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PSU-90-125WL (psu-90-125wl-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: PSU-90-125WL (psu-90-125wl-il)
Reynolds number: 200,000
Max Cl/Cd: 70.28 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-psu-90-125wl-il-200000-n5.txt
Download as CSV file: xf-psu-90-125wl-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: PSU-90-125WL                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.4677   0.08972   0.08603  -0.0494   1.0000   0.0180
 -11.000  -0.5878   0.05778   0.05383  -0.0705   1.0000   0.0162
 -10.750  -0.6232   0.05141   0.04724  -0.0737   1.0000   0.0159
 -10.500  -0.6493   0.04797   0.04367  -0.0728   1.0000   0.0159
 -10.250  -0.6751   0.04605   0.04168  -0.0688   1.0000   0.0159
 -10.000  -0.6952   0.04397   0.03946  -0.0649   0.9991   0.0159
  -9.750  -0.6816   0.04031   0.03547  -0.0680   0.9907   0.0162
  -9.500  -0.6619   0.03769   0.03259  -0.0704   0.9840   0.0167
  -9.250  -0.6442   0.03506   0.02965  -0.0717   0.9756   0.0171
  -9.000  -0.6218   0.03257   0.02683  -0.0733   0.9694   0.0177
  -8.750  -0.6015   0.03018   0.02408  -0.0738   0.9610   0.0180
  -8.500  -0.5759   0.02790   0.02142  -0.0750   0.9555   0.0182
  -8.250  -0.5524   0.02610   0.01935  -0.0752   0.9477   0.0185
  -8.000  -0.5234   0.02443   0.01742  -0.0763   0.9432   0.0189
  -7.750  -0.4982   0.02308   0.01588  -0.0764   0.9355   0.0192
  -7.500  -0.4686   0.02183   0.01446  -0.0774   0.9304   0.0196
  -7.250  -0.4412   0.02078   0.01324  -0.0777   0.9239   0.0200
  -7.000  -0.4146   0.01956   0.01194  -0.0781   0.9177   0.0206
  -6.750  -0.3867   0.01859   0.01093  -0.0787   0.9122   0.0216
  -6.500  -0.3608   0.01792   0.01019  -0.0788   0.9049   0.0228
  -6.250  -0.3321   0.01721   0.00938  -0.0793   0.8997   0.0241
  -6.000  -0.3075   0.01658   0.00865  -0.0790   0.8924   0.0250
  -5.750  -0.2802   0.01600   0.00795  -0.0791   0.8866   0.0260
  -5.500  -0.2548   0.01541   0.00728  -0.0789   0.8802   0.0277
  -5.250  -0.2290   0.01494   0.00674  -0.0787   0.8738   0.0304
  -5.000  -0.2016   0.01448   0.00620  -0.0787   0.8688   0.0355
  -4.750  -0.1776   0.01397   0.00576  -0.0781   0.8617   0.0524
  -4.500  -0.1524   0.01339   0.00535  -0.0780   0.8562   0.0941
  -4.250  -0.1277   0.01292   0.00504  -0.0777   0.8501   0.1380
  -4.000  -0.1030   0.01246   0.00477  -0.0774   0.8441   0.1907
  -3.750  -0.0768   0.01204   0.00451  -0.0774   0.8393   0.2462
  -3.500  -0.0535   0.01160   0.00435  -0.0768   0.8327   0.3175
  -3.250  -0.0292   0.01115   0.00420  -0.0764   0.8273   0.4012
  -3.000  -0.0045   0.01083   0.00410  -0.0758   0.8219   0.4695
  -2.750   0.0205   0.01066   0.00407  -0.0752   0.8158   0.5222
  -2.500   0.0473   0.01055   0.00402  -0.0749   0.8108   0.5633
  -2.250   0.0733   0.01051   0.00399  -0.0744   0.8047   0.5960
  -2.000   0.0999   0.01047   0.00397  -0.0739   0.7988   0.6232
  -1.750   0.1272   0.01045   0.00392  -0.0737   0.7937   0.6459
  -1.500   0.1532   0.01044   0.00392  -0.0732   0.7871   0.6658
  -1.250   0.1805   0.01043   0.00387  -0.0728   0.7816   0.6840
  -1.000   0.2070   0.01043   0.00387  -0.0724   0.7754   0.7003
  -0.750   0.2337   0.01042   0.00385  -0.0720   0.7690   0.7149
  -0.500   0.2608   0.01042   0.00383  -0.0717   0.7631   0.7286
  -0.250   0.2869   0.01042   0.00384  -0.0712   0.7558   0.7418
   0.000   0.3141   0.01041   0.00381  -0.0709   0.7497   0.7549
   0.250   0.3398   0.01041   0.00384  -0.0703   0.7416   0.7678
   0.500   0.3669   0.01041   0.00381  -0.0699   0.7351   0.7805
   1.000   0.4187   0.01041   0.00384  -0.0688   0.7192   0.8054
   1.250   0.4440   0.01041   0.00388  -0.0682   0.7101   0.8179
   1.500   0.4696   0.01041   0.00391  -0.0675   0.7013   0.8307
   1.750   0.4953   0.01041   0.00391  -0.0669   0.6920   0.8438
   2.000   0.5201   0.01041   0.00395  -0.0660   0.6810   0.8578
