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K3311 (smoothed) (k3311sm-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: K3311 (smoothed) (k3311sm-il)
Reynolds number: 500,000
Max Cl/Cd: 108.28 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-k3311sm-il-500000.txt
Download as CSV file: xf-k3311sm-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: K3311 (smoothed)                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3661   0.08449   0.08231  -0.0403   1.0000   0.0220
  -8.500  -0.3737   0.08052   0.07839  -0.0416   1.0000   0.0231
  -8.000  -0.4057   0.07325   0.07127  -0.0430   0.9991   0.0237
  -7.750  -0.3832   0.06021   0.05804  -0.0644   0.9897   0.0240
  -7.500  -0.3653   0.05261   0.05014  -0.0738   0.9836   0.0241
  -6.750  -0.3280   0.02622   0.02208  -0.0856   0.9603   0.0186
  -6.500  -0.2967   0.02348   0.01897  -0.0873   0.9564   0.0184
  -6.250  -0.2738   0.02057   0.01566  -0.0872   0.9466   0.0184
  -6.000  -0.2479   0.01734   0.01204  -0.0877   0.9390   0.0190
  -5.750  -0.2189   0.01657   0.01121  -0.0883   0.9300   0.0202
  -5.500  -0.1914   0.01581   0.01033  -0.0883   0.9194   0.0213
  -5.250  -0.1641   0.01467   0.00899  -0.0880   0.9089   0.0223
  -5.000  -0.1369   0.01382   0.00797  -0.0877   0.8979   0.0234
  -4.750  -0.1111   0.01320   0.00720  -0.0871   0.8853   0.0243
  -4.500  -0.0884   0.01195   0.00585  -0.0862   0.8726   0.0263
  -4.250  -0.0626   0.01164   0.00549  -0.0857   0.8601   0.0286
  -4.000  -0.0366   0.01138   0.00514  -0.0852   0.8476   0.0309
  -3.750  -0.0125   0.01076   0.00440  -0.0843   0.8352   0.0328
  -3.500   0.0121   0.01031   0.00388  -0.0836   0.8229   0.0360
  -3.250   0.0378   0.01009   0.00358  -0.0831   0.8107   0.0396
  -3.000   0.0628   0.00973   0.00313  -0.0823   0.7983   0.0432
  -2.750   0.0881   0.00944   0.00280  -0.0818   0.7862   0.0501
  -2.500   0.1136   0.00918   0.00248  -0.0812   0.7746   0.0612
  -2.250   0.1386   0.00883   0.00221  -0.0806   0.7635   0.0982
  -2.000   0.1595   0.00794   0.00200  -0.0797   0.7524   0.3051
  -1.750   0.1822   0.00745   0.00194  -0.0789   0.7412   0.4505
  -1.500   0.2065   0.00724   0.00192  -0.0781   0.7306   0.5352
  -1.250   0.2315   0.00714   0.00190  -0.0774   0.7205   0.5884
  -1.000   0.2566   0.00705   0.00188  -0.0767   0.7101   0.6320
  -0.750   0.2812   0.00694   0.00188  -0.0759   0.7001   0.6814
  -0.500   0.3046   0.00680   0.00189  -0.0747   0.6908   0.7449
  -0.250   0.3270   0.00662   0.00191  -0.0733   0.6810   0.8190
   0.000   0.3554   0.00646   0.00193  -0.0730   0.6715   0.8930
   0.250   0.4138   0.00647   0.00192  -0.0796   0.6614   0.9513
   0.750   0.5061   0.00662   0.00190  -0.0877   0.6406   1.0000
   1.000   0.5300   0.00671   0.00191  -0.0869   0.6315   1.0000
   1.250   0.5542   0.00680   0.00193  -0.0861   0.6219   1.0000
   1.500   0.5787   0.00688   0.00196  -0.0854   0.6124   1.0000
   1.750   0.6032   0.00699   0.00199  -0.0847   0.6035   1.0000
   2.000   0.6279   0.00708   0.00204  -0.0841   0.5938   1.0000
   2.250   0.6527   0.00718   0.00211  -0.0834   0.5845   1.0000
   2.500   0.6772   0.00731   0.00217  -0.0827   0.5753   1.0000
   2.750   0.7022   0.00740   0.00224  -0.0821   0.5653   1.0000
   3.000   0.7269   0.00752   0.00232  -0.0815   0.5557   1.0000
   3.500   0.7765   0.00776   0.00252  -0.0802   0.5363   1.0000
   3.750   0.8013   0.00789   0.00262  -0.0796   0.5263   1.0000
   4.000   0.8258   0.00805   0.00274  -0.0789   0.5164   1.0000
   4.250   0.8506   0.00817   0.00287  -0.0783   0.5055   1.0000
   4.500   0.8753   0.00831   0.00300  -0.0776   0.4945   1.0000
   4.750   0.8997   0.00847   0.00314  -0.0770   0.4829   1.0000
