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GRUMMAN K-3 AIRFOIL (k3-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GRUMMAN K-3 AIRFOIL (k3-il)
Reynolds number: 100,000
Max Cl/Cd: 30.1 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-k3-il-100000.txt
Download as CSV file: xf-k3-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.000  -0.7811   0.08871   0.08194  -0.0673   0.9999   0.1306
 -13.750  -0.8815   0.07448   0.06748  -0.0711   0.9999   0.1291
 -13.500  -0.9505   0.06681   0.05959  -0.0706   0.9999   0.1283
 -13.250  -1.0037   0.06198   0.05456  -0.0679   0.9999   0.1280
 -13.000  -1.0498   0.05876   0.05118  -0.0634   0.9999   0.1279
 -12.750  -1.0848   0.05552   0.04771  -0.0603   0.9999   0.1285
 -12.500  -1.1081   0.05222   0.04408  -0.0580   0.9999   0.1297
 -12.250  -1.1168   0.04935   0.04092  -0.0564   0.9999   0.1314
 -12.000  -1.0992   0.04843   0.04014  -0.0552   0.9999   0.1339
 -11.750  -1.0896   0.04703   0.03868  -0.0540   0.9999   0.1367
 -11.500  -1.0866   0.04480   0.03614  -0.0531   0.9999   0.1398
 -11.250  -1.0769   0.04283   0.03397  -0.0525   0.9999   0.1430
 -11.000  -1.0596   0.04191   0.03314  -0.0516   0.9999   0.1463
 -10.750  -1.0455   0.04046   0.03151  -0.0511   0.9999   0.1504
 -10.500  -1.0298   0.03887   0.02976  -0.0509   0.9999   0.1546
 -10.250  -1.0109   0.03804   0.02900  -0.0502   0.9999   0.1588
 -10.000  -0.9927   0.03667   0.02733  -0.0504   0.9999   0.1643
  -9.750  -0.9728   0.03576   0.02658  -0.0498   0.9999   0.1690
  -9.500  -0.9522   0.03479   0.02548  -0.0498   0.9999   0.1752
  -9.250  -0.9312   0.03377   0.02449  -0.0496   0.9999   0.1810
  -9.000  -0.9093   0.03299   0.02368  -0.0497   0.9999   0.1880
  -8.750  -0.8872   0.03207   0.02277  -0.0496   0.9999   0.1951
  -8.500  -0.8640   0.03135   0.02202  -0.0498   0.9999   0.2034
  -8.250  -0.8411   0.03056   0.02132  -0.0498   0.9999   0.2115
  -8.000  -0.8159   0.02989   0.02051  -0.0505   0.9999   0.2216
  -7.750  -0.7930   0.02924   0.02007  -0.0503   0.9999   0.2306
  -7.500  -0.7675   0.02857   0.01939  -0.0509   0.9999   0.2418
  -7.250  -0.7420   0.02804   0.01891  -0.0514   0.9999   0.2538
  -7.000  -0.7169   0.02749   0.01851  -0.0517   0.9999   0.2660
  -6.750  -0.6903   0.02696   0.01808  -0.0523   0.9999   0.2803
  -6.500  -0.6631   0.02649   0.01771  -0.0531   0.9999   0.2969
  -6.250  -0.6356   0.02608   0.01747  -0.0539   0.9999   0.3159
  -6.000  -0.6079   0.02576   0.01740  -0.0547   0.9999   0.3384
  -5.750  -0.5795   0.02558   0.01742  -0.0556   0.9999   0.3666
  -5.500  -0.5532   0.02565   0.01777  -0.0557   0.9999   0.3959
  -5.250  -0.5268   0.02592   0.01817  -0.0558   0.9999   0.4285
  -5.000  -0.5055   0.02651   0.01893  -0.0544   0.9999   0.4524
  -4.750  -0.4847   0.02719   0.01969  -0.0528   0.9999   0.4734
  -4.500  -0.4637   0.02789   0.02043  -0.0514   0.9999   0.4924
  -4.250  -0.4413   0.02857   0.02109  -0.0504   0.9999   0.5106
  -4.000  -0.4287   0.02952   0.02219  -0.0464   0.9999   0.5186
  -3.750  -0.4061   0.03014   0.02277  -0.0456   0.9999   0.5343
  -3.500  -0.3930   0.03104   0.02378  -0.0419   0.9999   0.5419
  -3.250  -0.3691   0.03154   0.02423  -0.0416   0.9999   0.5564
  -3.000  -0.3565   0.03237   0.02516  -0.0378   0.9999   0.5630
  -2.750  -0.3297   0.03277   0.02549  -0.0385   0.9999   0.5779
  -2.500  -0.3185   0.03352   0.02634  -0.0345   0.9999   0.5834
  -2.250  -0.3018   0.03414   0.02700  -0.0322   0.9999   0.5923
  -2.000  -0.2775   0.03448   0.02732  -0.0323   0.9999   0.6039
  -1.750  -0.2650   0.03511   0.02803  -0.0289   0.9999   0.6102
  -1.500  -0.2336   0.03543   0.02827  -0.0313   0.9999   0.6246
  -1.250  -0.2235   0.03593   0.02888  -0.0274   0.9999   0.6296
