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

NACA 23012 12% (naca23012-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NACA 23012 12% (naca23012-il)
Reynolds number: 1,000,000
Max Cl/Cd: 96.79 at α=8.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca23012-il-1000000.txt
Download as CSV file: xf-naca23012-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 23012  12%                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.250  -1.0627   0.06220   0.05971  -0.0331   1.0000   0.0142
 -15.000  -1.0952   0.05313   0.05040  -0.0395   1.0000   0.0142
 -14.750  -1.1159   0.04706   0.04411  -0.0428   1.0000   0.0143
 -14.500  -1.1291   0.04270   0.03955  -0.0442   1.0000   0.0144
 -14.250  -1.1381   0.03932   0.03598  -0.0443   1.0000   0.0145
 -14.000  -1.1426   0.03672   0.03321  -0.0434   1.0000   0.0146
 -13.750  -1.1428   0.03474   0.03108  -0.0420   1.0000   0.0147
 -13.500  -1.1396   0.03320   0.02940  -0.0402   1.0000   0.0148
 -13.250  -1.1329   0.03211   0.02819  -0.0382   1.0000   0.0149
 -13.000  -1.1469   0.02890   0.02470  -0.0341   1.0000   0.0153
 -12.750  -1.1358   0.02770   0.02343  -0.0324   1.0000   0.0155
 -12.500  -1.1201   0.02691   0.02259  -0.0310   1.0000   0.0157
 -12.250  -1.1035   0.02614   0.02177  -0.0297   1.0000   0.0159
 -12.000  -1.0862   0.02534   0.02091  -0.0285   1.0000   0.0162
 -11.750  -1.0687   0.02450   0.01998  -0.0272   1.0000   0.0164
 -11.500  -1.0507   0.02364   0.01902  -0.0260   1.0000   0.0167
 -11.250  -1.0323   0.02278   0.01806  -0.0247   1.0000   0.0170
 -11.000  -1.0133   0.02195   0.01712  -0.0235   1.0000   0.0173
 -10.750  -0.9938   0.02119   0.01626  -0.0222   1.0000   0.0176
 -10.500  -0.9737   0.02056   0.01553  -0.0210   1.0000   0.0178
 -10.250  -0.9563   0.01948   0.01431  -0.0194   1.0000   0.0181
 -10.000  -0.9394   0.01845   0.01323  -0.0177   1.0000   0.0186
  -9.750  -0.9196   0.01797   0.01275  -0.0163   1.0000   0.0190
  -9.500  -0.8996   0.01754   0.01229  -0.0149   1.0000   0.0193
  -9.250  -0.8801   0.01706   0.01177  -0.0133   1.0000   0.0197
  -9.000  -0.8610   0.01657   0.01123  -0.0117   1.0000   0.0200
  -8.750  -0.8422   0.01608   0.01069  -0.0099   1.0000   0.0204
  -8.500  -0.8235   0.01563   0.01019  -0.0082   1.0000   0.0208
  -8.250  -0.8046   0.01523   0.00973  -0.0064   1.0000   0.0211
  -8.000  -0.7838   0.01492   0.00938  -0.0050   0.9999   0.0213
  -7.750  -0.7532   0.01385   0.00828  -0.0060   0.9983   0.0222
  -7.500  -0.7191   0.01344   0.00787  -0.0075   0.9966   0.0228
  -7.250  -0.6847   0.01303   0.00744  -0.0089   0.9951   0.0235
  -7.000  -0.6502   0.01261   0.00700  -0.0104   0.9935   0.0241
  -6.750  -0.6173   0.01223   0.00659  -0.0115   0.9907   0.0247
  -6.500  -0.5833   0.01178   0.00611  -0.0128   0.9881   0.0253
  -6.250  -0.5491   0.01120   0.00553  -0.0143   0.9859   0.0264
  -6.000  -0.5130   0.01088   0.00523  -0.0161   0.9840   0.0274
  -5.750  -0.4818   0.01058   0.00492  -0.0167   0.9789   0.0284
  -5.500  -0.4498   0.01031   0.00462  -0.0175   0.9736   0.0293
