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K3311 (smoothed) (k3311sm-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: K3311 (smoothed) (k3311sm-il)
Reynolds number: 100,000
Max Cl/Cd: 55.35 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-k3311sm-il-100000.txt
Download as CSV file: xf-k3311sm-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3545   0.10629   0.10129  -0.0362   1.0000   0.0917
  -9.250  -0.3686   0.10414   0.09926  -0.0397   1.0000   0.0934
  -9.000  -0.3886   0.10209   0.09736  -0.0433   1.0000   0.0940
  -8.750  -0.3514   0.09685   0.09204  -0.0370   1.0000   0.0993
  -8.500  -0.3518   0.09420   0.08945  -0.0371   1.0000   0.1035
  -8.250  -0.2824   0.08257   0.07830  -0.0368   1.0000   0.1144
  -8.000  -0.2899   0.08003   0.07584  -0.0360   1.0000   0.1184
  -7.750  -0.3156   0.07816   0.07412  -0.0355   1.0000   0.1213
  -7.500  -0.3821   0.08382   0.07948  -0.0349   1.0000   0.1143
  -7.250  -0.3966   0.08204   0.07782  -0.0328   1.0000   0.1165
  -7.000  -0.4161   0.07985   0.07575  -0.0325   1.0000   0.1195
  -6.750  -0.4506   0.07725   0.07317  -0.0363   1.0000   0.1221
  -6.500  -0.4638   0.07380   0.06974  -0.0358   1.0000   0.1240
  -6.250  -0.4557   0.07224   0.06831  -0.0299   1.0000   0.1271
  -6.000  -0.4604   0.07020   0.06630  -0.0283   1.0000   0.1319
  -5.750  -0.4734   0.06624   0.06221  -0.0318   1.0000   0.1392
  -5.500  -0.4594   0.06415   0.06018  -0.0298   0.9980   0.1450
  -5.250  -0.4276   0.05864   0.05438  -0.0397   0.9888   0.1682
  -5.000  -0.3958   0.05530   0.05104  -0.0424   0.9823   0.1850
  -4.750  -0.3667   0.05224   0.04789  -0.0458   0.9736   0.2135
  -4.500  -0.3108   0.03746   0.03079  -0.0573   0.9664   0.0956
  -4.250  -0.2699   0.03348   0.02597  -0.0590   0.9596   0.0793
  -4.000  -0.2342   0.03016   0.02228  -0.0608   0.9529   0.0767
  -3.750  -0.1956   0.02814   0.01972  -0.0626   0.9454   0.0782
  -3.500  -0.1578   0.02643   0.01756  -0.0641   0.9380   0.0807
  -3.250  -0.1194   0.02446   0.01553  -0.0660   0.9311   0.0842
  -3.000  -0.0817   0.02349   0.01439  -0.0676   0.9233   0.0932
  -2.750  -0.0436   0.02206   0.01307  -0.0694   0.9162   0.1019
  -2.500  -0.0097   0.02112   0.01221  -0.0704   0.9079   0.1182
  -2.250   0.0284   0.01991   0.01123  -0.0722   0.9010   0.1569
  -2.000   0.0452   0.01767   0.01118  -0.0698   0.8923   0.6287
  -1.750   0.0791   0.01712   0.01105  -0.0690   0.8863   0.7864
  -1.500   0.2022   0.01665   0.01062  -0.0845   0.8903   0.9841
  -1.250   0.2610   0.01624   0.00991  -0.0913   0.8849   1.0000
  -1.000   0.2829   0.01617   0.00963  -0.0910   0.8721   1.0000
  -0.750   0.3091   0.01617   0.00942  -0.0910   0.8607   1.0000
  -0.500   0.3436   0.01605   0.00911  -0.0922   0.8522   1.0000
  -0.250   0.3719   0.01604   0.00895  -0.0922   0.8417   1.0000
   0.000   0.3958   0.01616   0.00893  -0.0914   0.8301   1.0000
   0.250   0.4235   0.01621   0.00885  -0.0912   0.8201   1.0000
   0.500   0.4546   0.01616   0.00867  -0.0914   0.8114   1.0000
   0.750   0.4773   0.01635   0.00877  -0.0904   0.7996   1.0000
   1.000   0.5023   0.01650   0.00884  -0.0897   0.7891   1.0000
   1.250   0.5340   0.01644   0.00866  -0.0898   0.7811   1.0000
   1.500   0.5560   0.01668   0.00886  -0.0887   0.7692   1.0000
   1.750   0.5799   0.01690   0.00902  -0.0878   0.7581   1.0000
   2.000   0.6073   0.01700   0.00905  -0.0874   0.7487   1.0000
   2.250   0.6339   0.01712   0.00911  -0.0868   0.7385   1.0000
   2.500   0.6569   0.01739   0.00938  -0.0858   0.7271   1.0000
