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NYU/GRUMMAN K-1 AIRFOIL (k1-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NYU/GRUMMAN K-1 AIRFOIL (k1-il)
Reynolds number: 100,000
Max Cl/Cd: 39.81 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-k1-il-100000.txt
Download as CSV file: xf-k1-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.5522   0.10739   0.10210  -0.0291   1.0000   0.1718
 -10.000  -0.7189   0.06406   0.05848  -0.0616   1.0000   0.0846
  -9.750  -0.7351   0.05982   0.05414  -0.0617   1.0000   0.0826
  -9.500  -0.7854   0.05370   0.04736  -0.0603   1.0000   0.0781
  -9.250  -0.7846   0.05043   0.04394  -0.0589   1.0000   0.0771
  -9.000  -0.7856   0.04685   0.04005  -0.0575   1.0000   0.0759
  -8.750  -0.7830   0.04329   0.03607  -0.0564   1.0000   0.0751
  -8.500  -0.7741   0.04039   0.03278  -0.0554   1.0000   0.0754
  -8.250  -0.7612   0.03773   0.02974  -0.0546   1.0000   0.0761
  -8.000  -0.7451   0.03523   0.02685  -0.0539   1.0000   0.0764
  -7.750  -0.7264   0.03294   0.02423  -0.0531   1.0000   0.0768
  -7.500  -0.7060   0.03094   0.02190  -0.0524   1.0000   0.0776
  -7.250  -0.6843   0.02920   0.01981  -0.0517   1.0000   0.0787
  -7.000  -0.6627   0.02770   0.01839  -0.0508   1.0000   0.0807
  -6.750  -0.6405   0.02648   0.01713  -0.0501   1.0000   0.0837
  -6.500  -0.6181   0.02530   0.01591  -0.0494   1.0000   0.0877
  -6.250  -0.5951   0.02428   0.01484  -0.0487   1.0000   0.0929
  -6.000  -0.5722   0.02316   0.01386  -0.0482   1.0000   0.0986
  -5.750  -0.5481   0.02211   0.01291  -0.0479   1.0000   0.1081
  -5.500  -0.5226   0.02093   0.01188  -0.0481   1.0000   0.1246
  -5.250  -0.4928   0.01913   0.01060  -0.0499   1.0000   0.1751
  -5.000  -0.4572   0.01698   0.00962  -0.0537   1.0000   0.3510
  -4.750  -0.4308   0.01678   0.00975  -0.0538   1.0000   0.4373
  -4.500  -0.4073   0.01704   0.01012  -0.0527   1.0000   0.4899
  -4.250  -0.3852   0.01747   0.01058  -0.0513   1.0000   0.5273
  -4.000  -0.3658   0.01809   0.01124  -0.0489   1.0000   0.5551
  -3.750  -0.3468   0.01875   0.01189  -0.0465   1.0000   0.5796
  -3.500  -0.3286   0.01934   0.01250  -0.0439   1.0000   0.5981
  -3.250  -0.3090   0.01979   0.01292  -0.0418   1.0000   0.6139
  -3.000  -0.2868   0.02009   0.01314  -0.0406   1.0000   0.6298
  -2.750  -0.2666   0.02046   0.01347  -0.0389   1.0000   0.6445
  -2.500  -0.2499   0.02089   0.01392  -0.0361   1.0000   0.6569
  -2.250  -0.2299   0.02121   0.01422  -0.0344   1.0000   0.6726
  -2.000  -0.2070   0.02147   0.01441  -0.0336   1.0000   0.6890
  -1.750  -0.1911   0.02166   0.01463  -0.0309   1.0000   0.6981
  -1.500  -0.1665   0.02174   0.01465  -0.0308   1.0000   0.7115
  -1.250  -0.1471   0.02186   0.01477  -0.0292   1.0000   0.7224
  -1.000  -0.1245   0.02191   0.01481  -0.0287   1.0000   0.7339
  -0.750  -0.0992   0.02202   0.01487  -0.0289   1.0000   0.7467
  -0.500  -0.0807   0.02205   0.01494  -0.0273   1.0000   0.7561
  -0.250  -0.0546   0.02214   0.01500  -0.0278   1.0000   0.7680
