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NACA 65(2)-415 a=0.5 (naca652415a05-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 65(2)-415 a=0.5 (naca652415a05-il)
Reynolds number: 50,000
Max Cl/Cd: 18.93 at α=10.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca652415a05-il-50000-n5.txt
Download as CSV file: xf-naca652415a05-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 65(2)-415 a=0.5                            
  
 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  -0.3834   0.10667   0.09996  -0.0626   1.0000   0.0633
 -11.250  -0.3882   0.10389   0.09726  -0.0623   1.0000   0.0629
 -11.000  -0.4035   0.10165   0.09515  -0.0609   1.0000   0.0627
 -10.750  -0.4040   0.09643   0.08993  -0.0649   0.9897   0.0624
 -10.500  -0.4052   0.08917   0.08263  -0.0722   0.9805   0.0622
 -10.250  -0.4076   0.08249   0.07589  -0.0792   0.9721   0.0616
 -10.000  -0.4171   0.07597   0.06924  -0.0861   0.9625   0.0612
  -9.750  -0.4289   0.07083   0.06394  -0.0906   0.9515   0.0609
  -9.500  -0.4419   0.06697   0.05987  -0.0920   0.9394   0.0607
  -9.250  -0.4517   0.06351   0.05616  -0.0922   0.9286   0.0606
  -9.000  -0.4565   0.06014   0.05246  -0.0920   0.9198   0.0606
  -8.750  -0.4608   0.05725   0.04924  -0.0906   0.9104   0.0605
  -8.500  -0.4610   0.05450   0.04612  -0.0892   0.9023   0.0606
  -8.250  -0.4579   0.05189   0.04312  -0.0876   0.8946   0.0610
  -8.000  -0.4525   0.04956   0.04033  -0.0858   0.8878   0.0620
  -7.750  -0.4470   0.04759   0.03786  -0.0836   0.8805   0.0632
  -7.500  -0.4290   0.04524   0.03525  -0.0832   0.8760   0.0648
  -7.250  -0.4179   0.04368   0.03348  -0.0814   0.8692   0.0659
  -7.000  -0.3992   0.04195   0.03147  -0.0805   0.8639   0.0670
  -6.750  -0.3745   0.04025   0.02948  -0.0804   0.8602   0.0690
  -6.500  -0.3598   0.03920   0.02818  -0.0787   0.8542   0.0717
  -6.250  -0.3385   0.03805   0.02669  -0.0777   0.8493   0.0744
  -6.000  -0.3087   0.03663   0.02510  -0.0780   0.8460   0.0768
  -5.750  -0.2764   0.03542   0.02384  -0.0787   0.8433   0.0805
  -5.500  -0.2615   0.03497   0.02330  -0.0767   0.8371   0.0845
  -5.250  -0.2373   0.03432   0.02246  -0.0760   0.8329   0.0897
  -5.000  -0.2134   0.03352   0.02167  -0.0755   0.8296   0.0947
  -4.750  -0.1890   0.03289   0.02087  -0.0750   0.8268   0.1029
  -4.500  -0.1859   0.03271   0.02075  -0.0716   0.8201   0.1093
  -4.250  -0.1705   0.03219   0.02019  -0.0699   0.8157   0.1207
  -4.000  -0.1522   0.03137   0.01949  -0.0689   0.8123   0.1437
  -3.750  -0.1447   0.03045   0.01902  -0.0665   0.8079   0.2026
  -3.500  -0.1520   0.02921   0.01910  -0.0617   0.8023   0.4023
  -3.250  -0.1425   0.02929   0.01992  -0.0568   0.7986   0.6184
  -3.000  -0.1255   0.02991   0.02063  -0.0526   0.7956   0.7091
  -2.750  -0.1178   0.03116   0.02199  -0.0457   0.7917   0.7862
  -2.500  -0.0833   0.03287   0.02361  -0.0424   0.7889   0.8474
  -2.250  -0.0580   0.03319   0.02370  -0.0422   0.7852   0.8634
  -2.000  -0.0290   0.03333   0.02361  -0.0428   0.7820   0.8756
  -1.750  -0.0007   0.03338   0.02344  -0.0434   0.7794   0.8873
  -1.500   0.0378   0.03352   0.02334  -0.0460   0.7770   0.8954
  -1.250   0.0480   0.03402   0.02376  -0.0445   0.7715   0.9082
  -1.000   0.0723   0.03427   0.02387  -0.0450   0.7678   0.9198
  -0.750   0.1135   0.03447   0.02389  -0.0484   0.7652   0.9274
  -0.500   0.1511   0.03461   0.02389  -0.0510   0.7629   0.9364
  -0.250   0.1879   0.03496   0.02411  -0.0539   0.7601   0.9451
   0.000   0.2115   0.03560   0.02470  -0.0553   0.7550   0.9565
   0.250   0.2466   0.03598   0.02499  -0.0581   0.7515   0.9663
   0.500   0.2854   0.03627   0.02521  -0.0613   0.7488   0.9754
   0.750   0.3273   0.03652   0.02539  -0.0650   0.7466   0.9841
   1.000   0.3594   0.03711   0.02594  -0.0678   0.7427   0.9958
   1.250   0.3460   0.03780   0.02663  -0.0629   0.7360   1.0000
   1.500   0.3502   0.03807   0.02685  -0.0599   0.7319   1.0000
