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I.S.A. 961 (isa961-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: I.S.A. 961 (isa961-il)
Reynolds number: 50,000
Max Cl/Cd: 34.92 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-isa961-il-50000.txt
Download as CSV file: xf-isa961-il-50000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3342   0.10527   0.09868  -0.0248   1.0000   0.1758
  -8.750  -0.3550   0.10536   0.09897  -0.0251   1.0000   0.1785
  -8.500  -0.3380   0.09998   0.09361  -0.0235   1.0000   0.1838
  -8.250  -0.3420   0.09791   0.09164  -0.0222   1.0000   0.1897
  -8.000  -0.3639   0.09779   0.09173  -0.0228   1.0000   0.1935
  -7.750  -0.3579   0.09368   0.08767  -0.0206   1.0000   0.1976
  -7.500  -0.3581   0.09120   0.08526  -0.0189   1.0000   0.2046
  -7.250  -0.3813   0.09154   0.08572  -0.0227   1.0000   0.2095
  -7.000  -0.3679   0.08644   0.08070  -0.0169   1.0000   0.2154
  -6.750  -0.3794   0.08553   0.07984  -0.0195   1.0000   0.2243
  -6.250  -0.3783   0.07980   0.07422  -0.0183   1.0000   0.2409
  -6.000  -0.3754   0.07725   0.07169  -0.0171   1.0000   0.2546
  -5.750  -0.3714   0.07390   0.06842  -0.0134   1.0000   0.2660
  -5.500  -0.3674   0.07175   0.06624  -0.0164   1.0000   0.2860
  -5.250   0.0584   0.04088   0.03415  -0.0346   1.0000   1.0000
  -5.000  -0.3567   0.06544   0.06004  -0.0116   1.0000   0.3197
  -4.750  -0.3502   0.06277   0.05738  -0.0106   1.0000   0.3483
  -4.500  -0.3469   0.06007   0.05475  -0.0065   1.0000   0.3816
  -4.250  -0.2335   0.04827   0.04120  -0.0417   1.0000   0.1948
  -4.000  -0.2065   0.04407   0.03676  -0.0432   1.0000   0.1882
  -3.750  -0.1733   0.04035   0.03248  -0.0461   1.0000   0.1972
  -3.500  -0.1486   0.03831   0.03023  -0.0465   1.0000   0.2182
  -3.250  -0.1209   0.03635   0.02789  -0.0476   1.0000   0.2342
  -3.000  -0.0904   0.03462   0.02559  -0.0490   1.0000   0.2414
  -2.750  -0.0660   0.03356   0.02431  -0.0494   1.0000   0.2515
  -2.500  -0.0383   0.03260   0.02289  -0.0502   1.0000   0.2545
  -2.250  -0.0150   0.03190   0.02210  -0.0504   1.0000   0.2626
  -2.000   0.0100   0.03153   0.02139  -0.0508   1.0000   0.2708
  -1.750   0.0328   0.03111   0.02088  -0.0510   1.0000   0.2767
  -1.500   0.0560   0.03098   0.02052  -0.0512   1.0000   0.2843
  -1.250   0.0787   0.03096   0.02041  -0.0514   1.0000   0.2956
  -1.000   0.1216   0.03107   0.02040  -0.0551   0.9940   0.3199
  -0.750   0.1813   0.03085   0.02023  -0.0615   0.9797   0.3653
  -0.500   0.2321   0.02841   0.02000  -0.0656   0.9668   0.8890
  -0.250   0.2882   0.02926   0.01993  -0.0711   0.9465   1.0000
   0.000   0.3415   0.02999   0.02029  -0.0762   0.9264   1.0000
   0.250   0.3901   0.03050   0.02057  -0.0803   0.9042   1.0000
   0.500   0.4483   0.03076   0.02065  -0.0853   0.8843   1.0000
   0.750   0.4850   0.03106   0.02085  -0.0868   0.8605   1.0000
   1.000   0.5368   0.03096   0.02068  -0.0902   0.8410   1.0000
   1.250   0.5781   0.03094   0.02062  -0.0918   0.8203   1.0000
   1.500   0.6179   0.03081   0.02047  -0.0929   0.8000   1.0000
   1.750   0.6616   0.03035   0.01999  -0.0941   0.7818   1.0000