   0.000  -0.0345   0.02219   0.01508  -0.0268   1.0000   0.7777
   0.250  -0.0095   0.02228   0.01518  -0.0271   1.0000   0.7882
   0.500   0.0133   0.02239   0.01531  -0.0269   1.0000   0.7982
   0.750   0.0369   0.02251   0.01546  -0.0269   1.0000   0.8077
   1.000   0.0790   0.02290   0.01588  -0.0305   0.9936   0.8181
   1.250   0.1240   0.02325   0.01628  -0.0343   0.9827   0.8273
   1.500   0.1888   0.02375   0.01683  -0.0416   0.9653   0.8375
   1.750   0.2421   0.02360   0.01678  -0.0454   0.9401   0.8457
   2.000   0.3041   0.02334   0.01660  -0.0507   0.9193   0.8547
   2.250   0.3404   0.02295   0.01633  -0.0514   0.9042   0.8627
   2.500   0.3759   0.02266   0.01615  -0.0524   0.8894   0.8717
   2.750   0.4073   0.02219   0.01581  -0.0521   0.8750   0.8801
   3.000   0.4512   0.02153   0.01530  -0.0538   0.8602   0.8888
   3.250   0.4908   0.02044   0.01438  -0.0536   0.8447   0.8969
   3.500   0.5265   0.01925   0.01335  -0.0528   0.8256   0.9061
   3.750   0.5529   0.01803   0.01229  -0.0502   0.8014   0.9156
   4.000   0.5830   0.01658   0.01099  -0.0478   0.7691   0.9253
   4.250   0.6075   0.01526   0.00970  -0.0443   0.6901   0.9369
   4.500   0.6268   0.01582   0.00854  -0.0397   0.4057   0.9472
   4.750   0.6476   0.01706   0.00912  -0.0388   0.3263   0.9617
   5.250   0.7090   0.01893   0.01043  -0.0411   0.2598   1.0000
   5.500   0.7395   0.01976   0.01120  -0.0425   0.2357   1.0000
   5.750   0.7696   0.02063   0.01196  -0.0438   0.2129   1.0000
   6.000   0.7988   0.02162   0.01274  -0.0450   0.1898   1.0000
   6.250   0.8272   0.02247   0.01362  -0.0460   0.1650   1.0000
   6.500   0.8547   0.02362   0.01468  -0.0467   0.1390   1.0000
   6.750   0.8824   0.02497   0.01590  -0.0473   0.1165   1.0000
   7.000   0.9112   0.02640   0.01724  -0.0480   0.1014   1.0000
   7.250   0.9403   0.02779   0.01865  -0.0486   0.0912   1.0000
   7.500   0.9705   0.02948   0.02038  -0.0492   0.0849   1.0000
   7.750   1.0003   0.03119   0.02203  -0.0499   0.0803   1.0000
   8.000   1.0275   0.03296   0.02403  -0.0500   0.0756   1.0000
   8.250   1.0529   0.03512   0.02645  -0.0500   0.0720   1.0000
   8.500   1.0786   0.03681   0.02817  -0.0501   0.0686   1.0000
   8.750   1.0978   0.03962   0.03148  -0.0492   0.0661   1.0000
   9.000   1.1151   0.04280   0.03509  -0.0481   0.0647   1.0000
   9.250   1.1298   0.04615   0.03882  -0.0469   0.0638   1.0000
   9.500   1.1381   0.05021   0.04335  -0.0451   0.0635   1.0000
   9.750   1.1282   0.05634   0.05023  -0.0420   0.0645   1.0000
  10.000   1.1142   0.06230   0.05672  -0.0392   0.0659   1.0000
  10.250   1.1025   0.06740   0.06213  -0.0371   0.0668   1.0000
  10.500   1.0905   0.07190   0.06684  -0.0352   0.0675   1.0000
  10.750   1.0788   0.07617   0.07124  -0.0336   0.0678   1.0000
  11.000   0.9354   0.09744   0.09322  -0.0427   0.0778   1.0000
  11.250   0.9343   0.10278   0.09855  -0.0439   0.0803   1.0000
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