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I.S.A. 571 (isa571-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: I.S.A. 571 (isa571-il)
Reynolds number: 500,000
Max Cl/Cd: 89.07 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-isa571-il-500000-n5.txt
Download as CSV file: xf-isa571-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3972   0.10509   0.10278  -0.0184   1.0000   0.0080
  -9.500  -0.3958   0.10184   0.09955  -0.0189   1.0000   0.0075
  -8.500  -0.4172   0.08693   0.08480  -0.0192   1.0000   0.0060
  -8.250  -0.4285   0.08474   0.08265  -0.0172   1.0000   0.0059
  -8.000  -0.4339   0.08164   0.07960  -0.0175   1.0000   0.0059
  -7.750  -0.4230   0.07623   0.07419  -0.0236   0.9982   0.0059
  -7.500  -0.3989   0.06857   0.06649  -0.0346   0.9953   0.0060
  -7.000  -0.3419   0.02167   0.01781  -0.0750   0.9856   0.0065
  -6.750  -0.3122   0.01968   0.01557  -0.0763   0.9827   0.0069
  -6.500  -0.2791   0.01746   0.01299  -0.0781   0.9803   0.0074
  -6.250  -0.2438   0.01551   0.01065  -0.0801   0.9783   0.0079
  -6.000  -0.2101   0.01413   0.00898  -0.0816   0.9756   0.0084
  -5.750  -0.1790   0.01318   0.00780  -0.0823   0.9715   0.0089
  -5.500  -0.1447   0.01209   0.00648  -0.0837   0.9689   0.0098
  -5.250  -0.1097   0.01142   0.00570  -0.0853   0.9667   0.0112
  -5.000  -0.0814   0.01093   0.00513  -0.0853   0.9612   0.0128
  -4.750  -0.0499   0.01038   0.00446  -0.0859   0.9565   0.0145
  -4.500  -0.0185   0.00993   0.00399  -0.0866   0.9511   0.0191
  -4.250   0.0111   0.00980   0.00390  -0.0868   0.9430   0.0261
  -4.000   0.0422   0.00968   0.00373  -0.0873   0.9356   0.0311
  -3.750   0.0734   0.00965   0.00369  -0.0879   0.9268   0.0345
  -3.500   0.1039   0.00960   0.00357  -0.0882   0.9157   0.0376
  -3.250   0.1345   0.00936   0.00327  -0.0887   0.9026   0.0399
  -3.000   0.1648   0.00915   0.00302  -0.0891   0.8847   0.0428
  -2.750   0.1939   0.00893   0.00268  -0.0892   0.8587   0.0440
  -2.500   0.2212   0.00884   0.00240  -0.0888   0.8158   0.0457
  -2.000   0.2697   0.00907   0.00199  -0.0868   0.6921   0.0477
  -1.750   0.2948   0.00920   0.00188  -0.0861   0.6467   0.0486
  -1.500   0.3208   0.00927   0.00178  -0.0857   0.6136   0.0494
  -1.250   0.3474   0.00927   0.00164  -0.0854   0.5864   0.0515
  -1.000   0.3740   0.00931   0.00156  -0.0852   0.5577   0.0538
  -0.750   0.4004   0.00939   0.00150  -0.0849   0.5245   0.0562
  -0.500   0.4266   0.00953   0.00147  -0.0845   0.4860   0.0590
  -0.250   0.4525   0.00971   0.00148  -0.0842   0.4466   0.0640
   0.000   0.4786   0.00987   0.00157  -0.0839   0.4128   0.0916
   0.250   0.5051   0.01003   0.00163  -0.0837   0.3879   0.1043
   0.500   0.5321   0.01013   0.00167  -0.0836   0.3728   0.1125
   0.750   0.5594   0.01019   0.00171  -0.0835   0.3626   0.1208
   1.250   0.6137   0.01031   0.00185  -0.0834   0.3431   0.1526
   1.500   0.6343   0.00850   0.00205  -0.0822   0.3330   1.0000
   1.750   0.6613   0.00866   0.00214  -0.0821   0.3228   1.0000
   2.000   0.6883   0.00881   0.00223  -0.0820   0.3136   1.0000
   2.250   0.7155   0.00895   0.00232  -0.0819   0.3059   1.0000
   2.500   0.7425   0.00910   0.00244  -0.0818   0.2984   1.0000
   2.750   0.7696   0.00924   0.00256  -0.0817   0.2914   1.0000
