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I.S.A. 961 (isa961-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: I.S.A. 961 (isa961-il)
Reynolds number: 50,000
Max Cl/Cd: 39.48 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-isa961-il-50000-n5.txt
Download as CSV file: xf-isa961-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: I.S.A. 961                                      
  
 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  -0.3234   0.09949   0.09291  -0.0326   1.0000   0.0500
  -8.750  -0.3290   0.09694   0.09049  -0.0320   1.0000   0.0493
  -8.500  -0.3373   0.09462   0.08830  -0.0310   1.0000   0.0488
  -8.250  -0.3451   0.09216   0.08597  -0.0304   1.0000   0.0484
  -8.000  -0.3517   0.08955   0.08346  -0.0301   1.0000   0.0481
  -7.750  -0.3575   0.08686   0.08086  -0.0301   1.0000   0.0480
  -7.500  -0.3620   0.08401   0.07809  -0.0303   1.0000   0.0479
  -7.250  -0.3644   0.08099   0.07512  -0.0308   1.0000   0.0480
  -7.000  -0.3646   0.07775   0.07191  -0.0317   1.0000   0.0481
  -6.750  -0.3621   0.07424   0.06841  -0.0330   1.0000   0.0482
  -6.500  -0.3567   0.07043   0.06457  -0.0347   1.0000   0.0483
  -6.250  -0.3479   0.06625   0.06033  -0.0370   1.0000   0.0483
  -6.000  -0.3354   0.06172   0.05568  -0.0396   1.0000   0.0482
  -5.750  -0.3144   0.05661   0.05036  -0.0437   0.9986   0.0486
  -5.500  -0.2756   0.05010   0.04343  -0.0511   0.9934   0.0505
  -5.250  -0.2318   0.04144   0.03379  -0.0592   0.9891   0.0549
  -5.000  -0.1980   0.03990   0.03210  -0.0617   0.9832   0.0599
  -4.750  -0.1568   0.03492   0.02616  -0.0660   0.9789   0.0684
  -4.500  -0.1198   0.03292   0.02372  -0.0686   0.9734   0.0826
  -4.250  -0.0834   0.03209   0.02260  -0.0708   0.9669   0.1041
  -4.000  -0.0505   0.03207   0.02247  -0.0724   0.9590   0.1268
  -3.750  -0.0114   0.03098   0.02098  -0.0749   0.9530   0.1411
  -3.500   0.0241   0.02982   0.01926  -0.0765   0.9450   0.1488
  -3.250   0.0642   0.02909   0.01834  -0.0791   0.9383   0.1583
  -3.000   0.0985   0.02833   0.01726  -0.0803   0.9287   0.1649
  -2.750   0.1413   0.02757   0.01632  -0.0830   0.9220   0.1716
  -2.500   0.1759   0.02706   0.01554  -0.0841   0.9114   0.1800
  -2.250   0.2148   0.02659   0.01493  -0.0860   0.9028   0.1938
  -2.000   0.2541   0.02604   0.01434  -0.0880   0.8943   0.2084
  -1.750   0.2885   0.02559   0.01387  -0.0891   0.8844   0.2264
  -1.500   0.3295   0.02499   0.01333  -0.0913   0.8770   0.2563
  -1.250   0.3593   0.02457   0.01309  -0.0916   0.8652   0.2979
  -1.000   0.3902   0.02385   0.01284  -0.0923   0.8542   0.3899
  -0.750   0.4271   0.02223   0.01246  -0.0929   0.8443   1.0000
  -0.500   0.4613   0.02220   0.01214  -0.0935   0.8329   1.0000
  -0.250   0.4907   0.02223   0.01196  -0.0934   0.8190   1.0000
   0.000   0.5205   0.02219   0.01175  -0.0931   0.8045   1.0000
   0.250   0.5503   0.02209   0.01150  -0.0928   0.7891   1.0000
   0.500   0.5798   0.02197   0.01125  -0.0923   0.7733   1.0000
   0.750   0.6090   0.02185   0.01101  -0.0918   0.7572   1.0000
   1.000   0.6350   0.02186   0.01093  -0.0909   0.7391   1.0000
   1.250   0.6615   0.02185   0.01084  -0.0901   0.7208   1.0000
