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I.S.A. 571 (isa571-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: I.S.A. 571 (isa571-il)
Reynolds number: 500,000
Max Cl/Cd: 93.61 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-isa571-il-500000.txt
Download as CSV file: xf-isa571-il-500000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4119   0.09075   0.08856  -0.0195   1.0000   0.0192
  -8.250  -0.4242   0.08858   0.08645  -0.0190   1.0000   0.0194
  -8.000  -0.4257   0.08539   0.08330  -0.0208   1.0000   0.0195
  -7.750  -0.4246   0.08198   0.07990  -0.0226   1.0000   0.0196
  -7.500  -0.4217   0.07828   0.07622  -0.0247   1.0000   0.0196
  -7.250  -0.4167   0.07436   0.07228  -0.0268   1.0000   0.0197
  -7.000  -0.4214   0.06875   0.06668  -0.0278   1.0000   0.0202
  -6.750  -0.4147   0.06649   0.06441  -0.0271   1.0000   0.0206
  -6.500  -0.4059   0.06439   0.06231  -0.0267   1.0000   0.0213
  -6.250  -0.3942   0.06147   0.05936  -0.0279   1.0000   0.0223
  -6.000  -0.3547   0.05571   0.05347  -0.0364   0.9974   0.0242
  -5.750  -0.3006   0.04873   0.04617  -0.0465   0.9949   0.0261
  -5.500  -0.2713   0.03479   0.03175  -0.0544   0.9922   0.0206
  -5.250  -0.2323   0.03596   0.03289  -0.0561   0.9893   0.0260
  -5.000  -0.2013   0.01525   0.01003  -0.0607   0.9897   0.0205
  -4.750  -0.1626   0.01488   0.00963  -0.0631   0.9870   0.0222
  -4.500  -0.1226   0.01397   0.00852  -0.0655   0.9849   0.0246
  -4.250  -0.0830   0.01279   0.00711  -0.0679   0.9835   0.0276
  -4.000  -0.0507   0.01290   0.00727  -0.0688   0.9785   0.0308
  -3.750  -0.0136   0.01286   0.00714  -0.0705   0.9752   0.0346
  -3.500   0.0237   0.01182   0.00605  -0.0726   0.9731   0.0399
  -3.250   0.0633   0.01171   0.00590  -0.0750   0.9712   0.0449
  -3.000   0.0941   0.01075   0.00488  -0.0756   0.9663   0.0489
  -2.750   0.1300   0.01031   0.00444  -0.0773   0.9622   0.0533
  -2.500   0.1688   0.00987   0.00398  -0.0795   0.9590   0.0566
  -2.250   0.2012   0.00947   0.00355  -0.0802   0.9515   0.0581
  -2.000   0.2359   0.00879   0.00285  -0.0814   0.9439   0.0619
  -1.750   0.2657   0.00845   0.00250  -0.0816   0.9314   0.0649
  -1.500   0.2972   0.00816   0.00219  -0.0820   0.9165   0.0675
  -1.250   0.3278   0.00793   0.00191  -0.0823   0.8937   0.0704
  -1.000   0.3580   0.00776   0.00169  -0.0824   0.8591   0.0784
  -0.750   0.3849   0.00780   0.00156  -0.0817   0.8027   0.0973
  -0.500   0.4089   0.00798   0.00148  -0.0806   0.7350   0.1188
  -0.250   0.4332   0.00818   0.00146  -0.0797   0.6813   0.1380
   0.000   0.4580   0.00822   0.00150  -0.0792   0.6366   0.2127
   0.250   0.4701   0.00655   0.00169  -0.0760   0.5982   0.9308
   0.500   0.5033   0.00678   0.00168  -0.0771   0.5479   1.0000
   0.750   0.5283   0.00709   0.00173  -0.0765   0.4992   1.0000
   1.000   0.5538   0.00738   0.00179  -0.0761   0.4600   1.0000
   1.250   0.5798   0.00764   0.00188  -0.0757   0.4323   1.0000
   1.500   0.6061   0.00789   0.00197  -0.0754   0.4112   1.0000
   1.750   0.6327   0.00809   0.00208  -0.0752   0.3949   1.0000
   2.250   0.6865   0.00845   0.00230  -0.0749   0.3721   1.0000
   2.500   0.7134   0.00861   0.00242  -0.0747   0.3628   1.0000
   3.000   0.7673   0.00895   0.00270  -0.0744   0.3450   1.0000
   3.250   0.7941   0.00913   0.00284  -0.0743   0.3363   1.0000
