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NASA SC(2)-0706 AIRFOIL (sc20706-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NASA SC(2)-0706 AIRFOIL (sc20706-il)
Reynolds number: 100,000
Max Cl/Cd: 38.19 at α=1.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sc20706-il-100000.txt
Download as CSV file: xf-sc20706-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA SC(2)-0706 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5835   0.09867   0.09355  -0.0119   1.0000   0.0961
  -9.250  -0.5981   0.09551   0.09052  -0.0157   1.0000   0.0991
  -9.000  -0.6165   0.09049   0.08560  -0.0272   1.0000   0.1001
  -8.750  -0.5972   0.08766   0.08278  -0.0155   1.0000   0.1042
  -8.500  -0.5942   0.08413   0.07929  -0.0167   1.0000   0.1090
  -8.250  -0.6117   0.07703   0.07190  -0.0386   1.0000   0.1141
  -8.000  -0.5935   0.07377   0.06897  -0.0274   1.0000   0.1182
  -7.750  -0.5915   0.06767   0.06261  -0.0389   1.0000   0.1286
  -7.500  -0.5785   0.06490   0.06002  -0.0334   1.0000   0.1333
  -7.250  -0.5671   0.06011   0.05511  -0.0377   1.0000   0.1453
  -7.000  -0.5523   0.05612   0.05099  -0.0399   1.0000   0.1595
  -6.750  -0.5361   0.05277   0.04760  -0.0407   1.0000   0.1766
  -6.500  -0.5202   0.04986   0.04467  -0.0409   1.0000   0.2047
  -6.250  -0.4368   0.03394   0.02641  -0.0594   1.0000   0.0838
  -6.000  -0.3986   0.02899   0.02064  -0.0615   1.0000   0.0696
  -5.750  -0.3651   0.02565   0.01676  -0.0626   1.0000   0.0664
  -5.500  -0.3334   0.02318   0.01386  -0.0631   1.0000   0.0663
  -5.250  -0.3032   0.02168   0.01199  -0.0632   1.0000   0.0720
  -5.000  -0.2744   0.01964   0.00990  -0.0633   1.0000   0.0778
  -4.750  -0.2452   0.01829   0.00846  -0.0632   1.0000   0.0857
  -4.500  -0.2144   0.01680   0.00718  -0.0641   1.0000   0.1051
  -4.250  -0.1629   0.01296   0.00573  -0.0709   1.0000   0.5264
  -4.000  -0.1487   0.01330   0.00642  -0.0658   1.0000   0.6943
  -3.750  -0.1375   0.01378   0.00687  -0.0604   1.0000   0.7471
  -3.500  -0.1282   0.01415   0.00722  -0.0546   1.0000   0.7858
  -3.250  -0.1207   0.01432   0.00737  -0.0487   1.0000   0.8158
  -3.000  -0.1144   0.01431   0.00734  -0.0427   1.0000   0.8453
  -2.750  -0.1081   0.01409   0.00710  -0.0369   1.0000   0.8742
  -2.500  -0.0995   0.01368   0.00665  -0.0321   1.0000   0.9012
  -2.250  -0.0887   0.01312   0.00604  -0.0280   1.0000   0.9283
  -2.000  -0.0727   0.01247   0.00532  -0.0254   1.0000   0.9549
  -1.750  -0.0454   0.01198   0.00476  -0.0256   1.0000   0.9790
  -1.500  -0.0189   0.01170   0.00445  -0.0261   1.0000   1.0000
  -1.250   0.0164   0.01172   0.00440  -0.0287   1.0000   1.0000
  -1.000   0.0521   0.01177   0.00440  -0.0314   1.0000   1.0000
  -0.750   0.0879   0.01185   0.00446  -0.0339   1.0000   1.0000
  -0.500   0.1234   0.01195   0.00457  -0.0363   1.0000   1.0000
  -0.250   0.1586   0.01207   0.00473  -0.0387   1.0000   1.0000
   0.000   0.1934   0.01221   0.00494  -0.0409   1.0000   1.0000
   0.250   0.2277   0.01237   0.00519  -0.0429   1.0000   1.0000
   0.500   0.2616   0.01255   0.00548  -0.0448   1.0000   1.0000
   0.750   0.2949   0.01275   0.00583  -0.0466   1.0000   1.0000
   1.000   0.3277   0.01297   0.00626  -0.0483   1.0000   1.0000
   1.250   0.3600   0.01322   0.00672  -0.0498   1.0000   1.0000
   1.500   0.3917   0.01349   0.00726  -0.0511   1.0000   1.0000
   1.750   0.4659   0.01220   0.00666  -0.0581   0.8858   1.0000
   2.000   0.5360   0.01767   0.00800  -0.0639   0.0948   1.0000
   2.250   0.5660   0.01920   0.00947  -0.0643   0.0792   1.0000
   2.500   0.5981   0.02093   0.01123  -0.0648   0.0721   1.0000
   2.750   0.6312   0.02376   0.01411  -0.0656   0.0685   1.0000
   3.000   0.6633   0.02523   0.01603  -0.0656   0.0634   1.0000
   3.250   0.6950   0.02792   0.01915  -0.0655   0.0636   1.0000
   3.500   0.7248   0.03136   0.02300  -0.0653   0.0665   1.0000
   3.750   0.7553   0.03566   0.02807  -0.0640   0.0797   1.0000
   4.500   0.8411   0.05344   0.04850  -0.0619   0.1750   1.0000
   4.750   0.8580   0.05655   0.05163  -0.0611   0.1535   1.0000
   5.000   0.8730   0.06043   0.05563  -0.0607   0.1390   1.0000
   5.500   0.8929   0.06879   0.06452  -0.0612   0.1156   1.0000
   5.750   0.8161   0.06294   0.05921  -0.0503   0.1183   1.0000
   6.000   0.8241   0.06741   0.06372  -0.0496   0.1121   1.0000
   6.250   0.8299   0.07370   0.06994  -0.0488   0.1089   1.0000
   6.500   0.8037   0.07926   0.07579  -0.0518   0.1058   1.0000
   6.750   0.7863   0.08441   0.08097  -0.0532   0.1039   1.0000
   7.000   0.7704   0.08989   0.08646  -0.0560   0.1023   1.0000
   7.250   0.7651   0.09483   0.09139  -0.0574   0.0994   1.0000
   7.500   0.7872   0.09946   0.09599  -0.0518   0.0953   1.0000
   7.750   0.7662   0.10530   0.10182  -0.0572   0.0951   1.0000
   8.000   0.7456   0.11073   0.10720  -0.0625   0.0943   1.0000
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