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

NACA 64(1)-112 (naca641112-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA 64(1)-112 (naca641112-il)
Reynolds number: 200,000
Max Cl/Cd: 47.85 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca641112-il-200000-n5.txt
Download as CSV file: xf-naca641112-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64(1)-112                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.7259   0.08171   0.07796  -0.0243   1.0000   0.0187
 -12.000  -0.7616   0.07108   0.06717  -0.0319   1.0000   0.0185
 -11.750  -0.7885   0.06394   0.05985  -0.0363   1.0000   0.0183
 -11.500  -0.8128   0.05817   0.05390  -0.0389   1.0000   0.0182
 -11.250  -0.8338   0.05348   0.04899  -0.0398   1.0000   0.0182
 -11.000  -0.8526   0.04949   0.04476  -0.0393   1.0000   0.0184
 -10.750  -0.8677   0.04614   0.04115  -0.0376   1.0000   0.0184
 -10.500  -0.8779   0.04306   0.03778  -0.0352   1.0000   0.0186
 -10.250  -0.8803   0.03990   0.03425  -0.0334   1.0000   0.0189
 -10.000  -0.8771   0.03698   0.03095  -0.0317   1.0000   0.0193
  -9.750  -0.8686   0.03445   0.02804  -0.0303   1.0000   0.0197
  -9.500  -0.8565   0.03245   0.02568  -0.0290   1.0000   0.0203
  -9.250  -0.8406   0.03059   0.02372  -0.0282   1.0000   0.0209
  -9.000  -0.8227   0.02930   0.02233  -0.0275   1.0000   0.0215
  -8.750  -0.8040   0.02795   0.02084  -0.0268   1.0000   0.0221
  -8.500  -0.7845   0.02656   0.01928  -0.0260   1.0000   0.0227
  -8.250  -0.7643   0.02524   0.01780  -0.0252   1.0000   0.0233
  -8.000  -0.7440   0.02402   0.01645  -0.0244   1.0000   0.0240
  -7.750  -0.7239   0.02292   0.01523  -0.0234   1.0000   0.0247
  -7.500  -0.7047   0.02202   0.01423  -0.0223   1.0000   0.0256
  -7.250  -0.6795   0.02090   0.01302  -0.0225   0.9917   0.0268
  -7.000  -0.6482   0.01983   0.01195  -0.0241   0.9785   0.0283
  -6.750  -0.6165   0.01890   0.01098  -0.0255   0.9666   0.0298
  -6.500  -0.5858   0.01806   0.01006  -0.0267   0.9549   0.0314
  -6.250  -0.5565   0.01732   0.00921  -0.0275   0.9430   0.0332
  -6.000  -0.5301   0.01653   0.00837  -0.0277   0.9305   0.0355
  -5.500  -0.4798   0.01549   0.00718  -0.0274   0.9062   0.0427
  -5.250  -0.4562   0.01493   0.00659  -0.0268   0.8945   0.0473
  -5.000  -0.4320   0.01452   0.00611  -0.0263   0.8838   0.0542
  -4.750  -0.4085   0.01403   0.00563  -0.0256   0.8735   0.0658
  -4.500  -0.3854   0.01347   0.00516  -0.0250   0.8628   0.0924
  -4.250  -0.3637   0.01268   0.00468  -0.0244   0.8530   0.1613
  -4.000  -0.3442   0.01160   0.00414  -0.0237   0.8436   0.2906
  -3.750  -0.3245   0.01067   0.00391  -0.0228   0.8337   0.4535
  -3.500  -0.2994   0.01048   0.00380  -0.0222   0.8253   0.5096
  -3.250  -0.2735   0.01036   0.00373  -0.0217   0.8163   0.5453
  -3.000  -0.2477   0.01030   0.00372  -0.0211   0.8082   0.5854
  -2.750  -0.2224   0.01031   0.00381  -0.0203   0.7998   0.6237
  -2.500  -0.1958   0.01033   0.00380  -0.0198   0.7916   0.6463
  -2.250  -0.1687   0.01029   0.00372  -0.0196   0.7836   0.6548
  -2.000  -0.1409   0.01026   0.00362  -0.0195   0.7756   0.6633
  -1.750  -0.1134   0.01024   0.00354  -0.0193   0.7683   0.6709
  -1.500  -0.0854   0.01021   0.00345  -0.0194   0.7606   0.6778
  -1.250  -0.0578   0.01018   0.00339  -0.0192   0.7532   0.6838
  -1.000  -0.0297   0.01016   0.00331  -0.0193   0.7455   0.6911
  -0.750  -0.0020   0.01014   0.00327  -0.0192   0.7383   0.6968
  -0.500   0.0260   0.01014   0.00324  -0.0192   0.7312   0.7035
  -0.250   0.0539   0.01013   0.00322  -0.0192   0.7243   0.7102
   0.000   0.0816   0.01014   0.00322  -0.0191   0.7180   0.7173
