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NYU/GRUMMAN K-1 AIRFOIL (k1-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NYU/GRUMMAN K-1 AIRFOIL (k1-il)
Reynolds number: 200,000
Max Cl/Cd: 49.61 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-k1-il-200000-n5.txt
Download as CSV file: xf-k1-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.750  -0.8281   0.08067   0.07621  -0.0409   1.0000   0.0234
 -13.500  -0.8692   0.06939   0.06461  -0.0494   1.0000   0.0232
 -13.250  -0.8901   0.06258   0.05756  -0.0543   1.0000   0.0232
 -13.000  -0.9034   0.05736   0.05214  -0.0578   1.0000   0.0233
 -12.750  -0.9122   0.05304   0.04762  -0.0604   1.0000   0.0234
 -12.500  -0.9176   0.04932   0.04371  -0.0625   1.0000   0.0235
 -12.250  -0.9204   0.04605   0.04025  -0.0641   1.0000   0.0237
 -12.000  -0.9209   0.04315   0.03715  -0.0653   1.0000   0.0239
 -11.750  -0.9197   0.04057   0.03438  -0.0660   1.0000   0.0242
 -11.500  -0.9177   0.03834   0.03195  -0.0663   1.0000   0.0245
 -11.250  -0.9126   0.03627   0.02966  -0.0665   1.0000   0.0249
 -11.000  -0.9091   0.03455   0.02769  -0.0653   1.0000   0.0254
 -10.750  -0.9065   0.03315   0.02609  -0.0631   1.0000   0.0257
 -10.500  -0.8991   0.03208   0.02499  -0.0611   1.0000   0.0260
 -10.250  -0.8888   0.03101   0.02386  -0.0596   0.9996   0.0264
 -10.000  -0.8631   0.02962   0.02236  -0.0609   0.9964   0.0269
  -9.750  -0.8364   0.02827   0.02088  -0.0622   0.9937   0.0274
  -9.500  -0.8095   0.02699   0.01947  -0.0634   0.9914   0.0279
  -9.250  -0.7839   0.02583   0.01817  -0.0642   0.9884   0.0285
  -9.000  -0.7568   0.02475   0.01699  -0.0652   0.9857   0.0293
  -8.750  -0.7284   0.02379   0.01603  -0.0666   0.9834   0.0301
  -8.500  -0.6983   0.02286   0.01505  -0.0682   0.9814   0.0310
  -8.250  -0.6672   0.02192   0.01402  -0.0699   0.9796   0.0319
  -8.000  -0.6404   0.02107   0.01309  -0.0706   0.9759   0.0328
  -7.750  -0.6118   0.02023   0.01226  -0.0719   0.9725   0.0337
  -7.500  -0.5815   0.01947   0.01145  -0.0733   0.9699   0.0350
  -7.250  -0.5505   0.01877   0.01067  -0.0748   0.9678   0.0367
  -6.750  -0.4925   0.01752   0.00935  -0.0768   0.9623   0.0410
  -6.500  -0.4639   0.01697   0.00878  -0.0776   0.9590   0.0447
  -6.250  -0.4335   0.01640   0.00818  -0.0788   0.9562   0.0501
  -6.000  -0.4023   0.01578   0.00758  -0.0802   0.9538   0.0584
  -5.750  -0.3706   0.01513   0.00706  -0.0817   0.9519   0.0762
  -5.500  -0.3441   0.01457   0.00665  -0.0821   0.9482   0.1102
  -5.250  -0.3160   0.01400   0.00626  -0.0829   0.9447   0.1473
  -5.000  -0.2864   0.01343   0.00591  -0.0840   0.9420   0.1971
  -4.750  -0.2558   0.01288   0.00560  -0.0852   0.9398   0.2545
  -4.500  -0.2248   0.01231   0.00535  -0.0865   0.9378   0.3274
  -4.250  -0.1948   0.01193   0.00524  -0.0874   0.9354   0.3914
  -4.000  -0.1679   0.01178   0.00521  -0.0874   0.9314   0.4313
  -3.750  -0.1392   0.01169   0.00518  -0.0876   0.9280   0.4641
  -3.500  -0.1098   0.01164   0.00518  -0.0879   0.9253   0.4878
  -3.250  -0.0797   0.01161   0.00516  -0.0883   0.9230   0.5061
  -3.000  -0.0495   0.01160   0.00513  -0.0886   0.9210   0.5219
  -2.750  -0.0216   0.01164   0.00521  -0.0886   0.9179   0.5386
  -2.500   0.0056   0.01170   0.00530  -0.0884   0.9141   0.5547
  -2.250   0.0341   0.01174   0.00535  -0.0884   0.9108   0.5682
  -2.000   0.0632   0.01178   0.00540  -0.0886   0.9080   0.5788
  -1.750   0.0929   0.01180   0.00541  -0.0888   0.9057   0.5882
  -1.500   0.1224   0.01184   0.00548  -0.0889   0.9036   0.5971
  -1.250   0.1504   0.01191   0.00554  -0.0890   0.9000   0.6066
  -1.000   0.1773   0.01200   0.00569  -0.0887   0.8959   0.6136
  -0.750   0.2059   0.01204   0.00574  -0.0887   0.8921   0.6219
  -0.500   0.2354   0.01195   0.00566  -0.0886   0.8875   0.6290
  -0.250   0.2617   0.01187   0.00562  -0.0878   0.8791   0.6350
