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NYU/GRUMMAN K-1 AIRFOIL (k1-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NYU/GRUMMAN K-1 AIRFOIL (k1-il)
Reynolds number: 50,000
Max Cl/Cd: 29.09 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-k1-il-50000-n5.txt
Download as CSV file: xf-k1-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NYU/GRUMMAN K-1 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.6666   0.08196   0.07389  -0.0506   1.0000   0.0601
 -11.000  -0.6904   0.07479   0.06663  -0.0556   1.0000   0.0597
 -10.750  -0.7135   0.06881   0.06052  -0.0594   1.0000   0.0594
 -10.500  -0.7347   0.06406   0.05561  -0.0615   1.0000   0.0592
 -10.250  -0.7518   0.06000   0.05135  -0.0627   1.0000   0.0592
 -10.000  -0.7627   0.05634   0.04742  -0.0628   1.0000   0.0594
  -9.750  -0.7690   0.05305   0.04380  -0.0620   1.0000   0.0597
  -9.500  -0.7715   0.05003   0.04043  -0.0609   1.0000   0.0602
  -9.250  -0.7620   0.04814   0.03851  -0.0596   1.0000   0.0614
  -9.000  -0.7543   0.04609   0.03629  -0.0583   1.0000   0.0630
  -8.750  -0.7463   0.04384   0.03374  -0.0570   1.0000   0.0646
  -8.500  -0.7354   0.04168   0.03128  -0.0556   1.0000   0.0663
  -8.250  -0.7208   0.04008   0.02962  -0.0542   1.0000   0.0680
  -8.000  -0.7055   0.03842   0.02779  -0.0528   1.0000   0.0698
  -7.750  -0.6895   0.03683   0.02598  -0.0513   1.0000   0.0724
  -7.500  -0.6735   0.03563   0.02479  -0.0499   1.0000   0.0755
  -7.250  -0.6566   0.03437   0.02337  -0.0483   1.0000   0.0793
  -7.000  -0.6399   0.03325   0.02224  -0.0468   1.0000   0.0832
  -6.750  -0.6230   0.03213   0.02107  -0.0454   1.0000   0.0882
  -6.500  -0.6059   0.03103   0.01990  -0.0441   1.0000   0.0951
  -6.250  -0.5885   0.02988   0.01875  -0.0431   1.0000   0.1038
  -6.000  -0.5706   0.02863   0.01757  -0.0425   1.0000   0.1162
  -5.750  -0.5515   0.02725   0.01633  -0.0423   1.0000   0.1363
  -5.500  -0.5304   0.02568   0.01505  -0.0429   1.0000   0.1735
  -5.250  -0.5072   0.02409   0.01395  -0.0441   1.0000   0.2409
  -5.000  -0.4838   0.02305   0.01340  -0.0447   1.0000   0.3233
  -4.750  -0.4620   0.02271   0.01341  -0.0439   1.0000   0.3948
  -4.500  -0.4415   0.02290   0.01379  -0.0422   1.0000   0.4563
  -4.250  -0.4208   0.02325   0.01415  -0.0404   1.0000   0.4989
  -4.000  -0.3992   0.02350   0.01432  -0.0389   1.0000   0.5269
  -3.750  -0.3784   0.02380   0.01451  -0.0371   1.0000   0.5496
  -3.500  -0.3580   0.02412   0.01476  -0.0352   1.0000   0.5714
  -3.250  -0.3376   0.02444   0.01499  -0.0334   1.0000   0.5917
  -3.000  -0.3166   0.02467   0.01513  -0.0319   1.0000   0.6105
  -2.750  -0.2939   0.02479   0.01511  -0.0310   1.0000   0.6280
  -2.500  -0.2741   0.02495   0.01521  -0.0292   1.0000   0.6413
  -2.250  -0.2524   0.02502   0.01521  -0.0281   1.0000   0.6549
  -2.000  -0.2279   0.02504   0.01511  -0.0280   1.0000   0.6699
  -1.750  -0.2076   0.02510   0.01513  -0.0265   1.0000   0.6816
  -1.500  -0.1844   0.02511   0.01507  -0.0261   1.0000   0.6941
  -1.250  -0.1596   0.02513   0.01500  -0.0261   1.0000   0.7072
  -1.000  -0.1386   0.02514   0.01500  -0.0251   1.0000   0.7173
  -0.750  -0.1052   0.02524   0.01502  -0.0269   0.9962   0.7298
  -0.500  -0.0740   0.02538   0.01514  -0.0278   0.9922   0.7398