   1.500   0.6887   0.02184   0.01075  -0.0893   0.7023   1.0000
   1.750   0.7164   0.02181   0.01063  -0.0886   0.6836   1.0000
   2.000   0.7429   0.02186   0.01061  -0.0878   0.6637   1.0000
   2.250   0.7680   0.02198   0.01066  -0.0868   0.6418   1.0000
   2.500   0.7947   0.02205   0.01062  -0.0860   0.6206   1.0000
   2.750   0.8184   0.02228   0.01080  -0.0849   0.5969   1.0000
   3.000   0.8437   0.02247   0.01087  -0.0840   0.5748   1.0000
   3.250   0.8667   0.02279   0.01113  -0.0829   0.5513   1.0000
   3.500   0.8909   0.02311   0.01137  -0.0820   0.5304   1.0000
   3.750   0.9143   0.02352   0.01173  -0.0811   0.5106   1.0000
   4.000   0.9377   0.02397   0.01215  -0.0803   0.4926   1.0000
   4.250   0.9614   0.02446   0.01261  -0.0796   0.4765   1.0000
   4.500   0.9849   0.02498   0.01315  -0.0789   0.4612   1.0000
   4.750   1.0079   0.02553   0.01369  -0.0781   0.4456   1.0000
   5.000   1.0301   0.02610   0.01426  -0.0772   0.4296   1.0000
   5.250   1.0518   0.02670   0.01490  -0.0763   0.4139   1.0000
   5.500   1.0727   0.02731   0.01553  -0.0753   0.3980   1.0000
   5.750   1.0930   0.02795   0.01621  -0.0742   0.3826   1.0000
   6.000   1.1128   0.02860   0.01692  -0.0731   0.3678   1.0000
   6.250   1.1324   0.02928   0.01768  -0.0720   0.3539   1.0000
   6.500   1.1517   0.02998   0.01850  -0.0709   0.3409   1.0000
   6.750   1.1708   0.03069   0.01931  -0.0697   0.3289   1.0000
   7.000   1.1898   0.03143   0.02017  -0.0686   0.3177   1.0000
   7.250   1.2078   0.03224   0.02116  -0.0674   0.3063   1.0000
   7.500   1.2256   0.03308   0.02216  -0.0662   0.2957   1.0000
   7.750   1.2432   0.03391   0.02314  -0.0649   0.2859   1.0000
   8.000   1.2587   0.03485   0.02430  -0.0635   0.2748   1.0000
   8.250   1.2734   0.03584   0.02547  -0.0619   0.2640   1.0000
   8.500   1.2877   0.03682   0.02657  -0.0603   0.2542   1.0000
   8.750   1.3005   0.03793   0.02790  -0.0587   0.2441   1.0000
   9.000   1.3126   0.03911   0.02929  -0.0569   0.2351   1.0000
   9.250   1.3199   0.04023   0.03049  -0.0545   0.2249   1.0000
   9.500   1.3213   0.04162   0.03206  -0.0518   0.2123   1.0000
   9.750   1.3209   0.04323   0.03384  -0.0494   0.1989   1.0000
  10.000   1.3201   0.04504   0.03581  -0.0473   0.1854   1.0000
  10.250   1.3209   0.04698   0.03802  -0.0456   0.1739   1.0000
  10.500   1.3211   0.04911   0.04031  -0.0441   0.1634   1.0000
  10.750   1.3191   0.05151   0.04281  -0.0429   0.1535   1.0000
  11.000   1.3153   0.05425   0.04562  -0.0420   0.1444   1.0000
  11.250   1.3101   0.05737   0.04881  -0.0413   0.1359   1.0000
  11.500   1.3010   0.06103   0.05241  -0.0410   0.1279   1.0000
  11.750   1.2917   0.06510   0.05662  -0.0411   0.1192   1.0000
  12.000   1.2812   0.06947   0.06105  -0.0415   0.1120   1.0000
  12.250   1.2726   0.07399   0.06583  -0.0423   0.1047   1.0000
  12.500   1.2622   0.07878   0.07077  -0.0432   0.0989   1.0000
  12.750   1.2528   0.08402   0.07647  -0.0446   0.0903   1.0000
  13.000   1.2411   0.08986   0.08270  -0.0464   0.0806   1.0000
  13.250   1.2283   0.09572   0.08867  -0.0486   0.0730   1.0000
  13.500   1.2151   0.10164   0.09451  -0.0509   0.0678   1.0000
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