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K3311 (original) (k3311-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: K3311 (original) (k3311-il)
Reynolds number: 1,000,000
Max Cl/Cd: 129.54 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-k3311-il-1000000.txt
Download as CSV file: xf-k3311-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: K3311  (original)                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4330   0.04308   0.04118  -0.0791   0.9807   0.0148
  -8.000  -0.4378   0.02726   0.02426  -0.0859   0.9699   0.0154
  -7.750  -0.4197   0.02323   0.01973  -0.0870   0.9597   0.0165
  -7.500  -0.3872   0.02323   0.01980  -0.0886   0.9535   0.0170
  -7.250  -0.3544   0.02397   0.02065  -0.0899   0.9447   0.0179
  -7.000  -0.3323   0.02154   0.01788  -0.0899   0.9313   0.0185
  -6.750  -0.3111   0.01942   0.01542  -0.0892   0.9175   0.0189
  -6.500  -0.2883   0.01811   0.01384  -0.0885   0.9043   0.0196
  -6.250  -0.2641   0.01790   0.01332  -0.0877   0.8915   0.0208
  -6.000  -0.2437   0.01561   0.01081  -0.0869   0.8790   0.0215
  -5.750  -0.2193   0.01507   0.01024  -0.0865   0.8667   0.0224
  -5.500  -0.1955   0.01399   0.00897  -0.0857   0.8539   0.0224
  -5.250  -0.1709   0.01324   0.00810  -0.0851   0.8407   0.0228
  -5.000  -0.1461   0.01250   0.00723  -0.0844   0.8272   0.0231
  -4.750  -0.1210   0.01198   0.00662  -0.0838   0.8130   0.0238
  -4.500  -0.0958   0.01155   0.00609  -0.0833   0.7985   0.0245
  -4.250  -0.0708   0.01101   0.00544  -0.0826   0.7847   0.0248
  -4.000  -0.0457   0.01057   0.00490  -0.0820   0.7717   0.0251
  -3.750  -0.0206   0.01016   0.00440  -0.0814   0.7597   0.0253
  -3.250   0.0303   0.00944   0.00354  -0.0803   0.7376   0.0257
  -3.000   0.0564   0.00922   0.00326  -0.0799   0.7271   0.0261
  -2.750   0.0827   0.00907   0.00306  -0.0795   0.7165   0.0265
  -2.500   0.1079   0.00870   0.00261  -0.0790   0.7060   0.0269
  -2.250   0.1332   0.00833   0.00215  -0.0784   0.6957   0.0278
  -2.000   0.1592   0.00816   0.00190  -0.0779   0.6852   0.0285
  -1.750   0.1854   0.00805   0.00172  -0.0776   0.6755   0.0293
  -1.500   0.2123   0.00794   0.00157  -0.0773   0.6673   0.0302
  -1.000   0.2664   0.00780   0.00135  -0.0768   0.6527   0.0327
  -0.750   0.2934   0.00777   0.00127  -0.0766   0.6457   0.0347
  -0.500   0.3203   0.00757   0.00119  -0.0764   0.6387   0.0734
  -0.250   0.3424   0.00677   0.00111  -0.0757   0.6309   0.3285
   0.000   0.3656   0.00622   0.00112  -0.0750   0.6223   0.5195
   0.250   0.3914   0.00610   0.00114  -0.0745   0.6130   0.5793
   0.500   0.4172   0.00599   0.00115  -0.0741   0.6025   0.6307
   0.750   0.4422   0.00586   0.00118  -0.0735   0.5909   0.6923
   1.000   0.4659   0.00574   0.00122  -0.0725   0.5775   0.7625
   1.250   0.4875   0.00556   0.00127  -0.0710   0.5647   0.8512
   1.500   0.5532   0.00547   0.00136  -0.0793   0.5504   0.9716
   1.750   0.6030   0.00560   0.00141  -0.0843   0.5394   1.0000
   2.000   0.6279   0.00569   0.00146  -0.0837   0.5305   1.0000
   2.250   0.6529   0.00578   0.00151  -0.0831   0.5228   1.0000
   2.500   0.6778   0.00588   0.00157  -0.0824   0.5143   1.0000
   2.750   0.7030   0.00598   0.00164  -0.0819   0.5051   1.0000
   3.000   0.7278   0.00610   0.00172  -0.0812   0.4957   1.0000
   3.250   0.7533   0.00619   0.00179  -0.0807   0.4875   1.0000
   3.500   0.7783   0.00631   0.00188  -0.0802   0.4784   1.0000
   4.000   0.8286   0.00655   0.00207  -0.0791   0.4584   1.0000
   4.250   0.8536   0.00668   0.00217  -0.0785   0.4483   1.0000
   4.500   0.8784   0.00682   0.00228  -0.0779   0.4361   1.0000
