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NACA 4415 (naca4415-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 4415 (naca4415-il)
Reynolds number: 50,000
Max Cl/Cd: 27.4 at α=8.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca4415-il-50000-n5.txt
Download as CSV file: xf-naca4415-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 4415                                       
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3774   0.10454   0.09726  -0.0481   1.0000   0.0748
 -10.000  -0.3910   0.10060   0.09341  -0.0482   1.0000   0.0756
  -9.750  -0.4080   0.09637   0.08929  -0.0483   1.0000   0.0762
  -9.500  -0.4318   0.09148   0.08452  -0.0487   1.0000   0.0770
  -9.250  -0.4600   0.08627   0.07943  -0.0491   1.0000   0.0770
  -9.000  -0.4999   0.07993   0.07320  -0.0502   1.0000   0.0765
  -8.750  -0.5522   0.07381   0.06716  -0.0497   1.0000   0.0752
  -8.500  -0.5978   0.06782   0.06109  -0.0486   1.0000   0.0746
  -8.250  -0.6266   0.06227   0.05531  -0.0479   0.9987   0.0751
  -8.000  -0.6329   0.05470   0.04708  -0.0518   0.9890   0.0779
  -7.750  -0.6183   0.05101   0.04302  -0.0538   0.9816   0.0811
  -7.500  -0.5984   0.04882   0.04060  -0.0549   0.9739   0.0854
  -7.250  -0.5833   0.04536   0.03659  -0.0557   0.9661   0.0902
  -7.000  -0.5564   0.04412   0.03522  -0.0569   0.9593   0.0957
  -6.750  -0.5372   0.04194   0.03265  -0.0570   0.9513   0.1017
  -6.500  -0.5089   0.04063   0.03111  -0.0582   0.9447   0.1092
  -6.250  -0.4870   0.03948   0.02982  -0.0580   0.9364   0.1159
  -6.000  -0.4581   0.03802   0.02797  -0.0591   0.9298   0.1257
  -5.750  -0.4351   0.03745   0.02740  -0.0587   0.9212   0.1336
  -5.500  -0.4048   0.03653   0.02630  -0.0597   0.9145   0.1438
  -5.250  -0.3818   0.03567   0.02514  -0.0593   0.9058   0.1546
  -5.000  -0.3515   0.03510   0.02456  -0.0601   0.8987   0.1653
  -4.750  -0.3264   0.03449   0.02385  -0.0599   0.8904   0.1754
  -4.500  -0.2972   0.03381   0.02294  -0.0604   0.8828   0.1876
  -4.250  -0.2689   0.03331   0.02239  -0.0606   0.8753   0.1986
  -4.000  -0.2419   0.03278   0.02179  -0.0606   0.8669   0.2096
  -3.750  -0.2060   0.03218   0.02105  -0.0620   0.8612   0.2237
  -3.500  -0.1853   0.03186   0.02065  -0.0609   0.8508   0.2352
  -3.250  -0.1479   0.03131   0.02006  -0.0625   0.8454   0.2508
  -3.000  -0.1272   0.03106   0.01978  -0.0614   0.8349   0.2638
  -2.750  -0.0900   0.03056   0.01923  -0.0630   0.8291   0.2828
  -2.500  -0.0661   0.03035   0.01899  -0.0624   0.8193   0.3001
  -2.250  -0.0318   0.02989   0.01854  -0.0634   0.8127   0.3229
  -2.000  -0.0057   0.02964   0.01830  -0.0631   0.8041   0.3465
  -1.750   0.0241   0.02926   0.01799  -0.0633   0.7964   0.3746
  -1.500   0.0634   0.02858   0.01747  -0.0650   0.7921   0.4142
  -1.250   0.0778   0.02858   0.01762  -0.0627   0.7802   0.4491
  -1.000   0.1137   0.02786   0.01724  -0.0635   0.7754   0.5160
  -0.750   0.1283   0.02776   0.01750  -0.0609   0.7642   0.5923
  -0.500   0.1727   0.02704   0.01735  -0.0625   0.7594   0.7471
  -0.250   0.3247   0.02666   0.01707  -0.0851   0.7592   0.9868
   0.000   0.3448   0.02695   0.01714  -0.0841   0.7487   1.0000
   0.250   0.3768   0.02684   0.01681  -0.0847   0.7416   1.0000
   0.500   0.3903   0.02714   0.01694  -0.0824   0.7306   1.0000
   0.750   0.4236   0.02702   0.01664  -0.0831   0.7237   1.0000
   1.000   0.4364   0.02741   0.01690  -0.0806   0.7128   1.0000
   1.250   0.4697   0.02730   0.01664  -0.0812   0.7060   1.0000
   1.500   0.4826   0.02774   0.01698  -0.0787   0.6953   1.0000
   1.750   0.5148   0.02769   0.01680  -0.0792   0.6885   1.0000
