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GRUMMAN K-3 AIRFOIL (k3-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GRUMMAN K-3 AIRFOIL (k3-il)
Reynolds number: 50,000
Max Cl/Cd: 24.89 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-k3-il-50000.txt
Download as CSV file: xf-k3-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GRUMMAN K-3 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.7479   0.07687   0.06820  -0.0333   0.9999   0.2555
  -9.250  -0.8490   0.06220   0.05333  -0.0368   0.9999   0.2530
  -9.000  -0.8859   0.05276   0.04325  -0.0408   0.9999   0.2571
  -8.750  -0.8556   0.05440   0.04528  -0.0368   0.9999   0.2650
  -8.500  -0.8593   0.04823   0.03851  -0.0407   0.9999   0.2741
  -8.250  -0.8385   0.04830   0.03885  -0.0378   0.9999   0.2824
  -8.000  -0.8245   0.04458   0.03474  -0.0405   0.9999   0.2944
  -7.750  -0.8047   0.04476   0.03519  -0.0376   0.9999   0.3037
  -7.500  -0.7855   0.04276   0.03306  -0.0384   0.9999   0.3164
  -7.250  -0.7638   0.04107   0.03121  -0.0394   0.9999   0.3310
  -7.000  -0.7457   0.04162   0.03206  -0.0359   0.9999   0.3413
  -6.750  -0.7250   0.04091   0.03137  -0.0353   0.9999   0.3562
  -6.500  -0.7040   0.04050   0.03097  -0.0345   0.9999   0.3729
  -6.250  -0.6826   0.04025   0.03075  -0.0337   0.9999   0.3903
  -6.000  -0.6684   0.04210   0.03287  -0.0278   0.9999   0.3992
  -5.750  -0.6490   0.04235   0.03317  -0.0258   0.9999   0.4149
  -5.500  -0.6292   0.04256   0.03338  -0.0240   0.9999   0.4319
  -5.250  -0.6097   0.04296   0.03379  -0.0221   0.9999   0.4498
  -5.000  -0.5972   0.04505   0.03603  -0.0156   0.9999   0.4581
  -4.750  -0.5798   0.04570   0.03669  -0.0127   0.9999   0.4750
  -4.500  -0.5621   0.04621   0.03719  -0.0102   0.9999   0.4934
  -4.250  -0.5445   0.04666   0.03762  -0.0078   0.9999   0.5127
  -4.000  -0.5268   0.04703   0.03797  -0.0055   0.9999   0.5328
  -3.750  -0.5171   0.04855   0.03958   0.0013   0.9999   0.5419
  -3.500  -0.5015   0.04878   0.03979   0.0041   0.9999   0.5611
  -3.250  -0.4856   0.04884   0.03983   0.0065   0.9999   0.5815
  -3.000  -0.4690   0.04877   0.03973   0.0085   0.9999   0.6027
  -2.750  -0.4579   0.04919   0.04017   0.0133   0.9999   0.6177
  -2.500  -0.4450   0.04914   0.04012   0.0168   0.9999   0.6349
  -2.250  -0.4301   0.04883   0.03978   0.0189   0.9999   0.6543
  -2.000  -0.4140   0.04845   0.03938   0.0205   0.9999   0.6742
  -1.750  -0.3963   0.04809   0.03899   0.0213   0.9999   0.6939
  -1.500  -0.3884   0.04787   0.03880   0.0265   0.9999   0.7069
  -1.250  -0.3738   0.04739   0.03832   0.0283   0.9999   0.7234
  -1.000  -0.3563   0.04690   0.03781   0.0290   0.9999   0.7403
  -0.750  -0.3413   0.04652   0.03742   0.0307   0.9999   0.7558
  -0.500  -0.3289   0.04604   0.03696   0.0334   0.9999   0.7694
  -0.250  -0.3116   0.04560   0.03652   0.0340   0.9999   0.7838
