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GRUMMAN K-2 AIRFOIL (k2-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GRUMMAN K-2 AIRFOIL (k2-il)
Reynolds number: 200,000
Max Cl/Cd: 28.99 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-k2-il-200000.txt
Download as CSV file: xf-k2-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.4772   0.11361   0.10970  -0.0240   1.0000   0.0645
 -10.250  -0.5118   0.10494   0.10107  -0.0309   1.0000   0.0675
 -10.000  -0.5647   0.09247   0.08859  -0.0409   1.0000   0.0678
  -9.750  -0.5345   0.09248   0.08867  -0.0345   1.0000   0.0690
  -9.500  -0.5214   0.09139   0.08759  -0.0318   1.0000   0.0700
  -9.250  -0.5194   0.08830   0.08452  -0.0312   1.0000   0.0712
  -9.000  -0.5264   0.08356   0.07980  -0.0322   1.0000   0.0726
  -8.750  -0.5465   0.07616   0.07243  -0.0356   1.0000   0.0736
  -8.500  -0.5893   0.06668   0.06291  -0.0405   1.0000   0.0735
  -8.250  -0.6288   0.06076   0.05692  -0.0408   1.0000   0.0732
  -8.000  -0.7956   0.06448   0.05996  -0.0339   1.0000   0.0693
  -7.750  -0.7867   0.06176   0.05728  -0.0327   1.0000   0.0703
  -7.500  -0.7827   0.05923   0.05472  -0.0311   1.0000   0.0715
  -7.250  -0.7808   0.05659   0.05198  -0.0296   1.0000   0.0734
  -6.750  -0.7995   0.03800   0.03098  -0.0241   1.0000   0.0426
  -6.500  -0.7807   0.03550   0.02830  -0.0232   1.0000   0.0421
  -6.250  -0.7616   0.03277   0.02532  -0.0225   1.0000   0.0419
  -6.000  -0.7409   0.03027   0.02258  -0.0218   1.0000   0.0416
  -5.750  -0.7188   0.02798   0.02007  -0.0211   1.0000   0.0412
  -5.500  -0.6956   0.02606   0.01792  -0.0203   1.0000   0.0411
  -5.250  -0.6717   0.02448   0.01613  -0.0195   1.0000   0.0413
  -5.000  -0.6474   0.02322   0.01466  -0.0188   1.0000   0.0419
  -4.750  -0.6233   0.02188   0.01322  -0.0180   1.0000   0.0428
  -4.500  -0.5996   0.02067   0.01209  -0.0174   1.0000   0.0443
  -4.250  -0.5749   0.01997   0.01139  -0.0169   1.0000   0.0471
  -4.000  -0.5495   0.01940   0.01071  -0.0165   1.0000   0.0496
  -3.750  -0.5247   0.01815   0.00963  -0.0162   1.0000   0.0526
  -3.500  -0.4984   0.01746   0.00896  -0.0161   1.0000   0.0564
  -3.250  -0.4706   0.01661   0.00818  -0.0167   1.0000   0.0624
  -3.000  -0.4412   0.01585   0.00748  -0.0175   1.0000   0.0705
  -2.750  -0.4099   0.01508   0.00682  -0.0188   1.0000   0.0856
  -2.500  -0.3417   0.01126   0.00579  -0.0306   1.0000   0.5904
  -2.250  -0.3281   0.01174   0.00662  -0.0263   1.0000   0.6869
  -2.000  -0.3096   0.01228   0.00717  -0.0235   1.0000   0.7215
  -1.750  -0.2930   0.01290   0.00778  -0.0202   1.0000   0.7417
  -1.500  -0.2770   0.01352   0.00837  -0.0168   1.0000   0.7568
  -1.250  -0.2611   0.01413   0.00897  -0.0135   1.0000   0.7709
  -1.000  -0.2502   0.01492   0.00976  -0.0087   1.0000   0.7863
  -0.750  -0.2435   0.01578   0.01065  -0.0028   1.0000   0.8025
  -0.500  -0.2426   0.01641   0.01132   0.0045   1.0000   0.8137
