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I.S.A. 962 (isa962-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: I.S.A. 962 (isa962-il)
Reynolds number: 100,000
Max Cl/Cd: 56.12 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-isa962-il-100000-n5.txt
Download as CSV file: xf-isa962-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: I.S.A. 962                                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3069   0.09515   0.09023  -0.0287   1.0000   0.0712
  -8.500  -0.3223   0.09411   0.08931  -0.0264   1.0000   0.0722
  -8.250  -0.3425   0.09334   0.08865  -0.0243   1.0000   0.0731
  -8.000  -0.3178   0.08789   0.08309  -0.0441   0.9869   0.0745
  -7.750  -0.3003   0.08360   0.07885  -0.0424   0.9837   0.0752
  -7.500  -0.2817   0.08043   0.07570  -0.0417   0.9784   0.0766
  -7.250  -0.2574   0.07710   0.07235  -0.0450   0.9728   0.0797
  -6.750  -0.1958   0.06721   0.06218  -0.0663   0.9545   0.0866
  -6.250  -0.1317   0.05146   0.04581  -0.0812   0.9412   0.0552
  -6.000  -0.1048   0.04893   0.04325  -0.0831   0.9350   0.0541
  -5.750  -0.0714   0.04487   0.03897  -0.0874   0.9300   0.0537
  -5.500  -0.0425   0.04101   0.03482  -0.0904   0.9217   0.0538
  -5.250  -0.0089   0.03749   0.03101  -0.0936   0.9166   0.0531
  -5.000   0.0199   0.03436   0.02756  -0.0953   0.9087   0.0521
  -4.750   0.0523   0.03120   0.02397  -0.0973   0.9026   0.0514
  -4.500   0.0828   0.02865   0.02099  -0.0984   0.8956   0.0510
  -4.250   0.1128   0.02659   0.01852  -0.0991   0.8880   0.0509
  -4.000   0.1435   0.02491   0.01648  -0.0996   0.8806   0.0514
  -3.750   0.1726   0.02366   0.01489  -0.0996   0.8714   0.0529
  -3.500   0.2013   0.02255   0.01346  -0.0995   0.8620   0.0542
  -3.250   0.2313   0.02151   0.01215  -0.0994   0.8531   0.0547
  -3.000   0.2577   0.02066   0.01117  -0.0988   0.8419   0.0553
  -2.750   0.2857   0.01987   0.01032  -0.0984   0.8323   0.0562
  -2.500   0.3131   0.01922   0.00964  -0.0980   0.8221   0.0573
  -2.250   0.3394   0.01870   0.00909  -0.0973   0.8109   0.0587
  -2.000   0.3671   0.01820   0.00855  -0.0968   0.8009   0.0611
  -1.750   0.3940   0.01778   0.00807  -0.0962   0.7896   0.0645
  -1.500   0.4203   0.01740   0.00773  -0.0956   0.7771   0.0682
  -1.250   0.4476   0.01705   0.00734  -0.0950   0.7659   0.0723
  -1.000   0.4755   0.01674   0.00702  -0.0946   0.7559   0.0783
  -0.750   0.5024   0.01650   0.00681  -0.0941   0.7447   0.0916
  -0.500   0.5303   0.01614   0.00656  -0.0937   0.7351   0.1342
  -0.250   0.5578   0.01568   0.00652  -0.0936   0.7243   0.2595
   0.250   0.6188   0.01403   0.00632  -0.0938   0.6989   1.0000
   0.750   0.6715   0.01422   0.00616  -0.0924   0.6680   1.0000
   1.000   0.6976   0.01435   0.00613  -0.0917   0.6522   1.0000
   1.250   0.7236   0.01449   0.00614  -0.0911   0.6358   1.0000
   1.500   0.7491   0.01465   0.00618  -0.0904   0.6179   1.0000
   1.750   0.7744   0.01483   0.00624  -0.0896   0.5978   1.0000
   2.000   0.7995   0.01502   0.00632  -0.0888   0.5772   1.0000
   2.250   0.8245   0.01524   0.00641  -0.0881   0.5569   1.0000
   2.500   0.8491   0.01548   0.00653  -0.0873   0.5338   1.0000
   2.750   0.8731   0.01575   0.00667  -0.0864   0.5076   1.0000
   3.000   0.8969   0.01606   0.00684  -0.0856   0.4810   1.0000
   3.250   0.9201   0.01642   0.00703  -0.0847   0.4550   1.0000
   3.500   0.9434   0.01681   0.00729  -0.0838   0.4302   1.0000
   3.750   0.9662   0.01724   0.00758  -0.0829   0.4084   1.0000
