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NPL 9510 AIRFOIL (npl9510-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NPL 9510 AIRFOIL (npl9510-il)
Reynolds number: 200,000
Max Cl/Cd: 25.44 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-npl9510-il-200000.txt
Download as CSV file: xf-npl9510-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NPL 9510 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.750  -0.8005   0.11882   0.11459  -0.0225   1.0000   0.0483
 -14.500  -0.8242   0.10857   0.10429  -0.0274   1.0000   0.0473
 -14.250  -0.8842   0.09179   0.08735  -0.0381   1.0000   0.0459
 -14.000  -0.9399   0.07888   0.07417  -0.0467   1.0000   0.0448
 -13.750  -0.9851   0.06927   0.06425  -0.0527   1.0000   0.0440
 -13.500  -1.0174   0.06227   0.05695  -0.0564   1.0000   0.0436
 -13.250  -1.0384   0.05713   0.05154  -0.0585   1.0000   0.0435
 -13.000  -1.0523   0.05303   0.04721  -0.0597   1.0000   0.0435
 -12.750  -1.0616   0.04958   0.04355  -0.0601   1.0000   0.0436
 -12.500  -1.0683   0.04666   0.04042  -0.0597   1.0000   0.0438
 -12.250  -1.0721   0.04412   0.03770  -0.0590   1.0000   0.0441
 -12.000  -1.0690   0.04169   0.03507  -0.0587   1.0000   0.0445
 -11.750  -1.0626   0.03951   0.03269  -0.0579   1.0000   0.0450
 -11.500  -1.0539   0.03751   0.03049  -0.0570   1.0000   0.0456
 -11.250  -1.0431   0.03569   0.02848  -0.0560   1.0000   0.0464
 -11.000  -1.0310   0.03411   0.02666  -0.0551   1.0000   0.0474
 -10.750  -1.0172   0.03256   0.02489  -0.0542   1.0000   0.0484
 -10.500  -1.0002   0.03079   0.02318  -0.0528   1.0000   0.0497
 -10.250  -0.9836   0.02958   0.02197  -0.0517   1.0000   0.0510
 -10.000  -0.9667   0.02842   0.02075  -0.0507   1.0000   0.0524
  -9.750  -0.9494   0.02731   0.01954  -0.0496   1.0000   0.0541
  -9.500  -0.9313   0.02631   0.01841  -0.0486   1.0000   0.0558
  -9.250  -0.9152   0.02493   0.01714  -0.0475   1.0000   0.0582
  -9.000  -0.8964   0.02399   0.01619  -0.0468   1.0000   0.0612
  -8.750  -0.8762   0.02312   0.01521  -0.0463   1.0000   0.0646
  -8.500  -0.8573   0.02183   0.01403  -0.0459   1.0000   0.0687
  -8.250  -0.8352   0.02098   0.01313  -0.0458   1.0000   0.0743
  -8.000  -0.8128   0.01989   0.01211  -0.0461   1.0000   0.0822
  -7.750  -0.7887   0.01889   0.01117  -0.0467   1.0000   0.0941
  -7.500  -0.7632   0.01787   0.01022  -0.0474   1.0000   0.1123
  -7.250  -0.7367   0.01691   0.00939  -0.0485   1.0000   0.1362
  -7.000  -0.7094   0.01608   0.00867  -0.0496   1.0000   0.1612
  -6.750  -0.6815   0.01532   0.00801  -0.0506   1.0000   0.1882
  -6.500  -0.6522   0.01445   0.00734  -0.0521   1.0000   0.2237
  -6.250  -0.6213   0.01349   0.00672  -0.0541   1.0000   0.2847
  -6.000  -0.5909   0.01285   0.00646  -0.0555   1.0000   0.3630
  -5.750  -0.5631   0.01274   0.00647  -0.0558   1.0000   0.4125
  -5.500  -0.5364   0.01282   0.00658  -0.0556   1.0000   0.4441
  -5.250  -0.5105   0.01301   0.00679  -0.0552   1.0000   0.4676
  -5.000  -0.4849   0.01324   0.00698  -0.0547   1.0000   0.4853
  -4.750  -0.4596   0.01345   0.00719  -0.0540   1.0000   0.4982
  -4.500  -0.4337   0.01363   0.00732  -0.0536   1.0000   0.5099
  -4.250  -0.4080   0.01381   0.00746  -0.0531   1.0000   0.5200
  -4.000  -0.3827   0.01395   0.00761  -0.0525   1.0000   0.5279
  -3.750  -0.3568   0.01411   0.00773  -0.0521   1.0000   0.5368
