423   0.0041   0.9822   0.9702
   0.000   0.0000   0.02440   0.01420   0.0000   0.9761   0.9761
   0.250   0.0430   0.02441   0.01423  -0.0041   0.9702   0.9822
   0.500   0.0855   0.02440   0.01424  -0.0081   0.9629   0.9868
   0.750   0.1292   0.02442   0.01432  -0.0123   0.9565   0.9922
   1.000   0.1737   0.02442   0.01440  -0.0166   0.9489   0.9971
   1.250   0.2187   0.02439   0.01447  -0.0208   0.9398   1.0000
   1.500   0.2564   0.02432   0.01450  -0.0234   0.9273   1.0000
   1.750   0.3017   0.02407   0.01439  -0.0268   0.9107   1.0000
   2.000   0.3558   0.02341   0.01388  -0.0305   0.8845   1.0000
   2.250   0.3894   0.02282   0.01339  -0.0301   0.8524   1.0000
   2.500   0.4157   0.02230   0.01293  -0.0283   0.8220   1.0000
   2.750   0.4350   0.02193   0.01265  -0.0255   0.7922   1.0000
   3.000   0.4516   0.02160   0.01238  -0.0224   0.7587   1.0000
   3.250   0.4666   0.02126   0.01207  -0.0189   0.7184   1.0000
   3.500   0.4789   0.02102   0.01187  -0.0152   0.6650   1.0000
   3.750   0.4906   0.02078   0.01152  -0.0112   0.5640   1.0000
   4.000   0.5005   0.02121   0.01083  -0.0064   0.4000   1.0000
   4.250   0.5072   0.02241   0.01129  -0.0032   0.2981   1.0000
   4.500   0.5168   0.02350   0.01192  -0.0007   0.2425   1.0000
   4.750   0.5289   0.02445   0.01259   0.0016   0.2086   1.0000
   5.000   0.5429   0.02532   0.01331   0.0036   0.1855   1.0000
   5.250   0.5586   0.02620   0.01403   0.0055   0.1691   1.0000
   5.500   0.5767   0.02706   0.01483   0.0070   0.1559   1.0000
   5.750   0.5972   0.02793   0.01569   0.0082   0.1446   1.0000
   6.000   0.6194   0.02889   0.01658   0.0092   0.1360   1.0000
   6.250   0.6429   0.02984   0.01757   0.0100   0.1274   1.0000
   6.500   0.6675   0.03096   0.01868   0.0106   0.1206   1.0000
   6.750   0.6918   0.03210   0.01993   0.0112   0.1138   1.0000
   7.000   0.7157   0.03341   0.02119   0.0117   0.1083   1.0000
   7.250   0.7392   0.03485   0.02289   0.0124   0.1028   1.0000
   7.500   0.7613   0.03620   0.02424   0.0130   0.0980   1.0000
   7.750   0.7827   0.03800   0.02629   0.0138   0.0938   1.0000
   8.000   0.8024   0.03982   0.02839   0.0148   0.0894   1.0000
   8.250   0.8221   0.04142   0.03002   0.0155   0.0857   1.0000
   8.500   0.8387   0.04372   0.03263   0.0166   0.0828   1.0000
   8.750   0.8510   0.04631   0.03568   0.0180   0.0795   1.0000
   9.000   0.8642   0.04852   0.03811   0.0192   0.0766   1.0000
   9.250   0.8786   0.05061   0.04030   0.0202   0.0744   1.0000
   9.500   0.8859   0.05357   0.04353   0.0216   0.0727   1.0000
   9.750   0.8809   0.05741   0.04790   0.0238   0.0712   1.0000
  10.000   0.8726   0.06123   0.05213   0.0258   0.0698   1.0000
  10.250   0.8604   0.06511   0.05631   0.0276   0.0688   1.0000
  10.500   0.8415   0.06910   0.06054   0.0293   0.0683   1.0000
  10.750   0.8154   0.07386   0.06550   0.0300   0.0682   1.0000
  11.000   0.7830   0.08033   0.07215   0.0280   0.0686   1.0000
  11.250   0.7447   0.08945   0.08140   0.0226   0.0694   1.0000
  11.500   0.7117   0.10073   0.09272   0.0148   0.0702   1.0000
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