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PSU-90-125WL (psu-90-125wl-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: PSU-90-125WL (psu-90-125wl-il)
Reynolds number: 50,000
Max Cl/Cd: 34.91 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-psu-90-125wl-il-50000-n5.txt
Download as CSV file: xf-psu-90-125wl-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.4222   0.10355   0.09621  -0.0472   1.0000   0.0529
 -10.500  -0.4258   0.09899   0.09173  -0.0487   1.0000   0.0525
 -10.250  -0.4310   0.09424   0.08705  -0.0505   1.0000   0.0520
 -10.000  -0.4390   0.08905   0.08195  -0.0525   1.0000   0.0514
  -9.750  -0.4516   0.08293   0.07595  -0.0555   1.0000   0.0507
  -9.500  -0.4717   0.07657   0.06966  -0.0589   1.0000   0.0499
  -9.250  -0.4972   0.07152   0.06468  -0.0608   1.0000   0.0492
  -9.000  -0.5279   0.06794   0.06115  -0.0599   1.0000   0.0488
  -8.750  -0.5541   0.06473   0.05793  -0.0578   1.0000   0.0483
  -8.500  -0.5769   0.06166   0.05479  -0.0553   1.0000   0.0481
  -8.250  -0.5955   0.05868   0.05166  -0.0525   1.0000   0.0478
  -8.000  -0.6093   0.05573   0.04850  -0.0497   1.0000   0.0477
  -7.750  -0.6179   0.05277   0.04528  -0.0471   1.0000   0.0477
  -7.500  -0.6214   0.04988   0.04207  -0.0448   1.0000   0.0477
  -7.250  -0.6204   0.04707   0.03892  -0.0428   1.0000   0.0480
  -7.000  -0.6151   0.04442   0.03591  -0.0409   1.0000   0.0485
  -6.750  -0.6063   0.04196   0.03308  -0.0392   1.0000   0.0491
  -6.500  -0.5945   0.03973   0.03045  -0.0376   1.0000   0.0499
  -6.250  -0.5683   0.03735   0.02762  -0.0384   0.9959   0.0515
  -6.000  -0.5389   0.03542   0.02516  -0.0393   0.9911   0.0546
  -5.750  -0.5109   0.03381   0.02354  -0.0403   0.9863   0.0584
  -5.500  -0.4813   0.03244   0.02196  -0.0411   0.9819   0.0625
  -5.250  -0.4530   0.03114   0.02035  -0.0412   0.9767   0.0667
  -5.000  -0.4239   0.02990   0.01912  -0.0421   0.9720   0.0730
  -4.750  -0.3974   0.02883   0.01798  -0.0424   0.9665   0.0856
  -4.500  -0.3699   0.02761   0.01685  -0.0431   0.9610   0.1109
  -4.250  -0.3404   0.02627   0.01592  -0.0448   0.9564   0.1770
  -4.000  -0.3176   0.02509   0.01532  -0.0452   0.9499   0.2777
  -3.750  -0.2901   0.02431   0.01501  -0.0459   0.9446   0.3841
  -3.500  -0.2675   0.02394   0.01502  -0.0449   0.9383   0.4785
  -3.250  -0.2428   0.02392   0.01520  -0.0438   0.9320   0.5585
  -3.000  -0.2169   0.02405   0.01530  -0.0428   0.9262   0.6211
  -2.750  -0.1943   0.02418   0.01536  -0.0413   0.9191   0.6695
  -2.500  -0.1647   0.02436   0.01544  -0.0408   0.9140   0.7133
  -2.250  -0.1464   0.02447   0.01547  -0.0386   0.9060   0.7484
  -2.000  -0.1178   0.02460   0.01548  -0.0379   0.9005   0.7824
  -1.750  -0.0968   0.02469   0.01549  -0.0361   0.8929   0.8129
  -1.500  -0.0663   0.02478   0.01546  -0.0360   0.8869   0.8431
  -1.250  -0.0354   0.02488   0.01544  -0.0362   0.8805   0.8721
  -1.000   0.0027   0.02500   0.01542  -0.0379   0.8741   0.9001
  -0.750   0.0567   0.02511   0.01536  -0.0428   0.8702   0.9250
  -0.500   0.1056   0.02525   0.01535  -0.0473   0.8634   0.9475
  -0.250   0.1644   0.02531   0.01525  -0.0536   0.8584   0.9669
   0.000   0.2285   0.02525   0.01506  -0.0609   0.8547   0.9825
   0.250   0.2675   0.02532   0.01504  -0.0642   0.8455   1.0000
   0.500   0.2881   0.02528   0.01492  -0.0637   0.8365   1.0000
   0.750   0.3072   0.02529   0.01485  -0.0627   0.8267   1.0000
   1.000   0.3198   0.02542   0.01491  -0.0607   0.8153   1.0000
   1.250   0.3456   0.02547   0.01488  -0.0606   0.8065   1.0000
   1.500   0.3715   0.02554   0.01489  -0.0605   0.7971   1.0000
   1.750   0.3913   0.02575   0.01504  -0.0594   0.7858   1.0000
   2.000   0.4206   0.02581   0.01506  -0.0597   0.7767   1.0000
