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NACA 2410 (naca2410-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NACA 2410 (naca2410-il)
Reynolds number: 100,000
Max Cl/Cd: 51.76 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca2410-il-100000.txt
Download as CSV file: xf-naca2410-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 2410                                       
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4926   0.10044   0.09529  -0.0166   1.0000   0.1359
  -9.000  -0.5244   0.09690   0.09192  -0.0249   1.0000   0.1412
  -8.750  -0.5087   0.09219   0.08720  -0.0225   1.0000   0.1440
  -8.500  -0.4935   0.08934   0.08431  -0.0206   1.0000   0.1496
  -8.250  -0.5189   0.08540   0.08053  -0.0266   1.0000   0.1553
  -8.000  -0.5171   0.08102   0.07618  -0.0269   1.0000   0.1593
  -7.750  -0.5088   0.07839   0.07356  -0.0260   1.0000   0.1677
  -7.500  -0.5812   0.05456   0.04896  -0.0447   1.0000   0.0992
  -7.250  -0.5721   0.05033   0.04461  -0.0437   1.0000   0.0958
  -7.000  -0.5676   0.04563   0.03963  -0.0428   1.0000   0.0941
  -6.750  -0.5621   0.04058   0.03413  -0.0416   1.0000   0.0916
  -6.500  -0.5517   0.03648   0.02953  -0.0403   1.0000   0.0913
  -6.250  -0.5374   0.03360   0.02618  -0.0388   1.0000   0.0941
  -6.000  -0.5206   0.03084   0.02287  -0.0374   1.0000   0.0959
  -5.750  -0.5015   0.02888   0.02029  -0.0360   1.0000   0.0980
  -5.500  -0.4818   0.02675   0.01817  -0.0353   1.0000   0.1024
  -5.250  -0.4602   0.02529   0.01651  -0.0342   1.0000   0.1058
  -5.000  -0.4375   0.02387   0.01477  -0.0333   1.0000   0.1094
  -4.750  -0.4146   0.02256   0.01329  -0.0325   1.0000   0.1149
  -4.500  -0.3916   0.02158   0.01226  -0.0317   1.0000   0.1209
  -4.250  -0.3673   0.02064   0.01109  -0.0309   1.0000   0.1272
  -4.000  -0.3436   0.01960   0.01019  -0.0303   1.0000   0.1361
  -3.750  -0.3197   0.01882   0.00947  -0.0298   1.0000   0.1508
  -3.500  -0.2953   0.01802   0.00876  -0.0294   1.0000   0.1740
  -3.250  -0.2709   0.01722   0.00821  -0.0290   1.0000   0.2105
  -3.000  -0.2467   0.01657   0.00785  -0.0288   1.0000   0.2649
  -2.750  -0.2228   0.01598   0.00764  -0.0286   1.0000   0.3339
  -2.500  -0.1991   0.01536   0.00755  -0.0283   1.0000   0.4284
  -2.250  -0.1771   0.01470   0.00763  -0.0274   1.0000   0.5734
  -2.000  -0.1602   0.01420   0.00788  -0.0242   1.0000   0.7531
  -1.750  -0.1292   0.01404   0.00804  -0.0237   1.0000   1.0000
  -1.500  -0.1095   0.01428   0.00804  -0.0233   1.0000   1.0000
  -1.250  -0.0755   0.01461   0.00815  -0.0257   0.9961   1.0000
  -1.000  -0.0239   0.01498   0.00828  -0.0311   0.9866   1.0000
  -0.750   0.0262   0.01528   0.00841  -0.0361   0.9763   1.0000
  -0.500   0.0746   0.01551   0.00850  -0.0407   0.9651   1.0000
  -0.250   0.1214   0.01569   0.00857  -0.0448   0.9532   1.0000
   0.000   0.1682   0.01580   0.00860  -0.0488   0.9414   1.0000
   0.250   0.2227   0.01581   0.00855  -0.0541   0.9325   1.0000
   0.500   0.2669   0.01577   0.00848  -0.0573   0.9192   1.0000