  -1.000  -0.2086   0.03646   0.02947  -0.0250   0.9999   0.6371
  -0.750  -0.1777   0.03677   0.02974  -0.0275   0.9999   0.6493
  -0.500  -0.1670   0.03723   0.03030  -0.0241   0.9999   0.6546
  -0.250  -0.1489   0.03773   0.03085  -0.0230   0.9999   0.6631
   0.000  -0.1226   0.03816   0.03129  -0.0243   0.9999   0.6735
   0.250  -0.0310   0.04028   0.03345  -0.0339   0.9621   0.6855
   0.500   0.0222   0.04068   0.03385  -0.0397   0.9473   0.6956
   0.750   0.0558   0.04095   0.03420  -0.0401   0.9341   0.7014
   1.000   0.1022   0.04117   0.03445  -0.0437   0.9214   0.7090
   1.250   0.1685   0.04117   0.03447  -0.0514   0.9089   0.7170
   1.500   0.2024   0.04032   0.03370  -0.0510   0.8870   0.7215
   1.750   0.2575   0.03916   0.03260  -0.0542   0.8664   0.7275
   2.000   0.3180   0.03813   0.03163  -0.0594   0.8528   0.7341
   2.250   0.3723   0.03701   0.03059  -0.0632   0.8412   0.7396
   2.500   0.4031   0.03616   0.02986  -0.0627   0.8264   0.7435
   2.750   0.4484   0.03490   0.02871  -0.0643   0.8143   0.7486
   3.000   0.5048   0.03313   0.02707  -0.0677   0.8024   0.7547
   3.250   0.5508   0.03155   0.02561  -0.0697   0.7851   0.7596
   3.500   0.5844   0.02981   0.02402  -0.0683   0.7670   0.7633
   3.750   0.6200   0.02782   0.02217  -0.0669   0.7443   0.7681
   4.000   0.6499   0.02633   0.02078  -0.0653   0.7008   0.7735
   4.250   0.7229   0.02406   0.01666  -0.0680   0.4079   0.7786
   4.500   0.7333   0.02537   0.01721  -0.0652   0.3226   0.7819
   4.750   0.7516   0.02628   0.01772  -0.0635   0.2845   0.7857
   5.000   0.7764   0.02704   0.01829  -0.0631   0.2589   0.7906
   5.250   0.8081   0.02787   0.01893  -0.0642   0.2388   0.7961
   5.500   0.8427   0.02873   0.01962  -0.0659   0.2219   0.8009
   5.750   0.8730   0.02956   0.02026  -0.0664   0.2076   0.8051
   6.000   0.8961   0.03008   0.02087  -0.0656   0.1951   0.8098
   6.250   0.9276   0.03098   0.02172  -0.0667   0.1821   0.8154
   6.500   0.9597   0.03195   0.02259  -0.0679   0.1699   0.8210
   6.750   0.9818   0.03262   0.02320  -0.0669   0.1594   0.8263
   7.000   1.0050   0.03345   0.02413  -0.0663   0.1486   0.8320
   7.250   1.0341   0.03455   0.02521  -0.0671   0.1373   0.8377
   7.500   1.0566   0.03548   0.02607  -0.0663   0.1280   0.8428
   7.750   1.0793   0.03639   0.02688  -0.0657   0.1191   0.8493
   8.000   1.0998   0.03744   0.02811  -0.0648   0.1103   0.8564
   8.250   1.1165   0.03849   0.02927  -0.0628   0.1032   0.8629
   8.500   1.1409   0.03970   0.03041  -0.0626   0.0971   0.8705
   8.750   1.1580   0.04080   0.03167  -0.0610   0.0915   0.8774
   9.000   1.1742   0.04212   0.03314  -0.0593   0.0869   0.8852
   9.250   1.1923   0.04321   0.03428  -0.0580   0.0829   0.8939
   9.500   1.2080   0.04494   0.03620  -0.0562   0.0799   0.9039
   9.750   1.2151   0.04653   0.03809  -0.0530   0.0772   0.9148
  10.000   1.2327   0.04755   0.03908  -0.0516   0.0749   0.9282
  10.250   1.2363   0.04941   0.04122  -0.0482   0.0730   0.9439
  10.500   1.2318   0.05146   0.04370  -0.0441   0.0712   0.9660
  10.750   1.2420   0.05330   0.04572  -0.0429   0.0692   1.0001
  11.000   1.2746   0.05526   0.04753  -0.0452   0.0671   1.0001
  11.250   1.2624   0.05915   0.05198  -0.0420   0.0665   1.0001
  11.500   1.2487   0.06337   0.05665  -0.0393   0.0660   1.0001
  11.750   1.2296   0.06796   0.06167  -0.0368   0.0658   1.0001
  12.000   1.2064   0.07299   0.06708  -0.0348   0.0657   1.0001
  12.250   1.1774   0.07870   0.07314  -0.0336   0.0659   1.0001
  12.500   1.1459   0.08506   0.07983  -0.0335   0.0662   1.0001
  12.750   1.1123   0.09224   0.08729  -0.0349   0.0665   1.0001
  13.000   1.0813   0.10002   0.09528  -0.0378   0.0669   1.0001
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