   0.000  -0.2932   0.04529   0.03621   0.0342   0.9999   0.7980
   0.250  -0.2797   0.04482   0.03578   0.0362   0.9999   0.8093
   0.500  -0.2586   0.04459   0.03555   0.0354   0.9999   0.8213
   0.750  -0.2428   0.04427   0.03526   0.0365   0.9999   0.8317
   1.000  -0.2217   0.04414   0.03516   0.0356   0.9999   0.8414
   1.250  -0.2033   0.04401   0.03507   0.0357   0.9999   0.8505
   1.500  -0.1810   0.04408   0.03517   0.0343   0.9999   0.8588
   1.750  -0.1632   0.04406   0.03522   0.0342   0.9999   0.8668
   2.000  -0.1380   0.04446   0.03566   0.0319   0.9999   0.8743
   2.250  -0.1207   0.04458   0.03586   0.0318   0.9999   0.8814
   2.500  -0.0977   0.04511   0.03646   0.0299   0.9999   0.8887
   2.750  -0.0771   0.04562   0.03706   0.0285   0.9999   0.8952
   3.000  -0.0566   0.04629   0.03783   0.0270   0.9999   0.9022
   3.250   0.0255   0.04872   0.04039   0.0150   0.9575   0.9107
   3.500   0.1040   0.04930   0.04110   0.0061   0.9051   0.9189
   3.750   0.1655   0.04880   0.04075   0.0008   0.8645   0.9269
   4.000   0.2271   0.04792   0.04003  -0.0039   0.8291   0.9355
   4.250   0.2959   0.04624   0.03854  -0.0085   0.7976   0.9438
   4.500   0.3548   0.04403   0.03656  -0.0111   0.7642   0.9524
   4.750   0.4125   0.04115   0.03392  -0.0126   0.7274   0.9619
   5.000   0.4844   0.03645   0.02955  -0.0139   0.6824   0.9712
   5.250   0.6173   0.02833   0.02063  -0.0175   0.5024   0.9779
   5.500   0.6804   0.02993   0.02099  -0.0224   0.3929   0.9841
   5.750   0.7731   0.03205   0.02242  -0.0337   0.3315   0.9890
   6.000   0.8341   0.03372   0.02408  -0.0401   0.2981   0.9957
   6.250   0.8766   0.03522   0.02550  -0.0433   0.2755   1.0001
   6.500   0.8962   0.03647   0.02670  -0.0426   0.2611   1.0001
   6.750   0.9203   0.03795   0.02800  -0.0427   0.2460   1.0001
   7.000   0.9282   0.03905   0.02939  -0.0402   0.2342   1.0001
   7.250   0.9511   0.04091   0.03130  -0.0404   0.2200   1.0001
   7.500   0.9798   0.04306   0.03340  -0.0416   0.2056   1.0001
   7.750   1.0042   0.04512   0.03559  -0.0421   0.1925   1.0001
   8.000   1.0196   0.04777   0.03862  -0.0413   0.1819   1.0001
   8.250   1.0480   0.05062   0.04144  -0.0428   0.1713   1.0001
   8.500   1.0565   0.05346   0.04476  -0.0412   0.1635   1.0001
   8.750   1.0807   0.05673   0.04807  -0.0423   0.1559   1.0001
   9.000   1.0752   0.06034   0.05228  -0.0394   0.1519   1.0001
   9.250   1.0800   0.06387   0.05612  -0.0382   0.1476   1.0001
   9.500   1.1029   0.06765   0.05987  -0.0395   0.1424   1.0001
   9.750   1.0810   0.07198   0.06469  -0.0359   0.1417   1.0001
  10.000   1.0555   0.07647   0.06955  -0.0327   0.1415   1.0001
  10.250   1.0278   0.08164   0.07504  -0.0305   0.1417   1.0001
  10.500   0.9997   0.08747   0.08112  -0.0296   0.1423   1.0001
  10.750   0.9739   0.09399   0.08783  -0.0300   0.1430   1.0001
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