  -0.250  -0.0420   0.02548   0.01520  -0.0294   0.9876   0.7505
   0.000  -0.0103   0.02562   0.01533  -0.0306   0.9829   0.7604
   0.250   0.0244   0.02581   0.01551  -0.0326   0.9785   0.7703
   0.500   0.0550   0.02594   0.01566  -0.0337   0.9725   0.7799
   0.750   0.0906   0.02615   0.01591  -0.0358   0.9670   0.7892
   1.000   0.1215   0.02632   0.01612  -0.0370   0.9601   0.7986
   1.250   0.1571   0.02654   0.01640  -0.0390   0.9533   0.8075
   1.500   0.1885   0.02672   0.01666  -0.0403   0.9449   0.8169
   1.750   0.2257   0.02694   0.01699  -0.0424   0.9372   0.8255
   2.000   0.2575   0.02706   0.01722  -0.0435   0.9253   0.8349
   2.250   0.2970   0.02699   0.01729  -0.0453   0.9081   0.8433
   2.500   0.3454   0.02650   0.01696  -0.0476   0.8832   0.8521
   2.750   0.3811   0.02583   0.01644  -0.0475   0.8563   0.8606
   3.000   0.4180   0.02522   0.01600  -0.0478   0.8345   0.8699
   3.250   0.4495   0.02455   0.01554  -0.0471   0.8132   0.8793
   3.500   0.4815   0.02379   0.01497  -0.0463   0.7903   0.8897
   3.750   0.5016   0.02329   0.01467  -0.0439   0.7608   0.9013
   4.000   0.5248   0.02269   0.01430  -0.0419   0.7255   0.9145
   4.250   0.5554   0.02182   0.01362  -0.0405   0.6764   0.9292
   4.500   0.5963   0.02080   0.01234  -0.0395   0.5485   0.9443
   4.750   0.6252   0.02149   0.01194  -0.0382   0.4001   0.9694
   5.000   0.6461   0.02266   0.01263  -0.0378   0.3319   1.0000
   5.250   0.6712   0.02381   0.01349  -0.0381   0.2925   1.0000
   5.500   0.6985   0.02489   0.01440  -0.0387   0.2647   1.0000
   5.750   0.7270   0.02594   0.01533  -0.0395   0.2408   1.0000
   6.000   0.7561   0.02694   0.01629  -0.0402   0.2175   1.0000
   6.250   0.7843   0.02795   0.01725  -0.0409   0.1948   1.0000
   6.500   0.8119   0.02903   0.01822  -0.0415   0.1737   1.0000
   6.750   0.8398   0.03013   0.01942  -0.0420   0.1526   1.0000
   7.000   0.8649   0.03127   0.02049  -0.0422   0.1334   1.0000
   7.250   0.8893   0.03242   0.02169  -0.0423   0.1153   1.0000
   7.500   0.9148   0.03380   0.02311  -0.0423   0.1012   1.0000
   7.750   0.9403   0.03527   0.02467  -0.0423   0.0904   1.0000
   8.000   0.9647   0.03678   0.02624  -0.0422   0.0825   1.0000
   8.250   0.9897   0.03864   0.02825  -0.0421   0.0766   1.0000
   8.500   1.0129   0.04059   0.03037  -0.0418   0.0718   1.0000
   8.750   1.0338   0.04230   0.03212  -0.0414   0.0678   1.0000
   9.000   1.0534   0.04478   0.03499  -0.0408   0.0641   1.0000
   9.250   1.0723   0.04702   0.03734  -0.0402   0.0621   1.0000
   9.500   1.0848   0.05047   0.04131  -0.0390   0.0601   1.0000
   9.750   1.0967   0.05310   0.04416  -0.0379   0.0581   1.0000
  10.000   1.1040   0.05604   0.04739  -0.0365   0.0564   1.0000
  10.250   1.1000   0.06008   0.05192  -0.0345   0.0550   1.0000
  10.500   1.0947   0.06375   0.05592  -0.0327   0.0539   1.0000
  10.750   1.0852   0.06732   0.05975  -0.0308   0.0533   1.0000
  11.000   1.0712   0.07136   0.06404  -0.0293   0.0529   1.0000
  11.250   1.0488   0.07640   0.06935  -0.0287   0.0528   1.0000
  11.500   1.0070   0.08443   0.07772  -0.0307   0.0535   1.0000
  11.750   0.9570   0.09597   0.08952  -0.0374   0.0547   1.0000
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