   2.250   0.5451   0.01041   0.00399  -0.0653   0.6699   0.8725
   2.500   0.5707   0.01042   0.00401  -0.0646   0.6580   0.8881
   2.750   0.5971   0.01043   0.00404  -0.0641   0.6448   0.9047
   3.000   0.6250   0.01046   0.00407  -0.0640   0.6297   0.9224
   3.250   0.6555   0.01050   0.00412  -0.0645   0.6123   0.9409
   3.500   0.6892   0.01059   0.00416  -0.0657   0.5922   0.9594
   3.750   0.7239   0.01071   0.00422  -0.0673   0.5699   0.9802
   4.000   0.7554   0.01089   0.00432  -0.0683   0.5468   1.0000
   4.250   0.7766   0.01112   0.00445  -0.0671   0.5252   1.0000
   4.500   0.7980   0.01138   0.00461  -0.0660   0.5029   1.0000
   4.750   0.8195   0.01166   0.00481  -0.0649   0.4800   1.0000
   5.000   0.8407   0.01198   0.00505  -0.0638   0.4574   1.0000
   5.250   0.8620   0.01231   0.00530  -0.0627   0.4343   1.0000
   5.500   0.8827   0.01268   0.00557  -0.0615   0.4121   1.0000
   5.750   0.9036   0.01304   0.00587  -0.0604   0.3894   1.0000
   6.000   0.9237   0.01345   0.00622  -0.0591   0.3676   1.0000
   6.250   0.9438   0.01385   0.00656  -0.0579   0.3450   1.0000
   6.500   0.9631   0.01430   0.00694  -0.0566   0.3238   1.0000
   6.750   0.9826   0.01474   0.00733  -0.0553   0.3025   1.0000
   7.000   1.0010   0.01524   0.00778  -0.0539   0.2816   1.0000
   7.250   1.0192   0.01574   0.00823  -0.0525   0.2606   1.0000
   7.500   1.0367   0.01627   0.00870  -0.0509   0.2404   1.0000
   7.750   1.0533   0.01683   0.00921  -0.0493   0.2215   1.0000
   8.000   1.0694   0.01739   0.00974  -0.0476   0.2025   1.0000
   8.250   1.0839   0.01798   0.01030  -0.0456   0.1853   1.0000
   8.500   1.0978   0.01861   0.01090  -0.0436   0.1690   1.0000
   8.750   1.1110   0.01931   0.01154  -0.0416   0.1529   1.0000
   9.000   1.1238   0.02005   0.01224  -0.0396   0.1352   1.0000
   9.250   1.1357   0.02088   0.01299  -0.0376   0.1165   1.0000
   9.500   1.1474   0.02175   0.01380  -0.0356   0.1012   1.0000
   9.750   1.1588   0.02265   0.01466  -0.0338   0.0874   1.0000
  10.000   1.1697   0.02362   0.01561  -0.0319   0.0745   1.0000
  10.250   1.1802   0.02464   0.01660  -0.0302   0.0629   1.0000
  10.500   1.1910   0.02566   0.01764  -0.0285   0.0540   1.0000
  10.750   1.1999   0.02685   0.01882  -0.0268   0.0439   1.0000
  11.000   1.2077   0.02816   0.02012  -0.0250   0.0347   1.0000
  11.250   1.2149   0.02956   0.02154  -0.0234   0.0279   1.0000
  11.500   1.2205   0.03113   0.02314  -0.0217   0.0220   1.0000
  11.750   1.2253   0.03282   0.02489  -0.0201   0.0188   1.0000
  12.000   1.2302   0.03456   0.02673  -0.0187   0.0163   1.0000
  12.250   1.2343   0.03640   0.02867  -0.0174   0.0151   1.0000
  12.500   1.2361   0.03852   0.03086  -0.0162   0.0141   1.0000
  12.750   1.2393   0.04057   0.03306  -0.0152   0.0134   1.0000
  13.000   1.2413   0.04280   0.03543  -0.0143   0.0128   1.0000
  13.250   1.2416   0.04529   0.03805  -0.0136   0.0122   1.0000
  13.500   1.2418   0.04788   0.04076  -0.0131   0.0116   1.0000
  13.750   1.2398   0.05079   0.04379  -0.0129   0.0111   1.0000
  14.000   1.2360   0.05405   0.04717  -0.0129   0.0108   1.0000
  14.250   1.2310   0.05762   0.05087  -0.0131   0.0105   1.0000
  14.500   1.2278   0.06114   0.05455  -0.0136   0.0102   1.0000
  14.750   1.2244   0.06486   0.05842  -0.0144   0.0099   1.0000
  15.000   1.2190   0.06901   0.06275  -0.0154   0.0098   1.0000
  15.250   1.2130   0.07341   0.06730  -0.0168   0.0097   1.0000
  15.500   1.2068   0.07802   0.07206  -0.0184   0.0095   1.0000
  15.750   1.2001   0.08285   0.07704  -0.0202   0.0094   1.0000
  16.000   1.1926   0.08798   0.08232  -0.0223   0.0093   1.0000
  16.250   1.1852   0.09320   0.08768  -0.0245   0.0092   1.0000
  16.500   1.1779   0.09855   0.09317  -0.0269   0.0091   1.0000
  16.750   1.1701   0.10409   0.09885  -0.0295   0.0090   1.0000
  17.000   1.1625   0.10970   0.10460  -0.0322   0.0090   1.0000
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