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I.S.A. 962 (isa962-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: I.S.A. 962 (isa962-il)
Reynolds number: 50,000
Max Cl/Cd: 36.21 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-isa962-il-50000.txt
Download as CSV file: xf-isa962-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3079   0.11290   0.10569  -0.0240   1.0000   0.1707
  -9.500  -0.3229   0.11330   0.10624  -0.0256   1.0000   0.1745
  -9.250  -0.3141   0.10898   0.10198  -0.0252   1.0000   0.1775
  -9.000  -0.2994   0.10510   0.09812  -0.0238   1.0000   0.1845
  -8.750  -0.3108   0.10446   0.09763  -0.0235   1.0000   0.1900
  -8.500  -0.3391   0.10565   0.09905  -0.0229   1.0000   0.1918
  -8.250  -0.3123   0.09937   0.09275  -0.0206   1.0000   0.1978
  -8.000  -0.3181   0.09778   0.09128  -0.0184   1.0000   0.2033
  -7.750  -0.3402   0.09795   0.09160  -0.0176   1.0000   0.2078
  -7.500  -0.3559   0.09699   0.09078  -0.0177   1.0000   0.2102
  -7.250  -0.3420   0.09267   0.08650  -0.0131   1.0000   0.2159
  -7.000  -0.3505   0.09140   0.08531  -0.0120   1.0000   0.2227
  -6.750  -0.3646   0.09052   0.08454  -0.0139   1.0000   0.2276
  -6.500  -0.3578   0.08708   0.08116  -0.0092   1.0000   0.2332
  -6.250  -0.3679   0.08712   0.08122  -0.0142   1.0000   0.2438
  -6.000  -0.3627   0.08302   0.07722  -0.0082   1.0000   0.2482
  -5.750  -0.3633   0.08198   0.07618  -0.0119   1.0000   0.2612
  -5.500  -0.3598   0.07858   0.07288  -0.0067   1.0000   0.2670
  -5.000  -0.3507   0.07443   0.06876  -0.0084   1.0000   0.2966
  -4.750  -0.3449   0.07212   0.06649  -0.0075   1.0000   0.3137
  -4.500  -0.3395   0.06967   0.06410  -0.0056   1.0000   0.3318
  -4.250  -0.3339   0.06733   0.06181  -0.0032   1.0000   0.3523
  -4.000  -0.3267   0.06517   0.05968  -0.0023   1.0000   0.3822
  -3.750  -0.3212   0.06297   0.05754   0.0001   1.0000   0.4150
  -3.500  -0.3183   0.06069   0.05536   0.0043   1.0000   0.4505
  -3.250  -0.3181   0.05867   0.05343   0.0093   1.0000   0.4994
  -3.000  -0.3189   0.05641   0.05129   0.0155   1.0000   0.5393
  -2.750  -0.3175   0.05428   0.04923   0.0202   1.0000   0.5855
  -2.500  -0.3148   0.05197   0.04702   0.0250   1.0000   0.6218
  -2.250  -0.3042   0.04975   0.04484   0.0267   1.0000   0.6536
  -2.000  -0.2870   0.04746   0.04257   0.0264   1.0000   0.6735
  -1.750  -0.0044   0.04219   0.03380  -0.0520   0.9993   0.1848
  -1.500   0.0764   0.04001   0.03081  -0.0620   0.9843   0.1681
  -1.250   0.1425   0.03874   0.02902  -0.0692   0.9693   0.1675
  -1.000   0.1978   0.03794   0.02781  -0.0743   0.9553   0.1716
  -0.750   0.2524   0.03728   0.02676  -0.0790   0.9429   0.1761
  -0.500   0.2975   0.03688   0.02624  -0.0821   0.9292   0.1892
  -0.250   0.3416   0.03654   0.02584  -0.0849   0.9153   0.2117
   0.000   0.3860   0.03593   0.02552  -0.0877   0.9013   0.2691
   0.250   0.4276   0.03348   0.02461  -0.0889   0.8881   1.0000
   0.500   0.4665   0.03414   0.02491  -0.0908   0.8713   1.0000
   0.750   0.5046   0.03473   0.02527  -0.0926   0.8538   1.0000
   1.000   0.5428   0.03523   0.02560  -0.0942   0.8361   1.0000
   1.250   0.5816   0.03562   0.02587  -0.0958   0.8182   1.0000
   1.500   0.6220   0.03583   0.02599  -0.0972   0.8003   1.0000
   1.750   0.6641   0.03586   0.02596  -0.0987   0.7829   1.0000
   2.000   0.7048   0.03571   0.02577  -0.0996   0.7655   1.0000
   2.250   0.7467   0.03516   0.02519  -0.0999   0.7481   1.0000
   2.500   0.7709   0.03527   0.02528  -0.0982   0.7250   1.0000
   2.750   0.8089   0.03433   0.02431  -0.0973   0.7052   1.0000
   3.000   0.8497   0.03297   0.02291  -0.0963   0.6860   1.0000
   3.250   0.8875   0.03184   0.02173  -0.0951   0.6672   1.0000
   3.500   0.9223   0.03109   0.02095  -0.0940   0.6488   1.0000
   3.750   0.9452   0.03130   0.02116  -0.0922   0.6268   1.0000
   4.000   0.9729   0.03111   0.02095  -0.0907   0.6057   1.0000
   4.250   1.0038   0.03070   0.02048  -0.0894   0.5850   1.0000
   4.500   1.0316   0.03053   0.02024  -0.0879   0.5627   1.0000
   4.750   1.0557   0.03060   0.02028  -0.0861   0.5377   1.0000
   5.000   1.0822   0.03056   0.02014  -0.0845   0.5122   1.0000
   5.250   1.1082   0.03062   0.02004  -0.0829   0.4849   1.0000
   5.500   1.1293   0.03119   0.02051  -0.0811   0.4561   1.0000
   5.750   1.1522   0.03189   0.02104  -0.0796   0.4294   1.0000
   6.000   1.1758   0.03276   0.02176  -0.0783   0.4054   1.0000
   6.250   1.1997   0.03385   0.02266  -0.0774   0.3849   1.0000
   6.500   1.2201   0.03529   0.02410  -0.0762   0.3670   1.0000
   6.750   1.2420   0.03674   0.02553  -0.0753   0.3512   1.0000
   7.000   1.2661   0.03818   0.02687  -0.0747   0.3372   1.0000
   7.250   1.2794   0.04017   0.02914  -0.0731   0.3249   1.0000
   7.500   1.2956   0.04216   0.03128  -0.0718   0.3140   1.0000
   7.750   1.3219   0.04366   0.03266  -0.0716   0.3036   1.0000
   8.000   1.3250   0.04639   0.03588  -0.0692   0.2953   1.0000
   8.250   1.3512   0.04803   0.03740  -0.0690   0.2869   1.0000
   8.500   1.3450   0.05139   0.04129  -0.0659   0.2804   1.0000
   8.750   1.3681   0.05304   0.04293  -0.0654   0.2728   1.0000
   9.000   1.3631   0.05673   0.04698  -0.0627   0.2684   1.0000
   9.250   1.3414   0.06150   0.05217  -0.0593   0.2653   1.0000
   9.500   1.3087   0.06710   0.05809  -0.0558   0.2634   1.0000
   9.750   1.2152   0.07812   0.06934  -0.0523   0.2662   1.0000
  10.000   1.1022   0.09901   0.09021  -0.0594   0.2705   1.0000
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