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I.S.A. 571 (isa571-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: I.S.A. 571 (isa571-il)
Reynolds number: 1,000,000
Max Cl/Cd: 109.42 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-isa571-il-1000000.txt
Download as CSV file: xf-isa571-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4200   0.08998   0.08841  -0.0193   1.0000   0.0106
  -8.500  -0.4284   0.08746   0.08593  -0.0179   1.0000   0.0106
  -8.250  -0.4519   0.08335   0.08188  -0.0164   1.0000   0.0108
  -8.000  -0.4537   0.08075   0.07929  -0.0166   1.0000   0.0110
  -7.750  -0.4531   0.07825   0.07681  -0.0170   1.0000   0.0112
  -7.500  -0.4346   0.07480   0.07335  -0.0216   0.9989   0.0115
  -7.250  -0.4195   0.01965   0.01645  -0.0650   0.9930   0.0091
  -7.000  -0.3872   0.01677   0.01314  -0.0669   0.9910   0.0097
  -6.750  -0.3530   0.01502   0.01105  -0.0687   0.9891   0.0102
  -6.500  -0.3180   0.01399   0.00982  -0.0704   0.9876   0.0105
  -6.250  -0.2851   0.01170   0.00710  -0.0719   0.9865   0.0115
  -6.000  -0.2494   0.01107   0.00638  -0.0737   0.9853   0.0123
  -5.750  -0.2132   0.01052   0.00574  -0.0754   0.9844   0.0132
  -5.500  -0.1774   0.01002   0.00514  -0.0771   0.9836   0.0142
  -5.250  -0.1486   0.00937   0.00439  -0.0772   0.9801   0.0155
  -5.000  -0.1146   0.00900   0.00403  -0.0785   0.9773   0.0177
  -4.750  -0.0786   0.00873   0.00372  -0.0801   0.9754   0.0196
  -4.500  -0.0438   0.00839   0.00340  -0.0815   0.9738   0.0239
  -4.250  -0.0096   0.00821   0.00322  -0.0828   0.9720   0.0277
  -4.000   0.0216   0.00827   0.00334  -0.0833   0.9688   0.0313
  -3.750   0.0504   0.00834   0.00342  -0.0833   0.9632   0.0340
  -3.500   0.0815   0.00800   0.00304  -0.0839   0.9585   0.0364
  -3.250   0.1092   0.00776   0.00280  -0.0837   0.9496   0.0391
  -3.000   0.1387   0.00761   0.00265  -0.0838   0.9399   0.0416
  -2.750   0.1673   0.00743   0.00243  -0.0838   0.9273   0.0435
  -2.500   0.1955   0.00736   0.00231  -0.0836   0.9104   0.0451
  -2.250   0.2230   0.00731   0.00218  -0.0832   0.8827   0.0458
  -2.000   0.2484   0.00699   0.00161  -0.0824   0.8337   0.0488
  -1.750   0.2719   0.00714   0.00143  -0.0813   0.7591   0.0513
  -1.500   0.2964   0.00731   0.00133  -0.0805   0.6967   0.0528
  -1.250   0.3222   0.00744   0.00126  -0.0800   0.6526   0.0542
  -1.000   0.3484   0.00755   0.00119  -0.0796   0.6129   0.0557
  -0.750   0.3750   0.00767   0.00114  -0.0793   0.5737   0.0573
  -0.500   0.4014   0.00781   0.00110  -0.0790   0.5278   0.0605
  -0.250   0.4276   0.00795   0.00113  -0.0787   0.4786   0.0755
   0.000   0.4541   0.00811   0.00119  -0.0785   0.4408   0.1039
   0.250   0.4812   0.00825   0.00123  -0.0783   0.4147   0.1140
   0.500   0.5084   0.00835   0.00127  -0.0782   0.3956   0.1222
   0.750   0.5357   0.00842   0.00132  -0.0781   0.3796   0.1331
   1.000   0.5631   0.00819   0.00140  -0.0783   0.3652   0.2935
   1.250   0.5839   0.00663   0.00157  -0.0771   0.3545   0.9966
   1.500   0.6118   0.00674   0.00162  -0.0771   0.3453   1.0000
   1.750   0.6393   0.00687   0.00169  -0.0770   0.3369   1.0000
   2.000   0.6668   0.00698   0.00176  -0.0770   0.3286   1.0000
   2.250   0.6943   0.00710   0.00184  -0.0769   0.3210   1.0000
   2.500   0.7218   0.00723   0.00192  -0.0769   0.3130   1.0000
   2.750   0.7493   0.00735   0.00202  -0.0768   0.3062   1.0000
   3.000   0.7766   0.00748   0.00212  -0.0767   0.2983   1.0000
   3.250   0.8041   0.00760   0.00222  -0.0767   0.2908   1.0000