   3.500   0.8209   0.00930   0.00299  -0.0741   0.3276   1.0000
   3.750   0.8478   0.00946   0.00317  -0.0740   0.3194   1.0000
   4.000   0.8744   0.00967   0.00334  -0.0738   0.3105   1.0000
   4.250   0.9013   0.00981   0.00351  -0.0737   0.3013   1.0000
   4.500   0.9279   0.01000   0.00368  -0.0735   0.2884   1.0000
   4.750   0.9541   0.01022   0.00387  -0.0733   0.2696   1.0000
   5.000   0.9801   0.01047   0.00406  -0.0731   0.2470   1.0000
   5.250   1.0052   0.01083   0.00429  -0.0728   0.2166   1.0000
   5.500   1.0296   0.01128   0.00460  -0.0724   0.1900   1.0000
   5.750   1.0538   0.01176   0.00499  -0.0719   0.1703   1.0000
   6.000   1.0784   0.01217   0.00536  -0.0715   0.1539   1.0000
   6.250   1.1026   0.01265   0.00575  -0.0711   0.1296   1.0000
   6.500   1.1231   0.01362   0.00637  -0.0702   0.0793   1.0000
   6.750   1.1409   0.01499   0.00742  -0.0687   0.0251   1.0000
   7.000   1.1628   0.01578   0.00829  -0.0678   0.0201   1.0000
   7.250   1.1850   0.01650   0.00913  -0.0669   0.0181   1.0000
   7.500   1.2069   0.01721   0.00995  -0.0659   0.0168   1.0000
   7.750   1.2276   0.01804   0.01087  -0.0649   0.0156   1.0000
   8.000   1.2465   0.01902   0.01196  -0.0635   0.0147   1.0000
   8.250   1.2602   0.02052   0.01360  -0.0614   0.0136   1.0000
   8.500   1.2737   0.02195   0.01516  -0.0593   0.0128   1.0000
   8.750   1.2915   0.02285   0.01618  -0.0579   0.0123   1.0000
   9.000   1.3066   0.02401   0.01744  -0.0560   0.0119   1.0000
   9.250   1.3201   0.02528   0.01882  -0.0540   0.0115   1.0000
   9.500   1.3324   0.02663   0.02028  -0.0519   0.0111   1.0000
   9.750   1.3435   0.02805   0.02180  -0.0496   0.0108   1.0000
  10.000   1.3528   0.02955   0.02342  -0.0472   0.0105   1.0000
  10.250   1.3590   0.03109   0.02507  -0.0443   0.0103   1.0000
  10.500   1.3641   0.03279   0.02689  -0.0414   0.0100   1.0000
  10.750   1.3682   0.03467   0.02888  -0.0387   0.0098   1.0000
  11.000   1.3712   0.03677   0.03109  -0.0361   0.0096   1.0000
  11.250   1.3727   0.03941   0.03384  -0.0336   0.0094   1.0000
  11.500   1.3712   0.04314   0.03775  -0.0312   0.0091   1.0000
  12.000   1.3549   0.04947   0.04454  -0.0267   0.0088   1.0000
  12.250   1.3476   0.05252   0.04779  -0.0254   0.0088   1.0000
  12.500   1.3383   0.05625   0.05171  -0.0248   0.0088   1.0000
  12.750   1.3274   0.06046   0.05612  -0.0250   0.0088   1.0000
  13.000   1.3155   0.06504   0.06089  -0.0261   0.0088   1.0000
  13.250   1.3011   0.07051   0.06655  -0.0277   0.0088   1.0000
  13.500   1.2842   0.07668   0.07290  -0.0298   0.0089   1.0000
  13.750   1.2773   0.08157   0.07790  -0.0307   0.0091   1.0000
  14.000   1.2629   0.08756   0.08405  -0.0339   0.0091   1.0000
  14.250   1.2497   0.09365   0.09029  -0.0375   0.0091   1.0000
  14.500   1.2371   0.10003   0.09681  -0.0415   0.0091   1.0000
  14.750   1.2226   0.10704   0.10396  -0.0459   0.0092   1.0000
  15.000   1.2100   0.11404   0.11110  -0.0504   0.0092   1.0000
  15.250   1.1954   0.12179   0.11898  -0.0554   0.0093   1.0000
  15.500   1.1817   0.12987   0.12721  -0.0608   0.0094   1.0000
  15.750   0.9280   0.12960   0.12730  -0.0438   0.0106   1.0000
  16.000   0.8881   0.14008   0.13796  -0.0498   0.0113   1.0000
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