   0.250   0.1096   0.01015   0.00323  -0.0191   0.7107   0.7246
   0.500   0.1373   0.01017   0.00325  -0.0190   0.7046   0.7313
   0.750   0.1654   0.01019   0.00329  -0.0191   0.6974   0.7389
   1.000   0.1929   0.01021   0.00334  -0.0189   0.6916   0.7458
   1.250   0.2210   0.01025   0.00341  -0.0190   0.6853   0.7542
   1.500   0.2484   0.01029   0.00350  -0.0188   0.6788   0.7615
   1.750   0.2762   0.01034   0.00357  -0.0188   0.6731   0.7699
   2.000   0.3036   0.01038   0.00371  -0.0187   0.6661   0.7772
   2.250   0.3311   0.01044   0.00377  -0.0185   0.6591   0.7856
   2.500   0.3582   0.01047   0.00391  -0.0183   0.6502   0.7938
   2.750   0.3854   0.01054   0.00402  -0.0181   0.6434   0.8025
   3.000   0.4118   0.01057   0.00410  -0.0176   0.6299   0.8114
   3.250   0.4370   0.01055   0.00408  -0.0168   0.6026   0.8199
   3.500   0.4617   0.01061   0.00406  -0.0160   0.5676   0.8296
   3.750   0.4859   0.01070   0.00413  -0.0151   0.5315   0.8386
   4.000   0.5104   0.01085   0.00423  -0.0144   0.4956   0.8484
   4.250   0.5330   0.01114   0.00436  -0.0133   0.4327   0.8590
   4.500   0.5491   0.01203   0.00470  -0.0116   0.3035   0.8701
   4.750   0.5644   0.01318   0.00530  -0.0100   0.1844   0.8823
   5.000   0.5819   0.01410   0.00586  -0.0087   0.1083   0.8954
   5.250   0.6020   0.01476   0.00637  -0.0075   0.0732   0.9096
   5.500   0.6235   0.01533   0.00689  -0.0066   0.0571   0.9249
   5.750   0.6479   0.01582   0.00741  -0.0063   0.0485   0.9418
   6.000   0.6759   0.01640   0.00804  -0.0068   0.0425   0.9602
   6.500   0.7300   0.01785   0.00957  -0.0080   0.0351   1.0000
   6.750   0.7516   0.01852   0.01031  -0.0074   0.0330   1.0000
   7.000   0.7729   0.01922   0.01104  -0.0068   0.0307   1.0000
   7.250   0.7933   0.02000   0.01182  -0.0061   0.0288   1.0000
   7.500   0.8116   0.02108   0.01292  -0.0052   0.0272   1.0000
   7.750   0.8324   0.02195   0.01387  -0.0044   0.0263   1.0000
   8.000   0.8529   0.02292   0.01492  -0.0036   0.0253   1.0000
   8.250   0.8735   0.02396   0.01604  -0.0029   0.0245   1.0000
   8.500   0.8942   0.02505   0.01722  -0.0022   0.0236   1.0000
   8.750   0.9148   0.02620   0.01844  -0.0016   0.0230   1.0000
   9.000   0.9351   0.02741   0.01972  -0.0010   0.0223   1.0000
   9.250   0.9545   0.02871   0.02107  -0.0004   0.0216   1.0000
   9.500   0.9736   0.03042   0.02291   0.0003   0.0209   1.0000
   9.750   0.9913   0.03186   0.02459   0.0012   0.0203   1.0000
  10.000   1.0074   0.03363   0.02664   0.0022   0.0198   1.0000
  10.250   1.0211   0.03563   0.02890   0.0034   0.0194   1.0000
  10.500   1.0315   0.03779   0.03133   0.0048   0.0190   1.0000
  10.750   1.0373   0.04002   0.03384   0.0066   0.0187   1.0000
  11.000   1.0382   0.04238   0.03646   0.0088   0.0184   1.0000
  11.250   1.0359   0.04483   0.03916   0.0109   0.0182   1.0000
  11.500   1.0320   0.04732   0.04186   0.0126   0.0179   1.0000
  11.750   1.0259   0.05005   0.04480   0.0138   0.0177   1.0000
  12.000   1.0192   0.05289   0.04783   0.0145   0.0175   1.0000
  12.250   1.0110   0.05600   0.05111   0.0147   0.0173   1.0000
  12.500   0.9977   0.06000   0.05531   0.0143   0.0171   1.0000
  12.750   0.9941   0.06281   0.05820   0.0135   0.0168   1.0000
  13.000   0.9751   0.06819   0.06380   0.0116   0.0168   1.0000
  13.250   0.9470   0.07555   0.07142   0.0079   0.0169   1.0000
  13.500   0.9175   0.08414   0.08024   0.0027   0.0169   1.0000
<< Back to NACA 64(1)-112 (naca641112-il)

Polar data table (+)

Polar graphs


<< Back to NACA 64(1)-112 (naca641112-il)