   0.750   0.3095   0.01569   0.00839  -0.0600   0.9060   1.0000
   1.000   0.3504   0.01557   0.00826  -0.0621   0.8926   1.0000
   1.250   0.3889   0.01541   0.00810  -0.0637   0.8787   1.0000
   1.500   0.4245   0.01524   0.00794  -0.0645   0.8640   1.0000
   1.750   0.4574   0.01509   0.00779  -0.0648   0.8484   1.0000
   2.000   0.4880   0.01495   0.00767  -0.0645   0.8321   1.0000
   2.250   0.5173   0.01484   0.00754  -0.0639   0.8153   1.0000
   2.500   0.5455   0.01475   0.00744  -0.0631   0.7980   1.0000
   2.750   0.5715   0.01476   0.00745  -0.0620   0.7789   1.0000
   3.000   0.5966   0.01482   0.00750  -0.0608   0.7587   1.0000
   3.250   0.6225   0.01486   0.00751  -0.0597   0.7390   1.0000
   3.500   0.6487   0.01492   0.00754  -0.0586   0.7195   1.0000
   3.750   0.6726   0.01509   0.00771  -0.0573   0.6967   1.0000
   4.000   0.6980   0.01518   0.00774  -0.0560   0.6749   1.0000
   4.250   0.7215   0.01535   0.00791  -0.0546   0.6496   1.0000
   4.500   0.7457   0.01550   0.00802  -0.0532   0.6249   1.0000
   4.750   0.7696   0.01569   0.00817  -0.0519   0.5994   1.0000
   5.000   0.7922   0.01588   0.00834  -0.0504   0.5700   1.0000
   5.250   0.8137   0.01604   0.00840  -0.0486   0.5353   1.0000
   5.500   0.8342   0.01625   0.00855  -0.0468   0.4961   1.0000
   5.750   0.8551   0.01655   0.00877  -0.0451   0.4588   1.0000
   6.000   0.8752   0.01691   0.00911  -0.0435   0.4161   1.0000
   6.250   0.8931   0.01743   0.00947  -0.0415   0.3588   1.0000
   6.500   0.9062   0.01847   0.01005  -0.0391   0.2706   1.0000
   6.750   0.9145   0.02041   0.01126  -0.0362   0.1828   1.0000
   7.000   0.9267   0.02225   0.01267  -0.0339   0.1457   1.0000
   7.250   0.9444   0.02374   0.01407  -0.0322   0.1279   1.0000
   7.500   0.9643   0.02527   0.01545  -0.0309   0.1170   1.0000
   7.750   0.9862   0.02654   0.01672  -0.0299   0.1080   1.0000
   8.000   1.0105   0.02827   0.01845  -0.0293   0.1021   1.0000
   8.250   1.0349   0.02982   0.02016  -0.0286   0.0970   1.0000
   8.500   1.0609   0.03209   0.02226  -0.0287   0.0915   1.0000
   8.750   1.0823   0.03371   0.02425  -0.0274   0.0879   1.0000
   9.000   1.1038   0.03566   0.02646  -0.0264   0.0841   1.0000
   9.250   1.1247   0.03768   0.02851  -0.0258   0.0798   1.0000
   9.500   1.1418   0.04090   0.03203  -0.0246   0.0772   1.0000
   9.750   1.1528   0.04335   0.03505  -0.0223   0.0749   1.0000
  10.000   1.1622   0.04594   0.03805  -0.0202   0.0720   1.0000
  10.250   1.1719   0.04876   0.04116  -0.0183   0.0698   1.0000
  10.500   1.1830   0.05184   0.04442  -0.0169   0.0680   1.0000
  10.750   1.1890   0.05631   0.04903  -0.0157   0.0661   1.0000
  11.000   1.1804   0.06064   0.05376  -0.0129   0.0653   1.0000
  11.250   1.1669   0.06407   0.05760  -0.0097   0.0649   1.0000
  11.500   1.1497   0.06782   0.06167  -0.0067   0.0648   1.0000
  11.750   1.1301   0.07183   0.06591  -0.0042   0.0650   1.0000
  12.000   1.1111   0.07654   0.07080  -0.0029   0.0653   1.0000
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