  -5.250  -0.4212   0.00985   0.00416  -0.0175   0.9663   0.0307
  -5.000  -0.3925   0.00960   0.00391  -0.0175   0.9576   0.0321
  -4.750  -0.3660   0.00940   0.00370  -0.0170   0.9458   0.0336
  -4.500  -0.3404   0.00914   0.00340  -0.0163   0.9310   0.0355
  -4.250  -0.3151   0.00894   0.00318  -0.0154   0.9115   0.0378
  -4.000  -0.2892   0.00883   0.00299  -0.0147   0.8910   0.0399
  -3.750  -0.2632   0.00862   0.00276  -0.0141   0.8717   0.0435
  -3.500  -0.2364   0.00853   0.00261  -0.0137   0.8511   0.0465
  -3.250  -0.2100   0.00838   0.00242  -0.0132   0.8298   0.0515
  -3.000  -0.1831   0.00832   0.00227  -0.0127   0.8075   0.0559
  -2.750  -0.1564   0.00821   0.00213  -0.0123   0.7831   0.0624
  -2.500  -0.1296   0.00814   0.00199  -0.0120   0.7577   0.0705
  -2.250  -0.1026   0.00805   0.00188  -0.0116   0.7340   0.0828
  -2.000  -0.0761   0.00792   0.00175  -0.0113   0.7080   0.1089
  -1.750  -0.0554   0.00692   0.00147  -0.0103   0.6828   0.3338
  -1.500  -0.0316   0.00644   0.00136  -0.0097   0.6569   0.4622
  -1.250  -0.0063   0.00619   0.00130  -0.0091   0.6327   0.5423
  -1.000   0.0194   0.00603   0.00127  -0.0086   0.6069   0.6065
  -0.750   0.0454   0.00595   0.00125  -0.0082   0.5798   0.6569
  -0.500   0.0716   0.00591   0.00125  -0.0077   0.5530   0.7008
  -0.250   0.0977   0.00587   0.00127  -0.0072   0.5289   0.7431
   0.000   0.1241   0.00587   0.00129  -0.0067   0.5035   0.7785
   0.250   0.1503   0.00591   0.00133  -0.0062   0.4776   0.8119
   0.500   0.1767   0.00597   0.00137  -0.0057   0.4514   0.8411
   0.750   0.2025   0.00603   0.00144  -0.0050   0.4281   0.8713
   1.000   0.2280   0.00612   0.00152  -0.0042   0.4047   0.8988
   1.250   0.2544   0.00627   0.00159  -0.0038   0.3804   0.9137
   1.500   0.2810   0.00642   0.00166  -0.0033   0.3574   0.9266
   1.750   0.3076   0.00657   0.00174  -0.0029   0.3367   0.9384
   2.000   0.3348   0.00674   0.00183  -0.0026   0.3174   0.9481
   2.250   0.3617   0.00691   0.00192  -0.0023   0.2995   0.9579
   2.500   0.3909   0.00709   0.00202  -0.0024   0.2833   0.9652
   2.750   0.4202   0.00724   0.00212  -0.0026   0.2705   0.9722
   3.000   0.4531   0.00742   0.00223  -0.0037   0.2588   0.9764
   3.250   0.4847   0.00761   0.00235  -0.0045   0.2478   0.9814
   3.500   0.5188   0.00775   0.00246  -0.0058   0.2396   0.9844
   3.750   0.5553   0.00794   0.00259  -0.0077   0.2312   0.9859
   4.000   0.5913   0.00808   0.00270  -0.0095   0.2241   0.9878
   4.250   0.6261   0.00828   0.00285  -0.0111   0.2166   0.9902
   4.500   0.6603   0.00840   0.00296  -0.0125   0.2117   0.9927
   4.750   0.6949   0.00857   0.00310  -0.0141   0.2052   0.9946
   5.000   0.7306   0.00873   0.00323  -0.0158   0.1994   0.9960
   5.250   0.7660   0.00886   0.00335  -0.0175   0.1943   0.9976
   5.500   0.8008   0.00905   0.00351  -0.0192   0.1879   0.9991
   5.750   0.8313   0.00918   0.00364  -0.0199   0.1835   1.0000
   6.000   0.8545   0.00930   0.00376  -0.0190   0.1792   1.0000
   6.250   0.8771   0.00948   0.00391  -0.0180   0.1736   1.0000
   6.500   0.9000   0.00963   0.00406  -0.0171   0.1692   1.0000
