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I.S.A. 960 (isa960-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: I.S.A. 960 (isa960-il)
Reynolds number: 50,000
Max Cl/Cd: 38.04 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-isa960-il-50000-n5.txt
Download as CSV file: xf-isa960-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: I.S.A. 960                                      
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3322   0.09744   0.09111  -0.0340   1.0000   0.0603
  -8.750  -0.3388   0.09489   0.08868  -0.0332   1.0000   0.0590
  -8.500  -0.3474   0.09231   0.08624  -0.0326   1.0000   0.0577
  -8.250  -0.3559   0.08942   0.08347  -0.0328   1.0000   0.0565
  -7.750  -0.3749   0.08178   0.07598  -0.0368   1.0000   0.0533
  -7.500  -0.3765   0.07871   0.07294  -0.0368   1.0000   0.0531
  -7.250  -0.3767   0.07513   0.06938  -0.0379   1.0000   0.0531
  -7.000  -0.3741   0.07079   0.06500  -0.0401   1.0000   0.0534
  -6.750  -0.3701   0.06972   0.06401  -0.0378   1.0000   0.0555
  -6.500  -0.3612   0.06656   0.06080  -0.0391   0.9994   0.0570
  -6.250  -0.3273   0.06037   0.05437  -0.0471   0.9927   0.0582
  -6.000  -0.2905   0.05367   0.04730  -0.0551   0.9863   0.0592
  -5.750  -0.2500   0.04555   0.03837  -0.0637   0.9799   0.0634
  -5.500  -0.2149   0.04298   0.03557  -0.0672   0.9736   0.0676
  -5.250  -0.1764   0.03862   0.03055  -0.0715   0.9670   0.0727
  -5.000  -0.1371   0.03588   0.02731  -0.0751   0.9592   0.0808
  -4.750  -0.0917   0.03231   0.02284  -0.0791   0.9517   0.0896
  -4.500  -0.0523   0.03111   0.02138  -0.0816   0.9407   0.1024
  -4.250  -0.0090   0.02940   0.01924  -0.0844   0.9310   0.1164
  -4.000   0.0359   0.02845   0.01813  -0.0875   0.9211   0.1354
  -3.750   0.0735   0.02793   0.01736  -0.0895   0.9094   0.1608
  -3.500   0.1136   0.02707   0.01636  -0.0915   0.8976   0.1794
  -3.250   0.1537   0.02603   0.01499  -0.0930   0.8840   0.1905
  -3.000   0.1906   0.02512   0.01392  -0.0939   0.8689   0.1989
  -2.750   0.2248   0.02439   0.01301  -0.0943   0.8538   0.2095
  -2.500   0.2560   0.02384   0.01236  -0.0944   0.8405   0.2236
  -2.250   0.2863   0.02333   0.01176  -0.0943   0.8281   0.2387
  -2.000   0.3162   0.02280   0.01122  -0.0942   0.8157   0.2558
  -1.750   0.3435   0.02235   0.01080  -0.0938   0.8023   0.2781
  -1.500   0.3704   0.02188   0.01044  -0.0934   0.7892   0.3144
  -1.000   0.4268   0.01952   0.00975  -0.0921   0.7641   1.0000
  -0.750   0.4553   0.01952   0.00943  -0.0916   0.7499   1.0000
  -0.500   0.4831   0.01953   0.00916  -0.0911   0.7348   1.0000
  -0.250   0.5105   0.01957   0.00896  -0.0905   0.7197   1.0000
   0.000   0.5374   0.01966   0.00884  -0.0900   0.7053   1.0000
   0.250   0.5633   0.01978   0.00879  -0.0893   0.6897   1.0000
   0.500   0.5883   0.01993   0.00881  -0.0885   0.6729   1.0000
   0.750   0.6127   0.02010   0.00886  -0.0877   0.6546   1.0000
   1.000   0.6370   0.02026   0.00890  -0.0868   0.6343   1.0000
   1.250   0.6608   0.02044   0.00898  -0.0859   0.6117   1.0000
   1.500   0.6849   0.02063   0.00903  -0.0850   0.5882   1.0000