   1.750   0.3638   0.03831   0.02703  -0.0581   0.7288   1.0000
   2.000   0.3246   0.03909   0.02775  -0.0490   0.7200   1.0000
   2.250   0.3386   0.03950   0.02809  -0.0474   0.7161   1.0000
   2.500   0.3630   0.03988   0.02841  -0.0473   0.7134   1.0000
   2.750   0.3515   0.04086   0.02933  -0.0427   0.7055   1.0000
   3.000   0.3705   0.04145   0.02989  -0.0421   0.7011   1.0000
   3.250   0.3982   0.04192   0.03034  -0.0425   0.6980   1.0000
   3.750   0.4188   0.04361   0.03201  -0.0394   0.6856   1.0000
   4.000   0.4476   0.04412   0.03255  -0.0399   0.6822   1.0000
   4.250   0.4516   0.04519   0.03363  -0.0377   0.6743   1.0000
   4.500   0.4739   0.04586   0.03433  -0.0375   0.6691   1.0000
   4.750   0.5057   0.04629   0.03482  -0.0383   0.6656   1.0000
   5.000   0.5067   0.04753   0.03609  -0.0360   0.6561   1.0000
   5.250   0.5352   0.04802   0.03666  -0.0364   0.6515   1.0000
   5.500   0.5441   0.04910   0.03779  -0.0349   0.6429   1.0000
   5.750   0.5690   0.04966   0.03846  -0.0349   0.6370   1.0000
   6.000   0.5838   0.05057   0.03945  -0.0340   0.6289   1.0000
   6.250   0.6061   0.05119   0.04018  -0.0337   0.6217   1.0000
   6.500   0.6218   0.05202   0.04112  -0.0329   0.6130   1.0000
   6.750   0.6462   0.05249   0.04173  -0.0326   0.6056   1.0000
   7.000   0.6589   0.05341   0.04277  -0.0315   0.5952   1.0000
   7.250   0.6900   0.05346   0.04299  -0.0316   0.5888   1.0000
   7.500   0.7000   0.05442   0.04410  -0.0303   0.5766   1.0000
   7.750   0.7187   0.05494   0.04478  -0.0295   0.5663   1.0000
   8.000   0.7486   0.05472   0.04477  -0.0291   0.5579   1.0000
   8.250   0.7614   0.05537   0.04560  -0.0278   0.5446   1.0000
   8.500   0.7775   0.05575   0.04618  -0.0266   0.5313   1.0000
   8.750   0.7969   0.05563   0.04627  -0.0253   0.5168   1.0000
   9.000   0.8211   0.05461   0.04548  -0.0237   0.5001   1.0000
   9.250   0.8418   0.05324   0.04434  -0.0214   0.4772   1.0000
   9.500   0.8578   0.05186   0.04313  -0.0187   0.4466   1.0000
   9.750   0.8751   0.05050   0.04189  -0.0161   0.4060   1.0000
  10.000   0.9017   0.04839   0.03962  -0.0132   0.3360   1.0000
  10.250   0.9134   0.04826   0.03860  -0.0101   0.2369   1.0000
  10.500   0.9057   0.05112   0.04094  -0.0083   0.1796   1.0000
  10.750   0.8992   0.05422   0.04363  -0.0070   0.1421   1.0000
  11.000   0.8960   0.05717   0.04628  -0.0060   0.1196   1.0000
  11.250   0.8972   0.05979   0.04874  -0.0051   0.1041   1.0000
  11.500   0.9009   0.06220   0.05106  -0.0044   0.0929   1.0000
  11.750   0.9096   0.06415   0.05308  -0.0035   0.0843   1.0000
  12.000   0.9187   0.06606   0.05496  -0.0027   0.0778   1.0000
  12.250   0.9322   0.06760   0.05660  -0.0019   0.0719   1.0000
  12.500   0.9491   0.06882   0.05775  -0.0009   0.0676   1.0000
  12.750   0.9710   0.06982   0.05901   0.0001   0.0633   1.0000
  13.000   0.9916   0.07098   0.06026   0.0009   0.0592   1.0000
  13.250   1.0237   0.07168   0.06106   0.0019   0.0564   1.0000
  13.500   1.0468   0.07354   0.06327   0.0026   0.0543   1.0000
  13.750   1.0604   0.07607   0.06608   0.0030   0.0524   1.0000
  14.000   1.0691   0.07886   0.06909   0.0032   0.0507   1.0000
  14.250   1.0773   0.08162   0.07198   0.0033   0.0492   1.0000
  14.500   1.0863   0.08471   0.07516   0.0033   0.0480   1.0000
  14.750   1.0785   0.08910   0.07991   0.0029   0.0476   1.0000
  15.000   1.0677   0.09392   0.08505   0.0022   0.0474   1.0000
  15.250   1.0540   0.09919   0.09061   0.0009   0.0473   1.0000
  15.500   1.0374   0.10502   0.09672  -0.0009   0.0473   1.0000
  15.750   1.0188   0.11146   0.10341  -0.0035   0.0473   1.0000
  16.000   0.9973   0.11881   0.11098  -0.0070   0.0474   1.0000
  16.250   0.9751   0.12691   0.11926  -0.0113   0.0476   1.0000
  16.500   0.9536   0.13569   0.12818  -0.0164   0.0479   1.0000
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