   5.000   0.9275   0.00716   0.00253  -0.0766   0.4018   1.0000
   5.250   0.9508   0.00741   0.00269  -0.0758   0.3791   1.0000
   5.500   0.9737   0.00770   0.00287  -0.0749   0.3531   1.0000
   5.750   0.9956   0.00805   0.00311  -0.0739   0.3247   1.0000
   6.000   1.0171   0.00845   0.00337  -0.0728   0.2946   1.0000
   6.250   1.0388   0.00884   0.00363  -0.0718   0.2657   1.0000
   6.500   1.0588   0.00935   0.00395  -0.0705   0.2287   1.0000
   6.750   1.0783   0.00989   0.00433  -0.0692   0.1946   1.0000
   7.000   1.0957   0.01057   0.00477  -0.0675   0.1510   1.0000
   7.250   1.1113   0.01137   0.00532  -0.0655   0.1071   1.0000
   7.500   1.1282   0.01206   0.00584  -0.0638   0.0766   1.0000
   7.750   1.1376   0.01325   0.00669  -0.0608   0.0270   1.0000
   8.000   1.1547   0.01388   0.00729  -0.0590   0.0186   1.0000
   8.250   1.1747   0.01429   0.00773  -0.0578   0.0168   1.0000
   8.500   1.1921   0.01484   0.00830  -0.0561   0.0148   1.0000
   8.750   1.2094   0.01538   0.00889  -0.0544   0.0139   1.0000
   9.000   1.2273   0.01584   0.00940  -0.0528   0.0131   1.0000
   9.250   1.2427   0.01633   0.00993  -0.0508   0.0125   1.0000
   9.500   1.2555   0.01687   0.01052  -0.0483   0.0119   1.0000
   9.750   1.2652   0.01759   0.01128  -0.0454   0.0112   1.0000
  10.000   1.2703   0.01857   0.01236  -0.0419   0.0106   1.0000
  10.250   1.2827   0.01921   0.01305  -0.0397   0.0104   1.0000
  10.500   1.2962   0.01981   0.01370  -0.0378   0.0100   1.0000
  10.750   1.3065   0.02062   0.01458  -0.0356   0.0097   1.0000
  11.000   1.3164   0.02149   0.01551  -0.0335   0.0094   1.0000
  11.250   1.3259   0.02243   0.01651  -0.0315   0.0091   1.0000
  11.500   1.3332   0.02356   0.01770  -0.0294   0.0088   1.0000
  11.750   1.3403   0.02478   0.01897  -0.0276   0.0084   1.0000
  12.000   1.3443   0.02630   0.02057  -0.0256   0.0084   1.0000
  12.250   1.3445   0.02821   0.02257  -0.0237   0.0081   1.0000
  12.500   1.3348   0.03111   0.02561  -0.0214   0.0078   1.0000
  12.750   1.3354   0.03330   0.02789  -0.0201   0.0077   1.0000
  13.000   1.3407   0.03514   0.02982  -0.0193   0.0076   1.0000
  13.250   1.3463   0.03701   0.03177  -0.0186   0.0076   1.0000
  13.500   1.3503   0.03911   0.03396  -0.0179   0.0074   1.0000
  13.750   1.3564   0.04107   0.03600  -0.0176   0.0072   1.0000
  14.000   1.3548   0.04382   0.03885  -0.0170   0.0072   1.0000
  14.250   1.3571   0.04625   0.04137  -0.0167   0.0070   1.0000
  14.500   1.3605   0.04864   0.04383  -0.0167   0.0068   1.0000
  14.750   1.3587   0.05163   0.04693  -0.0165   0.0067   1.0000
  15.000   1.3550   0.05490   0.05030  -0.0164   0.0068   1.0000
  15.250   1.3577   0.05765   0.05313  -0.0169   0.0065   1.0000
  15.500   1.3587   0.06065   0.05620  -0.0175   0.0063   1.0000
  15.750   1.3557   0.06415   0.05979  -0.0181   0.0062   1.0000
  16.000   1.3505   0.06798   0.06374  -0.0186   0.0062   1.0000
  16.250   1.3493   0.07153   0.06735  -0.0196   0.0061   1.0000
  16.500   1.3444   0.07554   0.07146  -0.0206   0.0060   1.0000
  16.750   1.3378   0.07983   0.07587  -0.0217   0.0060   1.0000
  17.000   1.3308   0.08438   0.08047  -0.0231   0.0058   1.0000
  17.250   1.3251   0.08882   0.08501  -0.0246   0.0058   1.0000
  17.500   1.3159   0.09379   0.09010  -0.0262   0.0057   1.0000
  17.750   1.3060   0.09902   0.09544  -0.0281   0.0057   1.0000
  18.000   1.2958   0.10447   0.10101  -0.0302   0.0056   1.0000
  18.250   1.2752   0.11169   0.10841  -0.0329   0.0055   1.0000
  18.500   1.2686   0.11697   0.11379  -0.0355   0.0056   1.0000
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