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NASA SC(2)-0712 AIRFOIL (sc20712-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NASA SC(2)-0712 AIRFOIL (sc20712-il)
Reynolds number: 100,000
Max Cl/Cd: 32.01 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sc20712-il-100000.txt
Download as CSV file: xf-sc20712-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.5079   0.10256   0.09685  -0.0295   1.0000   0.1825
 -10.250  -0.7729   0.06411   0.05795  -0.0545   1.0000   0.0966
 -10.000  -0.7687   0.06010   0.05382  -0.0537   1.0000   0.0935
  -9.750  -0.7707   0.05558   0.04911  -0.0535   1.0000   0.0921
  -9.500  -0.7700   0.05105   0.04424  -0.0539   1.0000   0.0915
  -9.250  -0.7621   0.04693   0.03971  -0.0545   1.0000   0.0919
  -9.000  -0.7480   0.04309   0.03542  -0.0553   1.0000   0.0925
  -8.750  -0.7293   0.03960   0.03148  -0.0562   1.0000   0.0930
  -8.500  -0.7066   0.03690   0.02824  -0.0571   1.0000   0.0946
  -8.250  -0.6842   0.03405   0.02515  -0.0577   1.0000   0.0975
  -8.000  -0.6615   0.03232   0.02337  -0.0576   1.0000   0.1004
  -7.750  -0.6370   0.03066   0.02151  -0.0577   1.0000   0.1033
  -7.500  -0.6109   0.02928   0.01983  -0.0579   1.0000   0.1078
  -7.250  -0.5859   0.02759   0.01801  -0.0579   1.0000   0.1120
  -7.000  -0.5617   0.02640   0.01685  -0.0575   1.0000   0.1166
  -6.750  -0.5356   0.02548   0.01577  -0.0575   1.0000   0.1232
  -6.500  -0.5109   0.02429   0.01467  -0.0571   1.0000   0.1298
  -6.250  -0.4847   0.02349   0.01384  -0.0570   1.0000   0.1383
  -6.000  -0.4591   0.02258   0.01308  -0.0568   1.0000   0.1485
  -5.750  -0.4324   0.02177   0.01236  -0.0568   1.0000   0.1615
  -5.500  -0.4046   0.02099   0.01178  -0.0573   1.0000   0.1800
  -5.250  -0.3738   0.02009   0.01122  -0.0585   1.0000   0.2129
  -5.000  -0.3284   0.01794   0.01119  -0.0635   1.0000   0.4849
  -4.750  -0.3140   0.01913   0.01257  -0.0591   1.0000   0.5999
  -4.250  -0.2886   0.02130   0.01465  -0.0502   1.0000   0.6526
  -4.000  -0.2761   0.02223   0.01553  -0.0459   1.0000   0.6698
  -3.750  -0.2682   0.02314   0.01645  -0.0403   1.0000   0.6826
  -3.500  -0.2594   0.02394   0.01723  -0.0351   1.0000   0.6959
  -3.250  -0.2480   0.02459   0.01786  -0.0307   1.0000   0.7105
  -3.000  -0.2353   0.02513   0.01836  -0.0269   1.0000   0.7258
  -2.750  -0.2216   0.02557   0.01878  -0.0234   1.0000   0.7414
  -2.500  -0.2099   0.02596   0.01916  -0.0194   1.0000   0.7575
  -2.250  -0.2003   0.02626   0.01945  -0.0149   1.0000   0.7740
  -2.000  -0.1916   0.02641   0.01961  -0.0103   1.0000   0.7906
  -1.750  -0.1803   0.02642   0.01962  -0.0065   1.0000   0.8064
  -1.500  -0.1639   0.02639   0.01957  -0.0044   1.0000   0.8207
  -1.250  -0.1470   0.02625   0.01942  -0.0025   1.0000   0.8322
  -1.000  -0.1293   0.02604   0.01920  -0.0009   1.0000   0.8415
  -0.750  -0.1026   0.02608   0.01921  -0.0018   1.0000   0.8506
  -0.500  -0.0846   0.02586   0.01901  -0.0005   1.0000   0.8583
  -0.250  -0.0565   0.02597   0.01911  -0.0019   1.0000   0.8654
   0.000  -0.0354   0.02586   0.01902  -0.0015   1.0000   0.8706
   0.250  -0.0078   0.02601   0.01919  -0.0029   1.0000   0.8751
   0.500   0.0231   0.02632   0.01953  -0.0052   1.0000   0.8790
   0.750   0.0602   0.02652   0.01977  -0.0080   0.9944   0.8826
   1.000   0.1163   0.02693   0.02023  -0.0144   0.9818   0.8858
   1.250   0.1697   0.02703   0.02039  -0.0199   0.9641   0.8891
   1.500   0.2389   0.02682   0.02027  -0.0275   0.9423   0.8918
   1.750   0.2962   0.02613   0.01968  -0.0322   0.9212   0.8946
   2.000   0.3467   0.02516   0.01884  -0.0353   0.8999   0.8972
   2.250   0.4025   0.02390   0.01773  -0.0388   0.8802   0.8993
   2.500   0.4575   0.02232   0.01631  -0.0416   0.8592   0.9016
   2.750   0.5074   0.02055   0.01473  -0.0430   0.8313   0.9044
   3.000   0.5485   0.01902   0.01332  -0.0429   0.7822   0.9069
   3.250   0.5947   0.01858   0.01121  -0.0419   0.4285   0.9086
   3.500   0.6015   0.02053   0.01184  -0.0386   0.2529   0.9113
   3.750   0.6213   0.02167   0.01251  -0.0376   0.2029   0.9146
   4.000   0.6464   0.02264   0.01326  -0.0375   0.1757   0.9176
   4.250   0.6751   0.02374   0.01415  -0.0382   0.1574   0.9200
   4.500   0.7025   0.02456   0.01492  -0.0383   0.1437   0.9226
   4.750   0.7322   0.02563   0.01595  -0.0388   0.1333   0.9253
   5.000   0.7639   0.02698   0.01713  -0.0399   0.1243   0.9280
   5.250   0.7946   0.02802   0.01837  -0.0406   0.1171   0.9312
   5.500   0.8255   0.02930   0.01964  -0.0414   0.1113   0.9346
   5.750   0.8537   0.03090   0.02136  -0.0416   0.1064   0.9382
   6.000   0.8812   0.03222   0.02296  -0.0416   0.1019   0.9417
   6.250   0.9102   0.03385   0.02471  -0.0422   0.0984   0.9450
   6.500   0.9373   0.03651   0.02735  -0.0429   0.0949   0.9487
   6.750   0.9567   0.03794   0.02936  -0.0414   0.0924   0.9532
   7.000   0.9771   0.04047   0.03235  -0.0404   0.0910   0.9576
   7.250   0.9941   0.04323   0.03558  -0.0391   0.0898   0.9622
   7.500   1.0088   0.04603   0.03880  -0.0377   0.0882   0.9676
   7.750   1.0221   0.04904   0.04218  -0.0364   0.0869   0.9733
   8.000   1.0264   0.05367   0.04738  -0.0344   0.0881   0.9801
   8.250   1.0253   0.05909   0.05331  -0.0324   0.0907   0.9922
   8.500   1.0316   0.06445   0.05892  -0.0321   0.0931   1.0000
   8.750   0.8078   0.10087   0.09702  -0.0448   0.1796   1.0000
   9.000   0.8329   0.10317   0.09935  -0.0429   0.1751   1.0000
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