   2.750   0.6821   0.01759   0.00955  -0.0851   0.7166   1.0000
   3.000   0.7117   0.01762   0.00952  -0.0849   0.7078   1.0000
   3.250   0.7340   0.01793   0.00984  -0.0838   0.6958   1.0000
   3.500   0.7578   0.01820   0.01014  -0.0829   0.6844   1.0000
   3.750   0.7838   0.01839   0.01032  -0.0823   0.6739   1.0000
   4.000   0.8121   0.01848   0.01037  -0.0819   0.6640   1.0000
   4.250   0.8348   0.01877   0.01074  -0.0808   0.6516   1.0000
   4.500   0.8584   0.01905   0.01105  -0.0799   0.6395   1.0000
   4.750   0.8832   0.01927   0.01130  -0.0791   0.6278   1.0000
   5.000   0.9094   0.01943   0.01147  -0.0784   0.6162   1.0000
   5.250   0.9370   0.01953   0.01159  -0.0779   0.6048   1.0000
   5.500   0.9602   0.01978   0.01190  -0.0768   0.5914   1.0000
   5.750   0.9836   0.02001   0.01220  -0.0758   0.5778   1.0000
   6.000   1.0075   0.02022   0.01246  -0.0748   0.5639   1.0000
   6.250   1.0314   0.02040   0.01273  -0.0737   0.5495   1.0000
   6.500   1.0553   0.02056   0.01294  -0.0727   0.5345   1.0000
   6.750   1.0792   0.02071   0.01314  -0.0716   0.5190   1.0000
   7.000   1.1034   0.02085   0.01330  -0.0705   0.5029   1.0000
   7.250   1.1237   0.02109   0.01366  -0.0689   0.4847   1.0000
   7.500   1.1438   0.02125   0.01391  -0.0672   0.4650   1.0000
   7.750   1.1647   0.02127   0.01390  -0.0655   0.4434   1.0000
   8.000   1.1801   0.02138   0.01406  -0.0631   0.4178   1.0000
   8.250   1.1939   0.02157   0.01429  -0.0604   0.3907   1.0000
   8.500   1.2065   0.02190   0.01467  -0.0577   0.3627   1.0000
   8.750   1.2171   0.02237   0.01513  -0.0548   0.3328   1.0000
   9.000   1.2247   0.02303   0.01572  -0.0515   0.3007   1.0000
   9.250   1.2282   0.02391   0.01655  -0.0479   0.2633   1.0000
   9.500   1.2249   0.02514   0.01759  -0.0434   0.2207   1.0000
   9.750   1.2132   0.02690   0.01903  -0.0381   0.1759   1.0000
  10.000   1.1986   0.02928   0.02103  -0.0332   0.1358   1.0000
  10.250   1.1879   0.03178   0.02328  -0.0293   0.1106   1.0000
  10.500   1.1815   0.03422   0.02555  -0.0262   0.0955   1.0000
  10.750   1.1800   0.03651   0.02781  -0.0238   0.0838   1.0000
  11.000   1.1832   0.03871   0.03001  -0.0217   0.0752   1.0000
  11.250   1.1932   0.04090   0.03204  -0.0200   0.0687   1.0000
  11.500   1.2042   0.04281   0.03411  -0.0185   0.0630   1.0000
  11.750   1.2266   0.04509   0.03624  -0.0177   0.0573   1.0000
  12.000   1.2443   0.04729   0.03871  -0.0165   0.0544   1.0000
  12.250   1.2637   0.04981   0.04145  -0.0157   0.0519   1.0000
  12.500   1.2787   0.05241   0.04418  -0.0148   0.0493   1.0000
  12.750   1.2988   0.05675   0.04865  -0.0147   0.0468   1.0000
  13.000   1.2915   0.05952   0.05176  -0.0127   0.0461   1.0000
  13.250   1.2836   0.06291   0.05549  -0.0111   0.0457   1.0000
  13.500   1.2738   0.06669   0.05958  -0.0099   0.0455   1.0000
  13.750   1.2608   0.07083   0.06403  -0.0092   0.0454   1.0000
  14.000   1.2458   0.07527   0.06875  -0.0089   0.0454   1.0000
  14.250   1.2275   0.08019   0.07394  -0.0093   0.0455   1.0000
  14.500   1.2076   0.08555   0.07955  -0.0104   0.0457   1.0000
  14.750   1.1865   0.09140   0.08561  -0.0122   0.0459   1.0000
  15.000   1.1661   0.09759   0.09201  -0.0145   0.0462   1.0000
  15.250   1.1432   0.10445   0.09905  -0.0177   0.0465   1.0000
  15.500   1.1223   0.11175   0.10650  -0.0212   0.0468   1.0000
  15.750   1.1024   0.11933   0.11424  -0.0252   0.0472   1.0000
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