   3.000   0.7965   0.00941   0.00269  -0.0816   0.2832   1.0000
   3.250   0.8235   0.00955   0.00283  -0.0815   0.2750   1.0000
   3.500   0.8502   0.00973   0.00298  -0.0813   0.2655   1.0000
   3.750   0.8769   0.00992   0.00314  -0.0812   0.2541   1.0000
   4.000   0.9032   0.01014   0.00331  -0.0810   0.2382   1.0000
   4.250   0.9287   0.01046   0.00353  -0.0807   0.2123   1.0000
   4.500   0.9543   0.01077   0.00377  -0.0804   0.1932   1.0000
   4.750   0.9794   0.01114   0.00406  -0.0801   0.1762   1.0000
   5.000   1.0044   0.01151   0.00438  -0.0798   0.1612   1.0000
   5.250   1.0295   0.01187   0.00470  -0.0795   0.1470   1.0000
   5.500   1.0539   0.01232   0.00504  -0.0791   0.1227   1.0000
   5.750   1.0763   0.01302   0.00551  -0.0784   0.0864   1.0000
   6.000   1.1004   0.01349   0.00596  -0.0779   0.0750   1.0000
   6.250   1.1199   0.01457   0.00677  -0.0768   0.0239   1.0000
   6.500   1.1430   0.01516   0.00737  -0.0761   0.0144   1.0000
   6.750   1.1666   0.01565   0.00793  -0.0755   0.0119   1.0000
   7.000   1.1889   0.01631   0.00868  -0.0747   0.0094   1.0000
   7.250   1.2119   0.01685   0.00930  -0.0740   0.0086   1.0000
   7.500   1.2343   0.01744   0.00998  -0.0732   0.0078   1.0000
   7.750   1.2559   0.01809   0.01075  -0.0724   0.0071   1.0000
   8.000   1.2758   0.01891   0.01163  -0.0713   0.0064   1.0000
   8.250   1.2953   0.01973   0.01256  -0.0702   0.0059   1.0000
   8.500   1.3149   0.02049   0.01343  -0.0690   0.0054   1.0000
   8.750   1.3330   0.02136   0.01440  -0.0677   0.0051   1.0000
   9.000   1.3501   0.02227   0.01541  -0.0662   0.0048   1.0000
   9.250   1.3661   0.02323   0.01646  -0.0647   0.0046   1.0000
   9.500   1.3803   0.02429   0.01761  -0.0628   0.0043   1.0000
   9.750   1.3900   0.02563   0.01907  -0.0604   0.0042   1.0000
  10.000   1.3945   0.02723   0.02080  -0.0572   0.0040   1.0000
  10.250   1.4001   0.02846   0.02221  -0.0541   0.0039   1.0000
  10.500   1.4047   0.02982   0.02370  -0.0511   0.0038   1.0000
  10.750   1.4082   0.03130   0.02533  -0.0482   0.0037   1.0000
  11.000   1.4109   0.03292   0.02708  -0.0455   0.0035   1.0000
  11.250   1.4130   0.03466   0.02896  -0.0432   0.0034   1.0000
  11.500   1.4139   0.03664   0.03108  -0.0411   0.0032   1.0000
  11.750   1.4146   0.03875   0.03333  -0.0395   0.0031   1.0000
  12.000   1.4131   0.04129   0.03600  -0.0382   0.0030   1.0000
  12.250   1.4099   0.04425   0.03911  -0.0375   0.0030   1.0000
  12.500   1.4058   0.04762   0.04263  -0.0374   0.0029   1.0000
  12.750   1.4010   0.05140   0.04655  -0.0380   0.0029   1.0000
  13.000   1.3945   0.05572   0.05103  -0.0391   0.0028   1.0000
  13.250   1.3870   0.06041   0.05586  -0.0407   0.0028   1.0000
  13.500   1.3781   0.06552   0.06112  -0.0426   0.0028   1.0000
  13.750   1.3677   0.07100   0.06676  -0.0448   0.0028   1.0000
  14.000   1.3560   0.07680   0.07269  -0.0472   0.0027   1.0000
  14.250   1.3441   0.08277   0.07880  -0.0497   0.0027   1.0000
  14.500   1.3311   0.08898   0.08515  -0.0523   0.0027   1.0000
  14.750   1.3175   0.09535   0.09165  -0.0550   0.0027   1.0000
  15.000   1.3039   0.10187   0.09830  -0.0579   0.0027   1.0000
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