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GRUMMAN K-2 AIRFOIL (k2-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GRUMMAN K-2 AIRFOIL (k2-il)
Reynolds number: 50,000
Max Cl/Cd: 21.75 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-k2-il-50000.txt
Download as CSV file: xf-k2-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GRUMMAN K-2 AIRFOIL                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.6912   0.07690   0.06937  -0.0257   1.0000   0.1793
  -7.000  -0.7225   0.06950   0.06174  -0.0277   1.0000   0.1601
  -6.750  -0.7390   0.06321   0.05504  -0.0282   1.0000   0.1460
  -6.500  -0.7477   0.05741   0.04852  -0.0282   1.0000   0.1340
  -6.250  -0.7365   0.05322   0.04414  -0.0274   1.0000   0.1299
  -6.000  -0.7265   0.04875   0.03910  -0.0269   1.0000   0.1248
  -5.750  -0.7113   0.04506   0.03472  -0.0264   1.0000   0.1222
  -5.500  -0.6920   0.04211   0.03150  -0.0258   1.0000   0.1235
  -5.250  -0.6708   0.03941   0.02852  -0.0251   1.0000   0.1251
  -5.000  -0.6478   0.03684   0.02562  -0.0244   1.0000   0.1261
  -4.750  -0.6237   0.03456   0.02306  -0.0234   1.0000   0.1281
  -4.500  -0.5991   0.03270   0.02086  -0.0225   1.0000   0.1334
  -4.250  -0.5751   0.03080   0.01889  -0.0212   1.0000   0.1397
  -4.000  -0.5508   0.02931   0.01737  -0.0195   1.0000   0.1477
  -3.750  -0.5276   0.02796   0.01613  -0.0175   1.0000   0.1602
  -3.500  -0.5050   0.02675   0.01501  -0.0151   1.0000   0.1772
  -3.250  -0.4848   0.02536   0.01390  -0.0129   1.0000   0.2068
  -3.000  -0.4694   0.02265   0.01234  -0.0113   1.0000   0.3056
  -2.750  -0.4886   0.02477   0.01687   0.0080   1.0000   0.7215
  -2.500  -0.3059   0.03169   0.02245   0.0038   1.0000   0.9247
  -2.250  -0.1887   0.02924   0.01935  -0.0136   1.0000   0.9763
  -2.000  -0.1092   0.02731   0.01708  -0.0256   1.0000   1.0000
  -1.750  -0.0979   0.02670   0.01639  -0.0242   1.0000   1.0000
  -1.500  -0.0864   0.02615   0.01579  -0.0226   1.0000   1.0000
  -1.250  -0.0749   0.02566   0.01525  -0.0210   1.0000   1.0000
  -1.000  -0.0632   0.02522   0.01478  -0.0193   1.0000   1.0000
  -0.750  -0.0516   0.02483   0.01435  -0.0175   1.0000   1.0000
  -0.500  -0.0401   0.02447   0.01398  -0.0156   1.0000   1.0000
  -0.250  -0.0286   0.02415   0.01366  -0.0136   1.0000   1.0000
   0.000  -0.0174   0.02386   0.01338  -0.0115   1.0000   1.0000
   0.250  -0.0063   0.02360   0.01313  -0.0094   1.0000   1.0000
   0.500   0.0046   0.02337   0.01293  -0.0072   1.0000   1.0000
   0.750   0.0152   0.02316   0.01276  -0.0049   1.0000   1.0000
   1.000   0.0255   0.02298   0.01262  -0.0026   1.0000   1.0000
   1.250   0.0355   0.02282   0.01252  -0.0002   1.0000   1.0000
   1.500   0.0452   0.02268   0.01245   0.0023   1.0000   1.0000
   1.750   0.0544   0.02256   0.01241   0.0048   1.0000   1.0000
   2.000   0.0632   0.02246   0.01239   0.0074   1.0000   1.0000
   2.250   0.0716   0.02238   0.01241   0.0100   1.0000   1.0000
   2.500   0.0794   0.02233   0.01246   0.0127   1.0000   1.0000
   2.750   0.0868   0.02229   0.01254   0.0154   1.0000   1.0000
   3.000   0.0936   0.02228   0.01265   0.0181   1.0000   1.0000
   3.250   0.0998   0.02230   0.01280   0.0209   1.0000   1.0000
   3.500   0.1055   0.02235   0.01300   0.0236   1.0000   1.0000
   3.750   0.1108   0.02245   0.01325   0.0261   1.0000   1.0000
   4.000   0.1174   0.02265   0.01362   0.0283   1.0000   1.0000
   4.250   0.1267   0.02299   0.01416   0.0295   1.0000   1.0000
   4.500   0.1858   0.02414   0.01573   0.0218   0.9817   1.0000
   4.750   0.5474   0.02517   0.01456  -0.0233   0.2764   1.0000
   5.000   0.5748   0.02684   0.01599  -0.0229   0.2209   1.0000
   5.250   0.5988   0.02870   0.01761  -0.0220   0.1807   1.0000
   5.500   0.6203   0.03057   0.01961  -0.0205   0.1556   1.0000
   5.750   0.6403   0.03250   0.02168  -0.0188   0.1400   1.0000
   6.000   0.6599   0.03464   0.02375  -0.0175   0.1292   1.0000
   6.250   0.6741   0.03672   0.02644  -0.0145   0.1236   1.0000
   6.500   0.6879   0.03866   0.02857  -0.0122   0.1177   1.0000
   6.750   0.7006   0.04128   0.03129  -0.0100   0.1138   1.0000
   7.000   0.7076   0.04385   0.03432  -0.0065   0.1132   1.0000
   7.250   0.7133   0.04664   0.03746  -0.0030   0.1134   1.0000
   7.500   0.7168   0.04953   0.04066   0.0004   0.1137   1.0000
   7.750   0.7196   0.05257   0.04395   0.0037   0.1142   1.0000
   8.000   0.6998   0.05622   0.04861   0.0093   0.1213   1.0000
   8.250   0.6986   0.06039   0.05308   0.0112   0.1249   1.0000
   8.500   0.7044   0.06468   0.05753   0.0120   0.1277   1.0000
   8.750   0.5745   0.09202   0.08604  -0.0224   0.3599   1.0000
   9.000   0.5810   0.09589   0.08988  -0.0228   0.3440   1.0000
   9.500   0.5845   0.10349   0.09741  -0.0248   0.3164   1.0000
   9.750   0.5856   0.10729   0.10118  -0.0261   0.3037   1.0000
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