   3.500   0.8312   0.00775   0.00234  -0.0766   0.2817   1.0000
   3.750   0.8585   0.00788   0.00246  -0.0766   0.2718   1.0000
   4.000   0.8852   0.00809   0.00259  -0.0764   0.2539   1.0000
   4.250   0.9112   0.00838   0.00275  -0.0762   0.2257   1.0000
   4.500   0.9357   0.00887   0.00301  -0.0758   0.1839   1.0000
   4.750   0.9616   0.00917   0.00326  -0.0756   0.1693   1.0000
   5.000   0.9876   0.00945   0.00349  -0.0754   0.1586   1.0000
   5.250   1.0136   0.00972   0.00372  -0.0752   0.1465   1.0000
   5.500   1.0391   0.01005   0.00397  -0.0749   0.1277   1.0000
   5.750   1.0626   0.01067   0.00437  -0.0744   0.0893   1.0000
   6.000   1.0874   0.01108   0.00473  -0.0740   0.0763   1.0000
   6.250   1.1071   0.01222   0.00553  -0.0728   0.0224   1.0000
   6.500   1.1314   0.01271   0.00604  -0.0723   0.0164   1.0000
   6.750   1.1550   0.01329   0.00668  -0.0716   0.0135   1.0000
   7.000   1.1793   0.01375   0.00720  -0.0711   0.0126   1.0000
   7.250   1.2033   0.01421   0.00772  -0.0705   0.0117   1.0000
   7.500   1.2269   0.01472   0.00828  -0.0699   0.0108   1.0000
   7.750   1.2491   0.01536   0.00898  -0.0692   0.0098   1.0000
   8.000   1.2673   0.01652   0.01030  -0.0676   0.0089   1.0000
   8.250   1.2901   0.01702   0.01086  -0.0670   0.0086   1.0000
   8.500   1.3116   0.01766   0.01156  -0.0661   0.0082   1.0000
   8.750   1.3320   0.01838   0.01236  -0.0650   0.0078   1.0000
   9.000   1.3516   0.01915   0.01320  -0.0639   0.0075   1.0000
   9.250   1.3704   0.01994   0.01407  -0.0627   0.0071   1.0000
   9.500   1.3883   0.02079   0.01499  -0.0613   0.0068   1.0000
   9.750   1.4037   0.02181   0.01610  -0.0597   0.0065   1.0000
  10.000   1.4095   0.02365   0.01806  -0.0566   0.0062   1.0000
  10.250   1.4143   0.02547   0.02003  -0.0534   0.0059   1.0000
  10.500   1.4308   0.02612   0.02076  -0.0519   0.0057   1.0000
  10.750   1.4405   0.02711   0.02184  -0.0494   0.0056   1.0000
  11.000   1.4458   0.02833   0.02317  -0.0463   0.0054   1.0000
  11.250   1.4491   0.02976   0.02471  -0.0432   0.0053   1.0000
  11.500   1.4512   0.03134   0.02641  -0.0403   0.0052   1.0000
  11.750   1.4524   0.03309   0.02829  -0.0377   0.0051   1.0000
  12.000   1.4524   0.03505   0.03037  -0.0353   0.0050   1.0000
  12.250   1.4511   0.03728   0.03273  -0.0333   0.0049   1.0000
  12.500   1.4488   0.03980   0.03537  -0.0318   0.0048   1.0000
  12.750   1.4454   0.04266   0.03837  -0.0309   0.0047   1.0000
  13.000   1.4420   0.04580   0.04164  -0.0306   0.0047   1.0000
  13.250   1.4364   0.04954   0.04552  -0.0310   0.0046   1.0000
  13.500   1.4298   0.05371   0.04983  -0.0320   0.0046   1.0000
  13.750   1.4208   0.05852   0.05479  -0.0335   0.0045   1.0000
  14.000   1.4124   0.06344   0.05985  -0.0355   0.0045   1.0000
  14.250   1.4017   0.06888   0.06542  -0.0378   0.0045   1.0000
  14.500   1.3886   0.07484   0.07153  -0.0404   0.0044   1.0000
  14.750   1.3762   0.08088   0.07769  -0.0432   0.0044   1.0000
  15.000   1.3606   0.08752   0.08447  -0.0461   0.0044   1.0000
  15.250   1.3467   0.09405   0.09112  -0.0492   0.0044   1.0000
  15.500   1.3299   0.10113   0.09833  -0.0525   0.0044   1.0000
  15.750   1.3130   0.10848   0.10581  -0.0560   0.0044   1.0000
  16.000   1.2984   0.11558   0.11303  -0.0596   0.0044   1.0000
  16.250   1.2786   0.12385   0.12144  -0.0637   0.0044   1.0000
  16.500   1.2617   0.13191   0.12963  -0.0679   0.0044   1.0000
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