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I.S.A. 571 (isa571-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: I.S.A. 571 (isa571-il)
Reynolds number: 50,000
Max Cl/Cd: 39.36 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-isa571-il-50000-n5.txt
Download as CSV file: xf-isa571-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3903   0.10930   0.10240  -0.0190   1.0000   0.0813
  -8.750  -0.3933   0.10719   0.10034  -0.0203   1.0000   0.0839
  -8.500  -0.4016   0.10566   0.09899  -0.0217   1.0000   0.0850
  -8.000  -0.4014   0.09948   0.09297  -0.0239   1.0000   0.0863
  -7.750  -0.3925   0.09538   0.08889  -0.0215   1.0000   0.0886
  -7.500  -0.3886   0.09231   0.08589  -0.0218   1.0000   0.0915
  -7.250  -0.3869   0.08964   0.08328  -0.0246   1.0000   0.0957
  -7.000  -0.3834   0.08724   0.08088  -0.0319   1.0000   0.0977
  -6.750  -0.3771   0.08272   0.07647  -0.0278   1.0000   0.1004
  -6.500  -0.3696   0.07947   0.07325  -0.0274   1.0000   0.1048
  -6.000  -0.3318   0.06795   0.06129  -0.0407   1.0000   0.0617
  -5.750  -0.3238   0.06446   0.05791  -0.0384   1.0000   0.0592
  -5.500  -0.3080   0.06038   0.05374  -0.0399   1.0000   0.0566
  -5.250  -0.2880   0.05595   0.04913  -0.0424   1.0000   0.0544
  -5.000  -0.2659   0.05177   0.04472  -0.0447   1.0000   0.0541
  -4.750  -0.2427   0.04811   0.04079  -0.0465   1.0000   0.0568
  -4.500  -0.2163   0.04419   0.03645  -0.0485   1.0000   0.0588
  -4.250  -0.1886   0.04035   0.03214  -0.0501   1.0000   0.0594
  -4.000  -0.1574   0.03652   0.02757  -0.0517   1.0000   0.0620
  -3.750  -0.1359   0.03489   0.02594  -0.0517   1.0000   0.0685
  -3.500  -0.1053   0.03202   0.02241  -0.0525   1.0000   0.0721
  -3.250  -0.0793   0.03043   0.02055  -0.0527   1.0000   0.0801
  -3.000  -0.0498   0.02859   0.01809  -0.0529   1.0000   0.0865
  -2.750  -0.0234   0.02722   0.01652  -0.0529   1.0000   0.0912
  -2.500   0.0029   0.02630   0.01530  -0.0528   1.0000   0.1012
  -2.250   0.0291   0.02534   0.01412  -0.0525   1.0000   0.1057
  -2.000   0.0555   0.02457   0.01304  -0.0521   1.0000   0.1097
  -1.750   0.0817   0.02391   0.01222  -0.0518   1.0000   0.1140
  -1.500   0.1149   0.02344   0.01160  -0.0531   0.9963   0.1241
  -1.250   0.1617   0.02280   0.01087  -0.0570   0.9851   0.1378
  -1.000   0.2059   0.02219   0.01022  -0.0604   0.9722   0.1534
  -0.750   0.2491   0.02149   0.00970  -0.0637   0.9584   0.1922
  -0.500   0.2818   0.01879   0.00929  -0.0643   0.9438   1.0000
  -0.250   0.3232   0.01882   0.00892  -0.0667   0.9266   1.0000
   0.000   0.3614   0.01880   0.00864  -0.0685   0.9073   1.0000
   0.250   0.3988   0.01873   0.00840  -0.0700   0.8865   1.0000
   0.500   0.4365   0.01862   0.00815  -0.0715   0.8653   1.0000
   0.750   0.4726   0.01850   0.00791  -0.0725   0.8409   1.0000
   1.000   0.5081   0.01839   0.00771  -0.0734   0.8135   1.0000
   1.250   0.5448   0.01828   0.00750  -0.0744   0.7843   1.0000
   1.500   0.5817   0.01820   0.00727  -0.0753   0.7527   1.0000
   1.750   0.6156   0.01825   0.00716  -0.0757   0.7184   1.0000
   2.000   0.6473   0.01843   0.00717  -0.0758   0.6845   1.0000
   2.250   0.6764   0.01874   0.00728  -0.0755   0.6524   1.0000