   2.250   0.4494   0.02585   0.01508  -0.0598   0.7671   1.0000
   2.500   0.4711   0.02606   0.01528  -0.0589   0.7551   1.0000
   2.750   0.4969   0.02618   0.01541  -0.0585   0.7442   1.0000
   3.000   0.5327   0.02601   0.01526  -0.0594   0.7360   1.0000
   3.250   0.5544   0.02621   0.01548  -0.0583   0.7230   1.0000
   3.500   0.5777   0.02636   0.01566  -0.0574   0.7103   1.0000
   3.750   0.6025   0.02645   0.01581  -0.0567   0.6976   1.0000
   4.000   0.6288   0.02647   0.01588  -0.0561   0.6849   1.0000
   4.250   0.6558   0.02643   0.01590  -0.0555   0.6720   1.0000
   4.500   0.6827   0.02638   0.01595  -0.0549   0.6587   1.0000
   4.750   0.7081   0.02637   0.01601  -0.0540   0.6442   1.0000
   5.000   0.7323   0.02638   0.01610  -0.0530   0.6286   1.0000
   5.250   0.7566   0.02638   0.01618  -0.0520   0.6125   1.0000
   5.500   0.7818   0.02634   0.01626  -0.0510   0.5956   1.0000
   5.750   0.8086   0.02625   0.01623  -0.0502   0.5783   1.0000
   6.000   0.8372   0.02608   0.01612  -0.0495   0.5604   1.0000
   6.250   0.8592   0.02626   0.01636  -0.0482   0.5398   1.0000
   6.500   0.8841   0.02634   0.01651  -0.0472   0.5188   1.0000
   6.750   0.9071   0.02656   0.01675  -0.0460   0.4968   1.0000
   7.000   0.9292   0.02686   0.01707  -0.0447   0.4741   1.0000
   7.250   0.9488   0.02731   0.01754  -0.0432   0.4508   1.0000
   7.500   0.9691   0.02776   0.01800  -0.0417   0.4277   1.0000
   7.750   0.9848   0.02842   0.01871  -0.0399   0.4041   1.0000
   8.000   1.0017   0.02907   0.01933  -0.0381   0.3813   1.0000
   8.250   1.0154   0.02987   0.02017  -0.0362   0.3585   1.0000
   8.500   1.0289   0.03068   0.02095  -0.0342   0.3371   1.0000
   8.750   1.0395   0.03161   0.02192  -0.0319   0.3159   1.0000
   9.000   1.0507   0.03258   0.02289  -0.0298   0.2959   1.0000
   9.250   1.0598   0.03369   0.02405  -0.0276   0.2760   1.0000
   9.500   1.0688   0.03488   0.02527  -0.0255   0.2572   1.0000
   9.750   1.0769   0.03614   0.02653  -0.0235   0.2393   1.0000
  10.000   1.0850   0.03749   0.02787  -0.0217   0.2228   1.0000
  10.250   1.0916   0.03899   0.02943  -0.0198   0.2064   1.0000
  10.500   1.0979   0.04059   0.03109  -0.0181   0.1912   1.0000
  10.750   1.1035   0.04230   0.03289  -0.0166   0.1770   1.0000
  11.000   1.1078   0.04414   0.03477  -0.0150   0.1636   1.0000
  11.250   1.1123   0.04606   0.03672  -0.0137   0.1515   1.0000
  11.500   1.1149   0.04820   0.03896  -0.0124   0.1396   1.0000
  11.750   1.1172   0.05052   0.04142  -0.0113   0.1284   1.0000
  12.000   1.1180   0.05303   0.04405  -0.0103   0.1181   1.0000
  12.250   1.1173   0.05565   0.04669  -0.0095   0.1090   1.0000
  12.500   1.1150   0.05850   0.04963  -0.0090   0.1003   1.0000
  12.750   1.1107   0.06181   0.05311  -0.0087   0.0920   1.0000
  13.000   1.1061   0.06499   0.05624  -0.0087   0.0851   1.0000
  13.250   1.0981   0.06900   0.06052  -0.0091   0.0778   1.0000
  13.500   1.0922   0.07272   0.06423  -0.0097   0.0722   1.0000
  13.750   1.0842   0.07723   0.06905  -0.0107   0.0668   1.0000
  14.000   1.0789   0.08113   0.07293  -0.0117   0.0625   1.0000
  14.250   1.0701   0.08626   0.07832  -0.0132   0.0587   1.0000
  14.500   1.0605   0.09165   0.08395  -0.0151   0.0555   1.0000
  14.750   1.0542   0.09643   0.08881  -0.0170   0.0528   1.0000
  15.000   1.0501   0.10092   0.09329  -0.0186   0.0504   1.0000
  15.250   1.0348   0.10823   0.10093  -0.0220   0.0493   1.0000
  15.500   1.0174   0.11636   0.10932  -0.0263   0.0486   1.0000
  15.750   0.9965   0.12580   0.11899  -0.0316   0.0485   1.0000
  16.000   0.9709   0.13719   0.13050  -0.0382   0.0489   1.0000
  16.250   0.9450   0.14975   0.14311  -0.0454   0.0494   1.0000
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