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NACA 0012-34 (naca001234-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NACA 0012-34 (naca001234-il)
Reynolds number: 100,000
Max Cl/Cd: 39.22 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca001234-il-100000.txt
Download as CSV file: xf-naca001234-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 0012-34                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.8178   0.04664   0.03950  -0.0092   1.0000   0.0736
  -7.500  -0.8078   0.04241   0.03480  -0.0054   1.0000   0.0627
  -7.250  -0.7982   0.03994   0.03162  -0.0009   1.0000   0.0568
  -7.000  -0.7850   0.03677   0.02815   0.0017   1.0000   0.0554
  -6.750  -0.7709   0.03465   0.02564   0.0045   1.0000   0.0563
  -6.500  -0.7547   0.03281   0.02337   0.0070   1.0000   0.0573
  -6.250  -0.7333   0.03053   0.02081   0.0087   1.0000   0.0574
  -6.000  -0.7097   0.02860   0.01863   0.0100   1.0000   0.0579
  -5.750  -0.6819   0.02603   0.01607   0.0103   1.0000   0.0599
  -5.500  -0.6621   0.02461   0.01472   0.0117   1.0000   0.0655
  -5.250  -0.6431   0.02356   0.01356   0.0136   1.0000   0.0706
  -5.000  -0.6303   0.02204   0.01216   0.0162   1.0000   0.0762
  -4.750  -0.6174   0.02100   0.01109   0.0190   1.0000   0.0856
  -4.500  -0.6055   0.01978   0.00998   0.0218   1.0000   0.1089
  -4.250  -0.6122   0.01615   0.00870   0.0274   1.0000   0.4504
  -4.000  -0.6065   0.01546   0.00925   0.0339   1.0000   0.7015
  -3.750  -0.5892   0.01601   0.00992   0.0381   1.0000   0.7784
  -3.500  -0.5686   0.01730   0.01121   0.0429   1.0000   0.8378
  -3.250  -0.5186   0.01963   0.01328   0.0432   1.0000   0.8805
  -3.000  -0.4790   0.02015   0.01355   0.0414   1.0000   0.8984
  -2.750  -0.4202   0.02076   0.01384   0.0357   1.0000   0.9103
  -2.500  -0.3589   0.02114   0.01397   0.0291   1.0000   0.9210
  -2.250  -0.3078   0.02131   0.01395   0.0240   1.0000   0.9329
  -2.000  -0.2603   0.02137   0.01383   0.0195   1.0000   0.9450
  -1.750  -0.2144   0.02137   0.01370   0.0151   1.0000   0.9571
  -1.500  -0.1655   0.02131   0.01353   0.0099   1.0000   0.9680
  -1.250  -0.1139   0.02115   0.01327   0.0041   1.0000   0.9774
  -1.000  -0.0645   0.02097   0.01303  -0.0015   1.0000   0.9874
  -0.750  -0.0129   0.02075   0.01276  -0.0077   1.0000   0.9969
  -0.500   0.0050   0.02062   0.01262  -0.0076   1.0000   1.0000
  -0.250   0.0026   0.02058   0.01257  -0.0038   1.0000   1.0000
   0.000   0.0000   0.02056   0.01256   0.0000   1.0000   1.0000
   0.250  -0.0026   0.02057   0.01257   0.0038   1.0000   1.0000
   0.500  -0.0050   0.02062   0.01262   0.0076   1.0000   1.0000
   0.750   0.0128   0.02075   0.01276   0.0077   0.9969   1.0000
   1.000   0.0644   0.02096   0.01302   0.0015   0.9874   1.0000
   1.250   0.1138   0.02115   0.01327  -0.0040   0.9774   1.0000
   1.500   0.1655   0.02130   0.01352  -0.0099   0.9680   1.0000
   1.750   0.2142   0.02136   0.01369  -0.0151   0.9571   1.0000
   2.000   0.2601   0.02136   0.01382  -0.0195   0.9450   1.0000
   2.250   0.3077   0.02130   0.01394  -0.0240   0.9329   1.0000
   2.500   0.3588   0.02114   0.01397  -0.0291   0.9210   1.0000
   2.750   0.4203   0.02075   0.01384  -0.0358   0.9104   1.0000
   3.000   0.4796   0.02014   0.01354  -0.0416   0.8986   1.0000
   3.250   0.5186   0.01962   0.01327  -0.0432   0.8804   1.0000
   3.500   0.5686   0.01730   0.01120  -0.0429   0.8378   1.0000
   3.750   0.5891   0.01601   0.00992  -0.0381   0.7786   1.0000
   4.000   0.6064   0.01546   0.00925  -0.0339   0.7019   1.0000
   4.250   0.6121   0.01614   0.00869  -0.0273   0.4504   1.0000
   4.500   0.6054   0.01978   0.00997  -0.0218   0.1090   1.0000
   4.750   0.6174   0.02099   0.01108  -0.0190   0.0858   1.0000
   5.000   0.6302   0.02204   0.01216  -0.0162   0.0763   1.0000
   5.250   0.6430   0.02355   0.01356  -0.0136   0.0707   1.0000
   5.500   0.6620   0.02460   0.01471  -0.0116   0.0655   1.0000
   5.750   0.6818   0.02602   0.01606  -0.0103   0.0600   1.0000
   6.000   0.7096   0.02860   0.01863  -0.0100   0.0579   1.0000
   6.250   0.7332   0.03053   0.02080  -0.0087   0.0574   1.0000
   6.500   0.7546   0.03280   0.02336  -0.0070   0.0573   1.0000
   6.750   0.7708   0.03464   0.02563  -0.0045   0.0563   1.0000
   7.000   0.7848   0.03676   0.02813  -0.0017   0.0554   1.0000
   7.250   0.7981   0.03993   0.03161   0.0009   0.0568   1.0000
   7.500   0.8078   0.04240   0.03479   0.0054   0.0627   1.0000
   7.750   0.8120   0.04974   0.04338   0.0122   0.1031   1.0000
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