   2.500   0.7036   0.01914   0.00751  -0.0749   0.6229   1.0000
   2.750   0.7297   0.01958   0.00785  -0.0744   0.5948   1.0000
   3.000   0.7554   0.02006   0.00821  -0.0738   0.5679   1.0000
   3.250   0.7805   0.02053   0.00857  -0.0731   0.5421   1.0000
   3.500   0.8053   0.02101   0.00899  -0.0724   0.5181   1.0000
   3.750   0.8301   0.02150   0.00944  -0.0718   0.4962   1.0000
   4.000   0.8556   0.02201   0.00995  -0.0713   0.4783   1.0000
   4.250   0.8814   0.02255   0.01051  -0.0709   0.4620   1.0000
   4.500   0.9073   0.02312   0.01116  -0.0706   0.4467   1.0000
   4.750   0.9331   0.02372   0.01183  -0.0703   0.4320   1.0000
   5.000   0.9584   0.02435   0.01254  -0.0699   0.4171   1.0000
   5.250   0.9830   0.02500   0.01327  -0.0693   0.4015   1.0000
   5.500   1.0072   0.02567   0.01408  -0.0687   0.3857   1.0000
   5.750   1.0307   0.02637   0.01490  -0.0680   0.3697   1.0000
   6.000   1.0530   0.02707   0.01578  -0.0672   0.3522   1.0000
   6.250   1.0747   0.02777   0.01666  -0.0662   0.3347   1.0000
   6.500   1.0964   0.02851   0.01765  -0.0653   0.3185   1.0000
   6.750   1.1182   0.02930   0.01866  -0.0643   0.3036   1.0000
   7.000   1.1403   0.03017   0.01978  -0.0635   0.2905   1.0000
   7.250   1.1620   0.03107   0.02094  -0.0625   0.2779   1.0000
   7.500   1.1781   0.03157   0.02168  -0.0608   0.2575   1.0000
   7.750   1.1898   0.03186   0.02211  -0.0585   0.2299   1.0000
   8.000   1.2014   0.03242   0.02275  -0.0564   0.2008   1.0000
   8.250   1.2113   0.03346   0.02373  -0.0543   0.1703   1.0000
   8.500   1.2207   0.03497   0.02540  -0.0523   0.1229   1.0000
   8.750   1.2222   0.03742   0.02747  -0.0498   0.0802   1.0000
   9.000   1.2231   0.04007   0.03012  -0.0471   0.0579   1.0000
   9.250   1.2213   0.04263   0.03269  -0.0443   0.0483   1.0000
   9.500   1.2171   0.04525   0.03538  -0.0416   0.0438   1.0000
   9.750   1.2098   0.04823   0.03844  -0.0392   0.0415   1.0000
  10.000   1.2035   0.05132   0.04171  -0.0374   0.0399   1.0000
  10.250   1.1964   0.05473   0.04533  -0.0363   0.0385   1.0000
  10.500   1.1886   0.05851   0.04931  -0.0359   0.0372   1.0000
  10.750   1.1805   0.06267   0.05365  -0.0362   0.0360   1.0000
  11.000   1.1723   0.06714   0.05828  -0.0370   0.0350   1.0000
  11.250   1.1638   0.07188   0.06314  -0.0382   0.0340   1.0000
  11.500   1.1554   0.07668   0.06805  -0.0394   0.0332   1.0000
  11.750   1.1501   0.08122   0.07277  -0.0404   0.0323   1.0000
  12.000   1.1451   0.08584   0.07763  -0.0415   0.0315   1.0000
  12.250   1.1398   0.09063   0.08265  -0.0427   0.0309   1.0000
  12.500   1.1341   0.09560   0.08784  -0.0441   0.0304   1.0000
  12.750   1.1277   0.10084   0.09330  -0.0457   0.0300   1.0000
  13.000   1.1200   0.10653   0.09921  -0.0478   0.0298   1.0000
  13.250   1.1108   0.11271   0.10560  -0.0504   0.0297   1.0000
  13.500   1.1000   0.11951   0.11261  -0.0535   0.0297   1.0000
  13.750   1.0875   0.12712   0.12041  -0.0574   0.0299   1.0000
  14.000   1.0734   0.13557   0.12904  -0.0620   0.0302   1.0000
  14.250   1.0583   0.14488   0.13848  -0.0671   0.0306   1.0000
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