   1.750   0.7095   0.02083   0.00910  -0.0842   0.5663   1.0000
   2.000   0.7341   0.02106   0.00922  -0.0834   0.5457   1.0000
   2.250   0.7585   0.02131   0.00934  -0.0826   0.5247   1.0000
   2.500   0.7823   0.02163   0.00953  -0.0818   0.5029   1.0000
   2.750   0.8057   0.02198   0.00981  -0.0810   0.4819   1.0000
   3.000   0.8290   0.02236   0.01012  -0.0803   0.4628   1.0000
   3.250   0.8519   0.02277   0.01048  -0.0795   0.4440   1.0000
   3.500   0.8746   0.02320   0.01089  -0.0787   0.4247   1.0000
   3.750   0.8968   0.02367   0.01136  -0.0779   0.4055   1.0000
   4.000   0.9186   0.02417   0.01184  -0.0770   0.3869   1.0000
   4.250   0.9400   0.02471   0.01235  -0.0761   0.3694   1.0000
   4.500   0.9610   0.02528   0.01293  -0.0752   0.3536   1.0000
   4.750   0.9815   0.02588   0.01353  -0.0742   0.3390   1.0000
   5.000   1.0011   0.02655   0.01417  -0.0732   0.3240   1.0000
   5.250   1.0201   0.02727   0.01486  -0.0721   0.3102   1.0000
   5.500   1.0393   0.02799   0.01564  -0.0710   0.2992   1.0000
   5.750   1.0585   0.02873   0.01642  -0.0699   0.2907   1.0000
   6.000   1.0776   0.02950   0.01725  -0.0689   0.2830   1.0000
   6.250   1.0958   0.03033   0.01813  -0.0678   0.2745   1.0000
   6.500   1.1130   0.03123   0.01910  -0.0665   0.2656   1.0000
   6.750   1.1315   0.03210   0.02008  -0.0655   0.2584   1.0000
   7.000   1.1496   0.03301   0.02110  -0.0644   0.2515   1.0000
   7.250   1.1681   0.03395   0.02215  -0.0633   0.2451   1.0000
   7.500   1.1871   0.03491   0.02327  -0.0624   0.2385   1.0000
   7.750   1.2067   0.03590   0.02438  -0.0615   0.2330   1.0000
   8.000   1.2271   0.03691   0.02565  -0.0607   0.2269   1.0000
   8.250   1.2483   0.03795   0.02685  -0.0601   0.2217   1.0000
   8.500   1.2705   0.03903   0.02810  -0.0596   0.2171   1.0000
   8.750   1.2910   0.04022   0.02960  -0.0589   0.2122   1.0000
   9.000   1.3120   0.04143   0.03105  -0.0583   0.2081   1.0000
   9.250   1.3272   0.04256   0.03238  -0.0570   0.2027   1.0000
   9.500   1.3297   0.04397   0.03416  -0.0545   0.1948   1.0000
   9.750   1.3305   0.04530   0.03566  -0.0520   0.1866   1.0000
  10.000   1.3297   0.04694   0.03761  -0.0497   0.1777   1.0000
  10.250   1.3281   0.04877   0.03972  -0.0479   0.1684   1.0000
  10.500   1.3235   0.05078   0.04188  -0.0463   0.1583   1.0000
  10.750   1.3171   0.05312   0.04418  -0.0451   0.1490   1.0000
  11.000   1.3098   0.05589   0.04677  -0.0442   0.1411   1.0000
  11.250   1.3035   0.05899   0.04971  -0.0434   0.1334   1.0000
  11.500   1.2971   0.06237   0.05299  -0.0426   0.1243   1.0000
  11.750   1.2912   0.06594   0.05661  -0.0419   0.1152   1.0000
  12.000   1.2847   0.06974   0.06059  -0.0415   0.1071   1.0000
  12.250   1.2736   0.07422   0.06534  -0.0419   0.0992   1.0000
  12.500   1.2595   0.07948   0.07099  -0.0432   0.0918   1.0000
  12.750   1.2447   0.08655   0.07920  -0.0460   0.0742   1.0000
  13.000   1.2346   0.09166   0.08438  -0.0479   0.0627   1.0000
  13.250   1.2238   0.09704   0.08968  -0.0503   0.0580   1.0000
  13.500   1.2121   0.10288   0.09551  -0.0527   0.0548   1.0000
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