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I.S.A. 571 (isa571-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: I.S.A. 571 (isa571-il)
Reynolds number: 200,000
Max Cl/Cd: 70.64 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-isa571-il-200000-n5.txt
Download as CSV file: xf-isa571-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: I.S.A. 571                                      
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3074   0.10184   0.09851  -0.0262   1.0000   0.0215
  -9.750  -0.3068   0.09835   0.09505  -0.0264   1.0000   0.0215
  -9.250  -0.3941   0.10412   0.10060  -0.0228   1.0000   0.0215
  -8.750  -0.3848   0.09670   0.09322  -0.0200   1.0000   0.0174
  -8.500  -0.3861   0.09374   0.09031  -0.0201   1.0000   0.0171
  -8.250  -0.3892   0.09106   0.08768  -0.0198   1.0000   0.0171
  -8.000  -0.3955   0.08859   0.08526  -0.0189   1.0000   0.0170
  -7.750  -0.3997   0.08593   0.08265  -0.0187   1.0000   0.0171
  -7.500  -0.4008   0.08278   0.07955  -0.0197   1.0000   0.0170
  -7.250  -0.4006   0.07926   0.07607  -0.0212   1.0000   0.0166
  -7.000  -0.3988   0.07488   0.07172  -0.0239   1.0000   0.0158
  -6.750  -0.3914   0.06731   0.06413  -0.0305   1.0000   0.0140
  -6.250  -0.3670   0.05879   0.05547  -0.0351   1.0000   0.0137
  -6.000  -0.3373   0.05230   0.04881  -0.0419   0.9976   0.0136
  -5.750  -0.3007   0.04498   0.04121  -0.0493   0.9950   0.0137
  -5.500  -0.2643   0.03665   0.03245  -0.0556   0.9920   0.0139
  -5.250  -0.2297   0.03379   0.02934  -0.0592   0.9890   0.0155
  -5.000  -0.1897   0.02854   0.02360  -0.0633   0.9864   0.0171
  -4.750  -0.1512   0.02025   0.01409  -0.0662   0.9840   0.0190
  -4.500  -0.1117   0.01750   0.01070  -0.0686   0.9801   0.0224
  -4.250  -0.0728   0.01718   0.01028  -0.0709   0.9747   0.0261
  -4.000  -0.0361   0.01611   0.00893  -0.0726   0.9694   0.0316
  -3.750   0.0014   0.01578   0.00836  -0.0744   0.9639   0.0384
  -3.500   0.0362   0.01523   0.00781  -0.0759   0.9567   0.0444
  -3.250   0.0714   0.01468   0.00706  -0.0773   0.9506   0.0503
  -3.000   0.1034   0.01397   0.00633  -0.0782   0.9435   0.0542
  -2.750   0.1384   0.01340   0.00569  -0.0796   0.9380   0.0572
  -2.500   0.1682   0.01295   0.00516  -0.0798   0.9286   0.0602
  -2.250   0.1995   0.01248   0.00464  -0.0804   0.9187   0.0614
  -2.000   0.2329   0.01198   0.00413  -0.0814   0.9080   0.0636
  -1.750   0.2659   0.01160   0.00374  -0.0823   0.8943   0.0667
  -1.500   0.2989   0.01130   0.00342  -0.0831   0.8771   0.0704
  -1.250   0.3340   0.01103   0.00313  -0.0844   0.8558   0.0759
  -1.000   0.3695   0.01081   0.00287  -0.0856   0.8259   0.0901
  -0.750   0.4026   0.01069   0.00258  -0.0863   0.7827   0.1108
  -0.500   0.4310   0.01069   0.00236  -0.0861   0.7289   0.1290
   0.000   0.4802   0.01027   0.00233  -0.0849   0.6395   0.4339
   0.250   0.5021   0.00917   0.00238  -0.0829   0.6059   1.0000
   0.500   0.5274   0.00943   0.00241  -0.0823   0.5726   1.0000
   0.750   0.5525   0.00970   0.00245  -0.0817   0.5374   1.0000
   1.000   0.5773   0.00999   0.00252  -0.0810   0.5017   1.0000
   1.250   0.6023   0.01029   0.00260  -0.0805   0.4714   1.0000
   1.500   0.6276   0.01058   0.00270  -0.0800   0.4464   1.0000
   1.750   0.6529   0.01087   0.00284  -0.0796   0.4244   1.0000
   2.000   0.6784   0.01116   0.00299  -0.0792   0.4042   1.0000
   2.250   0.7041   0.01143   0.00314  -0.0788   0.3882   1.0000
   2.500   0.7301   0.01167   0.00333  -0.0785   0.3756   1.0000
