Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

NACA 65(1)-412 (naca651412-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: NACA 65(1)-412 (naca651412-il)
Reynolds number: 1,000,000
Max Cl/Cd: 100.92 at α=2.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca651412-il-1000000-n5.txt
Download as CSV file: xf-naca651412-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 65(1)-412                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.250  -0.9366   0.05435   0.05211  -0.0728   1.0000   0.0059
 -15.000  -0.9672   0.04669   0.04424  -0.0777   1.0000   0.0059
 -14.750  -0.9875   0.04145   0.03880  -0.0800   1.0000   0.0059
 -14.500  -1.0004   0.03761   0.03479  -0.0809   1.0000   0.0059
 -14.250  -1.0082   0.03464   0.03165  -0.0809   1.0000   0.0060
 -14.000  -1.0107   0.03244   0.02932  -0.0802   1.0000   0.0060
 -13.750  -1.0174   0.03016   0.02689  -0.0788   1.0000   0.0060
 -13.500  -1.0240   0.02829   0.02489  -0.0764   1.0000   0.0062
 -13.250  -1.0300   0.02704   0.02354  -0.0729   1.0000   0.0063
 -13.000  -1.0208   0.02589   0.02230  -0.0716   0.9986   0.0064
 -12.750  -0.9994   0.02477   0.02108  -0.0723   0.9906   0.0066
 -12.500  -0.9733   0.02373   0.01995  -0.0738   0.9858   0.0068
 -12.250  -0.9464   0.02272   0.01883  -0.0753   0.9801   0.0070
 -11.750  -0.8875   0.02091   0.01680  -0.0788   0.9683   0.0076
 -11.500  -0.8583   0.01993   0.01569  -0.0804   0.9608   0.0078
 -11.250  -0.8310   0.01905   0.01467  -0.0815   0.9510   0.0081
 -11.000  -0.8068   0.01832   0.01381  -0.0817   0.9394   0.0083
 -10.750  -0.7855   0.01752   0.01287  -0.0814   0.9280   0.0085
 -10.500  -0.7641   0.01687   0.01210  -0.0808   0.9174   0.0088
 -10.250  -0.7412   0.01648   0.01163  -0.0804   0.9075   0.0091
 -10.000  -0.7181   0.01608   0.01116  -0.0800   0.8987   0.0093
  -9.500  -0.6715   0.01527   0.01019  -0.0792   0.8815   0.0099
  -9.250  -0.6483   0.01480   0.00962  -0.0788   0.8735   0.0102
  -9.000  -0.6243   0.01440   0.00912  -0.0785   0.8653   0.0106
  -8.750  -0.5999   0.01406   0.00869  -0.0782   0.8578   0.0110
  -8.500  -0.5750   0.01373   0.00828  -0.0779   0.8500   0.0112
  -8.250  -0.5521   0.01310   0.00756  -0.0775   0.8429   0.0117
  -8.000  -0.5271   0.01277   0.00718  -0.0773   0.8355   0.0121
  -7.750  -0.5019   0.01247   0.00681  -0.0771   0.8287   0.0124
  -7.500  -0.4762   0.01217   0.00647  -0.0770   0.8216   0.0129
  -7.000  -0.4247   0.01158   0.00576  -0.0768   0.8090   0.0138
  -6.750  -0.3986   0.01132   0.00543  -0.0767   0.8025   0.0143
  -6.500  -0.3724   0.01106   0.00510  -0.0766   0.7965   0.0146
  -6.250  -0.3466   0.01068   0.00466  -0.0765   0.7899   0.0150
  -6.000  -0.3209   0.01031   0.00423  -0.0764   0.7839   0.0157
  -5.750  -0.2939   0.01007   0.00397  -0.0764   0.7782   0.0163
  -5.500  -0.2670   0.00987   0.00374  -0.0765   0.7724   0.0170
  -5.250  -0.2400   0.00965   0.00348  -0.0765   0.7671   0.0176
  -5.000  -0.2127   0.00944   0.00322  -0.0766   0.7611   0.0182
  -4.750  -0.1856   0.00926   0.00299  -0.0767   0.7554   0.0188