  -3.500  -0.3312   0.01422   0.00785  -0.0516   1.0000   0.5437
  -3.250  -0.3061   0.01437   0.00801  -0.0510   1.0000   0.5506
  -3.000  -0.2794   0.01447   0.00806  -0.0509   1.0000   0.5588
  -2.750  -0.2559   0.01469   0.00836  -0.0499   1.0000   0.5651
  -2.500  -0.2293   0.01486   0.00848  -0.0498   1.0000   0.5750
  -2.250  -0.2075   0.01515   0.00890  -0.0482   1.0000   0.5816
  -2.000  -0.1812   0.01533   0.00905  -0.0481   1.0000   0.5910
  -1.750  -0.1570   0.01544   0.00923  -0.0473   1.0000   0.5957
  -1.500  -0.1319   0.01554   0.00938  -0.0469   1.0000   0.6004
  -1.250  -0.1047   0.01559   0.00942  -0.0471   1.0000   0.6061
  -1.000  -0.0774   0.01561   0.00945  -0.0473   1.0000   0.6110
  -0.750  -0.0527   0.01572   0.00964  -0.0468   1.0000   0.6147
  -0.500  -0.0270   0.01583   0.00981  -0.0466   1.0000   0.6193
  -0.250   0.0005   0.01592   0.00990  -0.0470   1.0000   0.6249
   0.000   0.0267   0.01601   0.01006  -0.0470   1.0000   0.6290
   0.250   0.0514   0.01616   0.01032  -0.0466   1.0000   0.6327
   0.500   0.1939   0.01504   0.00939  -0.0678   0.9601   0.6399
   0.750   0.2802   0.01330   0.00782  -0.0771   0.9232   0.6455
   1.000   0.3041   0.01465   0.00665  -0.0728   0.2826   0.6487
   1.250   0.3227   0.01616   0.00725  -0.0713   0.1037   0.6525
   1.500   0.3493   0.01664   0.00764  -0.0710   0.0898   0.6572
   1.750   0.3758   0.01723   0.00813  -0.0708   0.0824   0.6621
   2.000   0.4014   0.01762   0.00857  -0.0700   0.0768   0.6656
   2.250   0.4265   0.01835   0.00923  -0.0694   0.0724   0.6696
   2.500   0.4537   0.01905   0.00994  -0.0691   0.0699   0.6742
   2.750   0.4825   0.01965   0.01053  -0.0691   0.0670   0.6793
   3.000   0.5088   0.02026   0.01116  -0.0686   0.0639   0.6829
   3.250   0.5361   0.02137   0.01223  -0.0683   0.0619   0.6872
   3.500   0.5653   0.02268   0.01361  -0.0683   0.0606   0.6921
   3.750   0.5945   0.02345   0.01455  -0.0683   0.0589   0.6969
   4.000   0.6215   0.02443   0.01574  -0.0676   0.0570   0.7007
   4.250   0.6492   0.02588   0.01742  -0.0671   0.0564   0.7055
   4.500   0.6774   0.02782   0.01963  -0.0667   0.0567   0.7109
   4.750   0.7034   0.02994   0.02209  -0.0658   0.0569   0.7151
   5.000   0.7275   0.03241   0.02496  -0.0646   0.0576   0.7191
   5.250   0.7530   0.03570   0.02832  -0.0641   0.0620   0.7241
   5.500   0.7235   0.03137   0.02576  -0.0512   0.0983   0.7195
   5.750   0.7364   0.03412   0.02912  -0.0489   0.0882   0.7247
   6.000   0.7547   0.03669   0.03165  -0.0484   0.0858   0.7301
   6.250   0.7582   0.04160   0.03701  -0.0461   0.0803   0.7335
   6.500   0.8327   0.05561   0.05072  -0.0543   0.0744   0.7469
   6.750   0.8493   0.05838   0.05348  -0.0536   0.0731   0.7518
   7.000   0.8611   0.06609   0.06100  -0.0541   0.0716   0.7571
   7.250   0.8534   0.06718   0.06309  -0.0504   0.0658   0.7619
   7.500   0.8603   0.07026   0.06632  -0.0493   0.0641   0.7665
   7.750   0.8689   0.07319   0.06932  -0.0484   0.0630   0.7722
   8.000   0.8802   0.07628   0.07239  -0.0477   0.0622   0.7785
   8.250   0.8954   0.08059   0.07662  -0.0474   0.0615   0.7843
   8.500   0.8839   0.08686   0.08309  -0.0466   0.0609   0.7894
   8.750   0.8393   0.09185   0.08850  -0.0463   0.0602   0.7935
   9.000   0.8038   0.09949   0.09631  -0.0522   0.0593   0.7973
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