   2.000   0.5283   0.02817   0.01719  -0.0768   0.6782   1.0000
   2.250   0.5595   0.02815   0.01708  -0.0770   0.6710   1.0000
   2.500   0.5740   0.02865   0.01750  -0.0749   0.6613   1.0000
   2.750   0.6032   0.02870   0.01747  -0.0748   0.6537   1.0000
   3.000   0.6199   0.02917   0.01788  -0.0729   0.6445   1.0000
   3.500   0.6664   0.02971   0.01832  -0.0711   0.6281   1.0000
   3.750   0.6877   0.03005   0.01863  -0.0699   0.6194   1.0000
   4.000   0.7140   0.03026   0.01880  -0.0695   0.6118   1.0000
   4.250   0.7282   0.03083   0.01934  -0.0673   0.6022   1.0000
   4.500   0.7629   0.03079   0.01927  -0.0680   0.5957   1.0000
   4.750   0.7674   0.03167   0.02016  -0.0644   0.5850   1.0000
   5.000   0.8110   0.03134   0.01979  -0.0664   0.5793   1.0000
   5.250   0.8055   0.03256   0.02104  -0.0615   0.5677   1.0000
   5.500   0.8534   0.03209   0.02055  -0.0640   0.5619   1.0000
   5.750   0.8427   0.03349   0.02199  -0.0584   0.5501   1.0000
   6.000   0.8882   0.03305   0.02153  -0.0605   0.5438   1.0000
   6.250   0.8788   0.03446   0.02299  -0.0552   0.5323   1.0000
   6.500   0.9159   0.03424   0.02278  -0.0561   0.5250   1.0000
   6.750   0.9140   0.03544   0.02404  -0.0519   0.5141   1.0000
   7.000   0.9392   0.03563   0.02424  -0.0512   0.5057   1.0000
   7.250   0.9495   0.03638   0.02504  -0.0487   0.4955   1.0000
   7.500   0.9606   0.03713   0.02583  -0.0464   0.4856   1.0000
   7.750   0.9879   0.03710   0.02582  -0.0458   0.4764   1.0000
   8.000   0.9851   0.03850   0.02729  -0.0421   0.4651   1.0000
   8.250   1.0298   0.03758   0.02636  -0.0432   0.4567   1.0000
   8.500   1.0145   0.03961   0.02849  -0.0384   0.4447   1.0000
   8.750   1.0299   0.04014   0.02906  -0.0366   0.4347   1.0000
   9.000   1.0485   0.04046   0.02943  -0.0352   0.4245   1.0000
   9.250   1.0431   0.04227   0.03133  -0.0319   0.4131   1.0000
   9.500   1.0767   0.04168   0.03072  -0.0317   0.4040   1.0000
   9.750   1.0673   0.04381   0.03297  -0.0284   0.3923   1.0000
  10.000   1.0710   0.04522   0.03446  -0.0262   0.3817   1.0000
  10.250   1.0986   0.04490   0.03414  -0.0254   0.3722   1.0000
  10.500   1.0849   0.04770   0.03707  -0.0226   0.3605   1.0000
  10.750   1.0986   0.04846   0.03786  -0.0212   0.3506   1.0000
  11.000   1.1098   0.04938   0.03883  -0.0197   0.3402   1.0000
  11.250   1.1006   0.05221   0.04177  -0.0177   0.3292   1.0000
  11.500   1.1259   0.05194   0.04149  -0.0167   0.3200   1.0000
  11.750   1.1158   0.05500   0.04467  -0.0151   0.3093   1.0000
  12.000   1.1165   0.05717   0.04691  -0.0138   0.2995   1.0000
  12.250   1.1360   0.05741   0.04717  -0.0127   0.2906   1.0000
  12.750   1.1489   0.06069   0.05052  -0.0105   0.2724   1.0000
  13.000   1.1212   0.06635   0.05638  -0.0101   0.2628   1.0000
  13.250   1.1400   0.06663   0.05665  -0.0090   0.2549   1.0000
  13.500   1.1211   0.07162   0.06177  -0.0089   0.2461   1.0000
  13.750   1.1323   0.07285   0.06305  -0.0081   0.2386   1.0000
  14.250   1.1219   0.07979   0.07014  -0.0080   0.2231   1.0000
  14.500   1.0898   0.08751   0.07802  -0.0096   0.2150   1.0000
  14.750   1.1097   0.08735   0.07786  -0.0085   0.2083   1.0000
  15.000   1.0516   0.09998   0.09067  -0.0127   0.1996   1.0000
  15.250   1.0943   0.09574   0.08640  -0.0099   0.1939   1.0000
  15.500   1.0144   0.11338   0.10419  -0.0169   0.1842   1.0000
  15.750   1.0935   0.10198   0.09275  -0.0107   0.1803   1.0000
  16.000   0.9867   0.12583   0.11675  -0.0214   0.1693   1.0000
  16.250   1.0486   0.11666   0.10763  -0.0160   0.1665   1.0000
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