  -0.250  -0.2289   0.01670   0.01161   0.0081   1.0000   0.8243
   0.000  -0.2063   0.01684   0.01172   0.0092   1.0000   0.8331
   0.250  -0.1894   0.01688   0.01176   0.0117   1.0000   0.8399
   0.500  -0.1682   0.01704   0.01191   0.0130   1.0000   0.8498
   0.750  -0.1568   0.01704   0.01193   0.0169   1.0000   0.8582
   1.000  -0.1316   0.01714   0.01203   0.0171   1.0000   0.8673
   1.250  -0.1162   0.01703   0.01194   0.0196   1.0000   0.8729
   1.500  -0.0807   0.01714   0.01207   0.0176   0.9969   0.8775
   1.750  -0.0214   0.01741   0.01235   0.0109   0.9861   0.8802
   2.000   0.0436   0.01733   0.01230   0.0038   0.9690   0.8816
   2.250   0.0904   0.01693   0.01195   0.0006   0.9544   0.8835
   2.500   0.1347   0.01654   0.01164  -0.0022   0.9436   0.8856
   2.750   0.1799   0.01602   0.01120  -0.0050   0.9310   0.8876
   3.000   0.2210   0.01542   0.01070  -0.0069   0.9157   0.8901
   3.250   0.2533   0.01486   0.01024  -0.0071   0.8935   0.8930
   3.500   0.2892   0.01418   0.00964  -0.0078   0.8599   0.8953
   3.750   0.3757   0.01447   0.00858  -0.0168   0.5220   0.8934
   4.000   0.3827   0.01541   0.00865  -0.0130   0.3459   0.8970
   4.250   0.3980   0.01606   0.00877  -0.0108   0.2440   0.9000
   4.500   0.4192   0.01653   0.00895  -0.0099   0.1909   0.9031
   4.750   0.4442   0.01693   0.00918  -0.0098   0.1570   0.9063
   5.000   0.4704   0.01732   0.00943  -0.0100   0.1300   0.9088
   5.250   0.4918   0.01757   0.00956  -0.0089   0.1007   0.9111
   5.500   0.5132   0.01818   0.00997  -0.0077   0.0614   0.9141
   5.750   0.5366   0.01885   0.01054  -0.0070   0.0481   0.9170
   6.000   0.5614   0.01968   0.01130  -0.0067   0.0425   0.9193
   6.250   0.5887   0.02048   0.01213  -0.0069   0.0389   0.9213
   6.500   0.6089   0.02122   0.01283  -0.0055   0.0363   0.9238
   6.750   0.6328   0.02183   0.01353  -0.0048   0.0337   0.9264
   7.000   0.6583   0.02300   0.01461  -0.0047   0.0320   0.9286
   7.250   0.6859   0.02427   0.01603  -0.0048   0.0311   0.9305
   7.500   0.7139   0.02570   0.01769  -0.0049   0.0304   0.9325
   7.750   0.7382   0.02723   0.01948  -0.0042   0.0301   0.9347
   8.000   0.7595   0.02900   0.02156  -0.0030   0.0300   0.9372
   8.250   0.7802   0.03128   0.02422  -0.0019   0.0302   0.9393
   8.500   0.7990   0.03398   0.02729  -0.0007   0.0308   0.9414
   8.750   0.8168   0.03701   0.03060   0.0001   0.0314   0.9434
   9.000   0.8152   0.04419   0.03884   0.0043   0.0377   0.9460
   9.250   0.7317   0.06754   0.06407   0.0110   0.0691   0.9505
   9.500   0.7353   0.07076   0.06737   0.0110   0.0680   0.9528
   9.750   0.7433   0.07376   0.07038   0.0111   0.0671   0.9547
  10.000   0.7661   0.07707   0.07356   0.0110   0.0662   0.9560
  10.250   0.7540   0.08270   0.07927   0.0110   0.0656   0.9584
  10.500   0.7065   0.08882   0.08568   0.0073   0.0653   0.9630
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