  -4.500  -0.1580   0.00909   0.00278  -0.0768   0.7499   0.0192
  -4.250  -0.1306   0.00884   0.00250  -0.0769   0.7444   0.0205
  -4.000  -0.1031   0.00868   0.00232  -0.0770   0.7395   0.0220
  -3.750  -0.0751   0.00854   0.00216  -0.0772   0.7346   0.0234
  -3.500  -0.0472   0.00842   0.00201  -0.0774   0.7293   0.0247
  -3.250  -0.0194   0.00830   0.00186  -0.0775   0.7243   0.0263
  -3.000   0.0087   0.00815   0.00172  -0.0777   0.7194   0.0298
  -2.750   0.0368   0.00805   0.00161  -0.0779   0.7146   0.0328
  -2.500   0.0648   0.00794   0.00149  -0.0781   0.7100   0.0406
  -2.250   0.0929   0.00773   0.00139  -0.0784   0.7055   0.0701
  -2.000   0.1207   0.00741   0.00127  -0.0787   0.7006   0.1374
  -1.750   0.1482   0.00697   0.00113  -0.0791   0.6961   0.2435
  -1.500   0.1752   0.00605   0.00094  -0.0799   0.6920   0.4697
  -1.000   0.2316   0.00564   0.00096  -0.0805   0.6828   0.6215
  -0.750   0.2600   0.00562   0.00097  -0.0807   0.6787   0.6413
  -0.500   0.2888   0.00561   0.00098  -0.0810   0.6744   0.6543
  -0.250   0.3175   0.00562   0.00100  -0.0812   0.6699   0.6613
   0.000   0.3460   0.00566   0.00100  -0.0815   0.6657   0.6660
   0.250   0.3748   0.00567   0.00102  -0.0817   0.6617   0.6703
   0.500   0.4035   0.00568   0.00104  -0.0820   0.6575   0.6749
   0.750   0.4321   0.00571   0.00107  -0.0822   0.6532   0.6798
   1.000   0.4606   0.00576   0.00111  -0.0825   0.6492   0.6843
   1.250   0.4893   0.00577   0.00115  -0.0827   0.6441   0.6889
   1.500   0.5173   0.00582   0.00119  -0.0828   0.6362   0.6940
   1.750   0.5455   0.00588   0.00124  -0.0830   0.6256   0.6988
   2.000   0.5729   0.00596   0.00129  -0.0830   0.6094   0.7034
   2.250   0.6002   0.00605   0.00136  -0.0830   0.5932   0.7086
   2.500   0.6267   0.00621   0.00143  -0.0828   0.5649   0.7138
   2.750   0.6515   0.00649   0.00155  -0.0824   0.5191   0.7187
   3.000   0.6706   0.00727   0.00186  -0.0810   0.4097   0.7240
   3.250   0.6890   0.00818   0.00228  -0.0797   0.2983   0.7295
   3.500   0.7082   0.00900   0.00270  -0.0785   0.2020   0.7350
   3.750   0.7280   0.00976   0.00310  -0.0774   0.1192   0.7411
   4.000   0.7502   0.01030   0.00344  -0.0767   0.0701   0.7466
   4.250   0.7734   0.01072   0.00374  -0.0760   0.0401   0.7524
   4.500   0.7984   0.01099   0.00398  -0.0757   0.0312   0.7585
   4.750   0.8234   0.01125   0.00423  -0.0754   0.0262   0.7646
   5.000   0.8488   0.01146   0.00448  -0.0751   0.0242   0.7715
   5.250   0.8736   0.01171   0.00474  -0.0747   0.0215   0.7779
   5.500   0.8980   0.01198   0.00503  -0.0743   0.0192   0.7848
   6.000   0.9468   0.01250   0.00561  -0.0734   0.0163   0.7985
   6.250   0.9701   0.01284   0.00596  -0.0728   0.0147   0.8063
   6.500   0.9935   0.01312   0.00629  -0.0722   0.0140   0.8140
   7.000   1.0391   0.01375   0.00702  -0.0708   0.0127   0.8301
   7.250   1.0610   0.01411   0.00741  -0.0700   0.0122   0.8381
   7.500   1.0820   0.01449   0.00784  -0.0690   0.0117   0.8473