   2.000   0.6996   0.02993   0.01956  -0.0943   0.7624   1.0000
   2.250   0.7313   0.02968   0.01934  -0.0935   0.7408   1.0000
   2.500   0.7700   0.02899   0.01862  -0.0933   0.7221   1.0000
   2.750   0.8010   0.02872   0.01835  -0.0924   0.7013   1.0000
   3.000   0.8308   0.02854   0.01819  -0.0913   0.6803   1.0000
   3.250   0.8649   0.02808   0.01768  -0.0906   0.6612   1.0000
   3.500   0.8893   0.02833   0.01792  -0.0892   0.6392   1.0000
   3.750   0.9174   0.02841   0.01802  -0.0881   0.6196   1.0000
   4.000   0.9463   0.02858   0.01815  -0.0874   0.6018   1.0000
   4.250   0.9725   0.02899   0.01854  -0.0865   0.5841   1.0000
   4.500   0.9948   0.02971   0.01931  -0.0853   0.5660   1.0000
   4.750   1.0185   0.03034   0.02001  -0.0843   0.5491   1.0000
   5.000   1.0425   0.03099   0.02070  -0.0833   0.5329   1.0000
   5.250   1.0668   0.03151   0.02123  -0.0823   0.5161   1.0000
   5.500   1.0924   0.03177   0.02149  -0.0811   0.4982   1.0000
   5.750   1.1184   0.03203   0.02168  -0.0801   0.4803   1.0000
   6.000   1.1376   0.03279   0.02254  -0.0785   0.4620   1.0000
   6.250   1.1585   0.03347   0.02329  -0.0772   0.4443   1.0000
   6.500   1.1800   0.03419   0.02410  -0.0759   0.4274   1.0000
   6.750   1.2013   0.03507   0.02507  -0.0747   0.4115   1.0000
   7.000   1.2220   0.03607   0.02617  -0.0735   0.3958   1.0000
   7.250   1.2420   0.03725   0.02748  -0.0723   0.3806   1.0000
   7.500   1.2610   0.03858   0.02899  -0.0711   0.3657   1.0000
   7.750   1.2788   0.04010   0.03067  -0.0697   0.3513   1.0000
   8.000   1.2956   0.04163   0.03236  -0.0682   0.3371   1.0000
   8.250   1.3120   0.04297   0.03385  -0.0666   0.3227   1.0000
   8.500   1.3276   0.04446   0.03550  -0.0650   0.3097   1.0000
   8.750   1.3457   0.04606   0.03729  -0.0638   0.2986   1.0000
   9.000   1.3682   0.04727   0.03855  -0.0629   0.2864   1.0000
   9.250   1.3684   0.04987   0.04156  -0.0600   0.2758   1.0000
   9.500   1.3754   0.05173   0.04364  -0.0576   0.2634   1.0000
   9.750   1.4084   0.05036   0.04199  -0.0569   0.2426   1.0000
  10.000   1.4145   0.05123   0.04299  -0.0542   0.2272   1.0000
  10.250   1.4206   0.05212   0.04401  -0.0515   0.2126   1.0000
  10.500   1.4247   0.05293   0.04489  -0.0486   0.1985   1.0000
  10.750   1.4096   0.05559   0.04794  -0.0445   0.1897   1.0000
  11.000   1.4038   0.05746   0.04995  -0.0410   0.1801   1.0000
  11.250   1.4030   0.05872   0.05125  -0.0380   0.1688   1.0000
  11.500   1.3957   0.05962   0.05212  -0.0348   0.1565   1.0000
  11.750   1.3877   0.06117   0.05361  -0.0321   0.1441   1.0000
  12.000   1.3796   0.06374   0.05608  -0.0299   0.1311   1.0000
  12.250   1.3562   0.06863   0.06131  -0.0285   0.1263   1.0000
  12.500   1.3461   0.07259   0.06520  -0.0272   0.1155   1.0000
  12.750   1.3217   0.07838   0.07129  -0.0273   0.1129   1.0000
  13.000   1.3165   0.08245   0.07528  -0.0266   0.1040   1.0000
  13.250   1.2894   0.08926   0.08236  -0.0282   0.1039   1.0000
  13.500   1.2612   0.09689   0.09023  -0.0308   0.1044   1.0000
  13.750   1.2328   0.10537   0.09888  -0.0343   0.1052   1.0000
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