   4.000   0.9888   0.01770   0.00791  -0.0820   0.3885   1.0000
   4.250   1.0112   0.01819   0.00829  -0.0811   0.3699   1.0000
   4.500   1.0333   0.01871   0.00870  -0.0802   0.3526   1.0000
   4.750   1.0551   0.01924   0.00915  -0.0793   0.3362   1.0000
   5.000   1.0767   0.01980   0.00964  -0.0784   0.3203   1.0000
   5.250   1.0979   0.02036   0.01015  -0.0774   0.3041   1.0000
   5.500   1.1189   0.02092   0.01067  -0.0765   0.2871   1.0000
   5.750   1.1397   0.02148   0.01122  -0.0755   0.2696   1.0000
   6.000   1.1601   0.02205   0.01178  -0.0744   0.2520   1.0000
   6.250   1.1799   0.02265   0.01235  -0.0733   0.2355   1.0000
   6.500   1.1990   0.02330   0.01296  -0.0722   0.2214   1.0000
   6.750   1.2173   0.02400   0.01361  -0.0709   0.2099   1.0000
   7.000   1.2351   0.02474   0.01430  -0.0696   0.2000   1.0000
   7.250   1.2530   0.02550   0.01505  -0.0684   0.1919   1.0000
   7.500   1.2693   0.02633   0.01584  -0.0669   0.1852   1.0000
   7.750   1.2864   0.02716   0.01670  -0.0656   0.1793   1.0000
   8.000   1.3029   0.02801   0.01758  -0.0642   0.1734   1.0000
   8.250   1.3174   0.02901   0.01852  -0.0626   0.1686   1.0000
   8.500   1.3338   0.02986   0.01947  -0.0612   0.1638   1.0000
   8.750   1.3489   0.03076   0.02048  -0.0597   0.1594   1.0000
   9.000   1.3632   0.03176   0.02149  -0.0581   0.1554   1.0000
   9.250   1.3784   0.03287   0.02256  -0.0568   0.1517   1.0000
   9.500   1.3931   0.03383   0.02371  -0.0553   0.1478   1.0000
   9.750   1.4070   0.03487   0.02487  -0.0539   0.1440   1.0000
  10.000   1.4210   0.03596   0.02604  -0.0525   0.1407   1.0000
  10.250   1.4364   0.03713   0.02721  -0.0514   0.1378   1.0000
  10.500   1.4503   0.03834   0.02856  -0.0501   0.1350   1.0000
  10.750   1.4608   0.03957   0.03001  -0.0485   0.1318   1.0000
  11.000   1.4702   0.04083   0.03143  -0.0470   0.1283   1.0000
  11.250   1.4785   0.04208   0.03276  -0.0455   0.1250   1.0000
  11.500   1.4873   0.04342   0.03409  -0.0442   0.1219   1.0000
  11.750   1.4901   0.04507   0.03604  -0.0425   0.1185   1.0000
  12.000   1.4937   0.04673   0.03790  -0.0411   0.1151   1.0000
  12.250   1.4974   0.04840   0.03969  -0.0399   0.1121   1.0000
  12.500   1.5015   0.05011   0.04148  -0.0389   0.1096   1.0000
  12.750   1.5048   0.05214   0.04368  -0.0379   0.1073   1.0000
  13.000   1.5054   0.05447   0.04627  -0.0371   0.1048   1.0000
  13.250   1.5052   0.05689   0.04890  -0.0365   0.1021   1.0000
  13.500   1.5043   0.05939   0.05154  -0.0360   0.0997   1.0000
  13.750   1.5032   0.06195   0.05420  -0.0358   0.0975   1.0000
  14.000   1.5009   0.06486   0.05726  -0.0357   0.0955   1.0000
  14.250   1.4946   0.06848   0.06117  -0.0359   0.0932   1.0000
  14.500   1.4873   0.07230   0.06522  -0.0364   0.0910   1.0000
  14.750   1.4792   0.07635   0.06945  -0.0373   0.0887   1.0000
  15.000   1.4711   0.08054   0.07376  -0.0386   0.0865   1.0000
  15.250   1.4625   0.08496   0.07827  -0.0400   0.0844   1.0000
  15.500   1.4457   0.09113   0.08474  -0.0422   0.0824   1.0000
  15.750   1.4273   0.09783   0.09169  -0.0450   0.0807   1.0000
  16.000   1.4066   0.10520   0.09928  -0.0483   0.0791   1.0000
  16.250   1.3827   0.11352   0.10780  -0.0523   0.0779   1.0000
  16.500   1.3506   0.12392   0.11840  -0.0577   0.0771   1.0000
  17.000   1.3093   0.14072   0.13537  -0.0670   0.0740   1.0000
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