   6.750   0.9232   0.00977   0.00421  -0.0162   0.1649   1.0000
   7.000   0.9458   0.00997   0.00438  -0.0152   0.1595   1.0000
   7.250   0.9689   0.01015   0.00456  -0.0143   0.1550   1.0000
   7.500   0.9922   0.01031   0.00473  -0.0135   0.1499   1.0000
   7.750   1.0146   0.01058   0.00495  -0.0125   0.1431   1.0000
   8.000   1.0385   0.01073   0.00513  -0.0118   0.1392   1.0000
   8.250   1.0616   0.01097   0.00534  -0.0110   0.1336   1.0000
   8.500   1.0848   0.01121   0.00559  -0.0102   0.1282   1.0000
   8.750   1.1082   0.01145   0.00582  -0.0094   0.1223   1.0000
   9.000   1.1313   0.01174   0.00609  -0.0087   0.1152   1.0000
   9.250   1.1545   0.01206   0.00637  -0.0080   0.1079   1.0000
   9.500   1.1780   0.01236   0.00667  -0.0074   0.1020   1.0000
   9.750   1.2009   0.01274   0.00702  -0.0067   0.0949   1.0000
  10.000   1.2243   0.01307   0.00736  -0.0061   0.0888   1.0000
  10.250   1.2468   0.01350   0.00775  -0.0054   0.0817   1.0000
  10.500   1.2689   0.01396   0.00818  -0.0047   0.0747   1.0000
  10.750   1.2913   0.01438   0.00860  -0.0040   0.0687   1.0000
  11.000   1.3128   0.01489   0.00909  -0.0032   0.0626   1.0000
  11.250   1.3336   0.01544   0.00962  -0.0024   0.0565   1.0000
  11.500   1.3547   0.01594   0.01013  -0.0016   0.0515   1.0000
  11.750   1.3746   0.01653   0.01071  -0.0007   0.0465   1.0000
  12.250   1.4128   0.01777   0.01194   0.0014   0.0382   1.0000
  12.500   1.4305   0.01844   0.01263   0.0025   0.0348   1.0000
  12.750   1.4475   0.01913   0.01334   0.0038   0.0318   1.0000
  13.000   1.4636   0.01983   0.01407   0.0051   0.0294   1.0000
  13.250   1.4766   0.02058   0.01485   0.0069   0.0272   1.0000
  13.500   1.4875   0.02140   0.01571   0.0090   0.0254   1.0000
  13.750   1.4987   0.02222   0.01658   0.0109   0.0238   1.0000
  14.000   1.5058   0.02334   0.01775   0.0130   0.0223   1.0000
  14.250   1.5157   0.02434   0.01882   0.0146   0.0213   1.0000
  14.500   1.5239   0.02550   0.02004   0.0161   0.0202   1.0000
  14.750   1.5287   0.02699   0.02159   0.0176   0.0193   1.0000
  15.000   1.5304   0.02886   0.02354   0.0188   0.0184   1.0000
  15.250   1.5368   0.03048   0.02526   0.0195   0.0179   1.0000
  15.500   1.5404   0.03248   0.02735   0.0200   0.0173   1.0000
  15.750   1.5413   0.03490   0.02987   0.0201   0.0169   1.0000
  16.000   1.5390   0.03789   0.03295   0.0197   0.0164   1.0000
  16.250   1.5325   0.04160   0.03678   0.0187   0.0161   1.0000
  16.500   1.5202   0.04636   0.04167   0.0170   0.0157   1.0000
  16.750   1.5026   0.05212   0.04757   0.0146   0.0155   1.0000
  17.000   1.4857   0.05803   0.05363   0.0119   0.0154   1.0000
  17.250   1.4649   0.06460   0.06035   0.0090   0.0153   1.0000
  17.500   1.4378   0.07227   0.06818   0.0055   0.0153   1.0000
  17.750   1.4051   0.08091   0.07698   0.0017   0.0154   1.0000
  18.000   1.3702   0.09002   0.08625  -0.0024   0.0154   1.0000
<< Back to NACA 23012 12% (naca23012-il)

Polar data table (+)

Polar graphs


<< Back to NACA 23012 12% (naca23012-il)