   5.000   0.9240   0.00865   0.00329  -0.0763   0.4711   1.0000
   5.250   0.9480   0.00883   0.00346  -0.0756   0.4589   1.0000
   5.500   0.9723   0.00900   0.00364  -0.0749   0.4459   1.0000
   5.750   0.9962   0.00920   0.00382  -0.0742   0.4321   1.0000
   6.000   1.0195   0.00942   0.00403  -0.0734   0.4165   1.0000
   6.250   1.0422   0.00967   0.00424  -0.0724   0.3946   1.0000
   6.500   1.0634   0.01001   0.00448  -0.0713   0.3673   1.0000
   6.750   1.0845   0.01037   0.00475  -0.0701   0.3434   1.0000
   7.000   1.1053   0.01077   0.00507  -0.0690   0.3164   1.0000
   7.250   1.1248   0.01125   0.00543  -0.0676   0.2870   1.0000
   7.500   1.1436   0.01177   0.00583  -0.0662   0.2575   1.0000
   7.750   1.1620   0.01233   0.00626  -0.0647   0.2281   1.0000
   8.000   1.1793   0.01295   0.00675  -0.0630   0.1968   1.0000
   8.250   1.1944   0.01369   0.00732  -0.0611   0.1624   1.0000
   8.500   1.2079   0.01451   0.00795  -0.0589   0.1276   1.0000
   8.750   1.2185   0.01547   0.00870  -0.0563   0.0919   1.0000
   9.000   1.2251   0.01660   0.00959  -0.0531   0.0573   1.0000
   9.250   1.2313   0.01755   0.01043  -0.0496   0.0401   1.0000
   9.500   1.2391   0.01842   0.01129  -0.0464   0.0321   1.0000
   9.750   1.2468   0.01933   0.01224  -0.0434   0.0275   1.0000
  10.000   1.2567   0.02015   0.01312  -0.0409   0.0246   1.0000
  10.250   1.2590   0.02144   0.01446  -0.0375   0.0220   1.0000
  10.500   1.2676   0.02241   0.01552  -0.0352   0.0211   1.0000
  10.750   1.2762   0.02343   0.01664  -0.0330   0.0199   1.0000
  11.000   1.2838   0.02456   0.01783  -0.0309   0.0186   1.0000
  11.250   1.2897   0.02587   0.01920  -0.0289   0.0177   1.0000
  11.500   1.2877   0.02784   0.02126  -0.0264   0.0167   1.0000
  11.750   1.2841   0.03010   0.02363  -0.0242   0.0160   1.0000
  12.000   1.2928   0.03148   0.02511  -0.0230   0.0155   1.0000
  12.250   1.2971   0.03329   0.02703  -0.0218   0.0150   1.0000
  12.500   1.3016   0.03518   0.02901  -0.0207   0.0144   1.0000
  12.750   1.3038   0.03733   0.03126  -0.0197   0.0140   1.0000
  13.000   1.3065   0.03951   0.03352  -0.0189   0.0136   1.0000
  13.250   1.3092   0.04176   0.03584  -0.0183   0.0131   1.0000
  13.500   1.3091   0.04434   0.03850  -0.0177   0.0126   1.0000
  13.750   1.3044   0.04746   0.04170  -0.0170   0.0122   1.0000
  14.000   1.2995   0.05064   0.04499  -0.0162   0.0120   1.0000
  14.250   1.2983   0.05357   0.04804  -0.0157   0.0116   1.0000
  14.500   1.3023   0.05606   0.05065  -0.0160   0.0113   1.0000
  14.750   1.3032   0.05893   0.05365  -0.0161   0.0109   1.0000
  15.000   1.3020   0.06204   0.05689  -0.0160   0.0109   1.0000
  15.250   1.3018   0.06521   0.06017  -0.0165   0.0105   1.0000
  15.500   1.3010   0.06852   0.06359  -0.0170   0.0102   1.0000
  15.750   1.2987   0.07209   0.06728  -0.0177   0.0100   1.0000
  16.000   1.2953   0.07589   0.07120  -0.0185   0.0098   1.0000
  16.250   1.2916   0.07982   0.07526  -0.0194   0.0097   1.0000
  16.500   1.2881   0.08388   0.07941  -0.0207   0.0095   1.0000
  16.750   1.2826   0.08826   0.08392  -0.0220   0.0094   1.0000
  17.000   1.2770   0.09280   0.08857  -0.0236   0.0093   1.0000
  17.250   1.2706   0.09754   0.09342  -0.0254   0.0091   1.0000
  17.500   1.2625   0.10269   0.09871  -0.0274   0.0090   1.0000
  17.750   1.2543   0.10798   0.10412  -0.0296   0.0090   1.0000
  18.000   1.2433   0.11387   0.11015  -0.0323   0.0088   1.0000
  18.250   1.2320   0.12009   0.11652  -0.0353   0.0088   1.0000
  18.500   1.2142   0.12767   0.12427  -0.0392   0.0087   1.0000
  18.750   1.2029   0.13436   0.13112  -0.0430   0.0087   1.0000
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