   2.750   0.7563   0.01190   0.00352  -0.0783   0.3655   1.0000
   3.000   0.7823   0.01215   0.00372  -0.0780   0.3563   1.0000
   3.250   0.8087   0.01236   0.00393  -0.0778   0.3473   1.0000
   3.500   0.8346   0.01261   0.00417  -0.0775   0.3383   1.0000
   3.750   0.8607   0.01285   0.00441  -0.0772   0.3286   1.0000
   4.000   0.8867   0.01309   0.00467  -0.0770   0.3189   1.0000
   4.250   0.9124   0.01336   0.00496  -0.0766   0.3092   1.0000
   4.500   0.9381   0.01361   0.00524  -0.0763   0.2980   1.0000
   4.750   0.9638   0.01387   0.00553  -0.0760   0.2856   1.0000
   5.000   0.9893   0.01414   0.00584  -0.0757   0.2732   1.0000
   5.250   1.0147   0.01442   0.00619  -0.0754   0.2608   1.0000
   5.500   1.0398   0.01472   0.00654  -0.0750   0.2461   1.0000
   5.750   1.0637   0.01513   0.00689  -0.0745   0.2192   1.0000
   6.000   1.0852   0.01582   0.00734  -0.0737   0.1819   1.0000
   6.250   1.1071   0.01649   0.00794  -0.0730   0.1579   1.0000
   6.500   1.1299   0.01707   0.00850  -0.0724   0.1357   1.0000
   6.750   1.1490   0.01811   0.00922  -0.0714   0.0871   1.0000
   7.000   1.1649   0.01957   0.01035  -0.0699   0.0318   1.0000
   7.250   1.1826   0.02078   0.01156  -0.0684   0.0200   1.0000
   7.500   1.2015   0.02182   0.01275  -0.0670   0.0165   1.0000
   7.750   1.2190   0.02299   0.01415  -0.0654   0.0145   1.0000
   8.000   1.2377   0.02389   0.01528  -0.0641   0.0132   1.0000
   8.250   1.2543   0.02496   0.01653  -0.0625   0.0120   1.0000
   8.500   1.2685   0.02620   0.01794  -0.0607   0.0112   1.0000
   8.750   1.2803   0.02757   0.01947  -0.0585   0.0107   1.0000
   9.000   1.2890   0.02911   0.02116  -0.0560   0.0102   1.0000
   9.250   1.2934   0.03088   0.02307  -0.0530   0.0098   1.0000
   9.500   1.2900   0.03303   0.02534  -0.0490   0.0093   1.0000
   9.750   1.2933   0.03476   0.02720  -0.0461   0.0090   1.0000
  10.000   1.2997   0.03624   0.02884  -0.0437   0.0085   1.0000
  10.250   1.3034   0.03803   0.03079  -0.0413   0.0081   1.0000
  10.500   1.3051   0.04015   0.03305  -0.0390   0.0079   1.0000
  10.750   1.3059   0.04246   0.03552  -0.0370   0.0077   1.0000
  11.000   1.3063   0.04494   0.03816  -0.0353   0.0075   1.0000
  11.250   1.3057   0.04765   0.04103  -0.0338   0.0074   1.0000
  11.500   1.3043   0.05058   0.04418  -0.0327   0.0072   1.0000
  11.750   1.3016   0.05378   0.04756  -0.0321   0.0071   1.0000
  12.000   1.2975   0.05732   0.05130  -0.0319   0.0070   1.0000
  12.250   1.2920   0.06121   0.05537  -0.0321   0.0069   1.0000
  12.500   1.2853   0.06545   0.05981  -0.0329   0.0069   1.0000
  12.750   1.2773   0.07007   0.06462  -0.0341   0.0068   1.0000
  13.000   1.2678   0.07510   0.06984  -0.0358   0.0068   1.0000
  13.250   1.2572   0.08053   0.07547  -0.0380   0.0068   1.0000
  13.500   1.2454   0.08632   0.08145  -0.0405   0.0068   1.0000
  13.750   1.2328   0.09252   0.08784  -0.0435   0.0067   1.0000
  14.000   1.2194   0.09911   0.09461  -0.0469   0.0067   1.0000
  14.250   1.2053   0.10607   0.10175  -0.0505   0.0068   1.0000
  14.500   1.1909   0.11339   0.10924  -0.0546   0.0068   1.0000
  14.750   1.1754   0.12128   0.11731  -0.0591   0.0068   1.0000
  15.000   1.1594   0.12970   0.12589  -0.0641   0.0069   1.0000
  15.250   1.1428   0.13871   0.13507  -0.0695   0.0070   1.0000
  15.500   1.1260   0.14841   0.14493  -0.0754   0.0071   1.0000
  15.750   1.1089   0.15894   0.15560  -0.0818   0.0072   1.0000
  16.000   1.0910   0.17060   0.16732  -0.0887   0.0074   1.0000
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