   7.750   1.1014   0.01496   0.00837  -0.0677   0.0111   0.8569
   8.000   1.1207   0.01541   0.00889  -0.0664   0.0108   0.8675
   8.250   1.1399   0.01579   0.00935  -0.0651   0.0106   0.8789
   8.500   1.1565   0.01620   0.00984  -0.0633   0.0104   0.8916
   8.750   1.1709   0.01663   0.01036  -0.0610   0.0102   0.9072
   9.000   1.1842   0.01709   0.01089  -0.0586   0.0101   0.9256
   9.250   1.1949   0.01752   0.01145  -0.0557   0.0099   0.9546
   9.500   1.2118   0.01808   0.01208  -0.0544   0.0097   1.0000
   9.750   1.2272   0.01872   0.01276  -0.0528   0.0096   1.0000
  10.000   1.2421   0.01940   0.01349  -0.0512   0.0094   1.0000
  10.250   1.2568   0.02011   0.01426  -0.0496   0.0093   1.0000
  10.500   1.2711   0.02086   0.01506  -0.0481   0.0091   1.0000
  10.750   1.2850   0.02165   0.01591  -0.0466   0.0090   1.0000
  11.000   1.2993   0.02243   0.01673  -0.0453   0.0088   1.0000
  11.250   1.3120   0.02335   0.01771  -0.0437   0.0087   1.0000
  11.500   1.3246   0.02430   0.01870  -0.0423   0.0084   1.0000
  11.750   1.3346   0.02547   0.01995  -0.0407   0.0083   1.0000
  12.000   1.3424   0.02688   0.02145  -0.0389   0.0081   1.0000
  12.250   1.3497   0.02838   0.02304  -0.0373   0.0080   1.0000
  12.500   1.3604   0.02960   0.02435  -0.0360   0.0080   1.0000
  12.750   1.3712   0.03083   0.02567  -0.0348   0.0079   1.0000
  13.000   1.3815   0.03212   0.02705  -0.0337   0.0078   1.0000
  13.250   1.3913   0.03347   0.02849  -0.0327   0.0077   1.0000
  13.500   1.4008   0.03489   0.03000  -0.0317   0.0076   1.0000
  13.750   1.4086   0.03648   0.03169  -0.0307   0.0075   1.0000
  14.000   1.4149   0.03829   0.03360  -0.0297   0.0074   1.0000
  14.250   1.4224   0.03998   0.03538  -0.0289   0.0072   1.0000
  14.500   1.4282   0.04188   0.03739  -0.0282   0.0071   1.0000
  14.750   1.4322   0.04402   0.03963  -0.0275   0.0070   1.0000
  15.000   1.4360   0.04623   0.04196  -0.0270   0.0069   1.0000
  15.250   1.4384   0.04868   0.04453  -0.0266   0.0069   1.0000
  15.500   1.4414   0.05113   0.04707  -0.0263   0.0067   1.0000
  15.750   1.4430   0.05382   0.04987  -0.0263   0.0067   1.0000
  16.000   1.4427   0.05685   0.05301  -0.0264   0.0066   1.0000
  16.250   1.4431   0.05989   0.05616  -0.0267   0.0065   1.0000
  16.500   1.4418   0.06326   0.05964  -0.0272   0.0064   1.0000
  16.750   1.4385   0.06705   0.06355  -0.0280   0.0064   1.0000
  17.000   1.4347   0.07106   0.06768  -0.0291   0.0063   1.0000
  17.250   1.4319   0.07507   0.07179  -0.0304   0.0062   1.0000
  17.500   1.4257   0.07976   0.07660  -0.0321   0.0062   1.0000
  17.750   1.4202   0.08454   0.08148  -0.0341   0.0061   1.0000
  18.000   1.4080   0.09069   0.08778  -0.0368   0.0061   1.0000
  18.250   1.3960   0.09712   0.09433  -0.0400   0.0060   1.0000
  18.500   1.3792   0.10474   0.10211  -0.0440   0.0060   1.0000
  18.750   1.3600   0.11326   0.11080  -0.0488   0.0060   1.0000
<< Back to NACA 65(1)-412 (naca651412-il)

Polar data table (+)

Polar graphs


<< Back to NACA 65(1)-412 (naca651412-il)