   0.000   0.2894   0.01163   0.00538  -0.0869   0.8692   0.6418
   0.250   0.3156   0.01140   0.00513  -0.0859   0.8549   0.6483
   0.500   0.3417   0.01119   0.00495  -0.0848   0.8407   0.6532
   0.750   0.3693   0.01102   0.00478  -0.0841   0.8288   0.6588
   1.000   0.3966   0.01095   0.00472  -0.0836   0.8131   0.6651
   1.250   0.4241   0.01087   0.00467  -0.0831   0.7975   0.6703
   1.500   0.4512   0.01081   0.00466  -0.0825   0.7802   0.6748
   1.750   0.4787   0.01077   0.00462  -0.0820   0.7586   0.6801
   2.000   0.5064   0.01074   0.00454  -0.0815   0.7271   0.6859
   2.250   0.5325   0.01079   0.00437  -0.0804   0.6755   0.6906
   2.500   0.5548   0.01122   0.00437  -0.0788   0.5685   0.6948
   2.750   0.5728   0.01223   0.00469  -0.0770   0.4315   0.6996
   3.000   0.5940   0.01308   0.00507  -0.0761   0.3362   0.7048
   3.250   0.6177   0.01371   0.00542  -0.0755   0.2745   0.7098
   3.500   0.6418   0.01419   0.00576  -0.0750   0.2354   0.7138
   4.000   0.6918   0.01509   0.00643  -0.0741   0.1856   0.7233
   4.250   0.7176   0.01552   0.00676  -0.0739   0.1666   0.7286
   4.500   0.7425   0.01587   0.00708  -0.0734   0.1510   0.7325
   4.750   0.7679   0.01621   0.00740  -0.0730   0.1378   0.7368
   5.000   0.7935   0.01655   0.00773  -0.0727   0.1262   0.7418
   5.250   0.8195   0.01691   0.00807  -0.0725   0.1161   0.7471
   5.500   0.8445   0.01725   0.00844  -0.0720   0.1056   0.7512
   5.750   0.8697   0.01758   0.00880  -0.0715   0.0917   0.7555
   6.000   0.8944   0.01803   0.00920  -0.0711   0.0749   0.7605
   6.250   0.9186   0.01863   0.00968  -0.0706   0.0577   0.7658
   6.500   0.9415   0.01928   0.01030  -0.0699   0.0483   0.7701
   6.750   0.9644   0.01994   0.01099  -0.0691   0.0428   0.7748
   7.000   0.9876   0.02062   0.01169  -0.0684   0.0392   0.7799
   7.250   1.0108   0.02129   0.01241  -0.0678   0.0361   0.7853
   7.500   1.0328   0.02195   0.01315  -0.0669   0.0337   0.7902
   7.750   1.0546   0.02267   0.01391  -0.0661   0.0316   0.7958
   8.000   1.0768   0.02339   0.01473  -0.0653   0.0299   0.8015
   8.250   1.0975   0.02414   0.01557  -0.0643   0.0287   0.8069
   8.500   1.1175   0.02498   0.01648  -0.0632   0.0278   0.8134
   9.000   1.1568   0.02670   0.01844  -0.0609   0.0259   0.8269
   9.250   1.1752   0.02763   0.01944  -0.0597   0.0251   0.8347
   9.500   1.1923   0.02865   0.02056  -0.0582   0.0245   0.8436
  10.000   1.2242   0.03076   0.02302  -0.0549   0.0232   0.8710
  10.250   1.2343   0.03162   0.02408  -0.0520   0.0227   0.9166
  10.500   1.2484   0.03273   0.02526  -0.0505   0.0222   1.0000
  10.750   1.2619   0.03405   0.02662  -0.0490   0.0216   1.0000
  11.000   1.2742   0.03548   0.02828  -0.0473   0.0208   1.0000
  11.250   1.2849   0.03687   0.02982  -0.0456   0.0201   1.0000
  11.500   1.2944   0.03828   0.03133  -0.0439   0.0195   1.0000
  11.750   1.3028   0.03976   0.03286  -0.0422   0.0191   1.0000
  12.000   1.3088   0.04158   0.03480  -0.0404   0.0187   1.0000
  12.250   1.3111   0.04375   0.03725  -0.0384   0.0182   1.0000
  12.500   1.3120   0.04606   0.03979  -0.0366   0.0178   1.0000
  12.750   1.3112   0.04858   0.04251  -0.0350   0.0175   1.0000
  13.000   1.3087   0.05130   0.04543  -0.0336   0.0172   1.0000
  13.250   1.3045   0.05427   0.04859  -0.0326   0.0170   1.0000
  13.500   1.2987   0.05756   0.05206  -0.0320   0.0168   1.0000
  13.750   1.2911   0.06119   0.05587  -0.0318   0.0167   1.0000
  14.000   1.2819   0.06528   0.06013  -0.0322   0.0165   1.0000
  14.250   1.2704   0.06997   0.06500  -0.0334   0.0164   1.0000
  14.500   1.2561   0.07548   0.07070  -0.0355   0.0164   1.0000
  14.750   1.2394   0.08190   0.07732  -0.0386   0.0163   1.0000
  15.000   1.2169   0.09030   0.08597  -0.0438   0.0163   1.0000
  15.250   1.1830   0.10248   0.09847  -0.0522   0.0164   1.0000
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