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I.S.A. 961 (isa961-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: I.S.A. 961 (isa961-il)
Reynolds number: 200,000
Max Cl/Cd: 70.41 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-isa961-il-200000.txt
Download as CSV file: xf-isa961-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3583   0.09275   0.08958  -0.0311   1.0000   0.0538
  -8.500  -0.3782   0.09151   0.08845  -0.0303   1.0000   0.0540
  -8.250  -0.3926   0.08969   0.08669  -0.0305   1.0000   0.0542
  -8.000  -0.4019   0.08716   0.08419  -0.0317   1.0000   0.0544
  -7.750  -0.4057   0.08417   0.08119  -0.0329   1.0000   0.0545
  -7.500  -0.3999   0.07860   0.07568  -0.0318   0.9982   0.0553
  -7.250  -0.3780   0.07479   0.07186  -0.0334   0.9951   0.0563
  -7.000  -0.3523   0.07068   0.06771  -0.0376   0.9909   0.0576
  -6.750  -0.3120   0.04452   0.04084  -0.0639   0.9840   0.0362
  -6.500  -0.2853   0.03406   0.02969  -0.0701   0.9785   0.0352
  -6.250  -0.2543   0.02578   0.02029  -0.0742   0.9750   0.0347
  -6.000  -0.2175   0.02205   0.01575  -0.0766   0.9726   0.0355
  -5.750  -0.1824   0.01974   0.01306  -0.0784   0.9693   0.0375
  -5.500  -0.1481   0.01902   0.01224  -0.0797   0.9637   0.0411
  -5.250  -0.1087   0.01812   0.01117  -0.0819   0.9602   0.0470
  -5.000  -0.0648   0.01747   0.01042  -0.0847   0.9575   0.0570
  -4.750  -0.0298   0.01744   0.01027  -0.0858   0.9487   0.0788
  -4.500   0.0154   0.01678   0.00958  -0.0894   0.9451   0.0964
  -4.250   0.0529   0.01673   0.00942  -0.0911   0.9388   0.1073
  -4.000   0.0903   0.01678   0.00950  -0.0930   0.9335   0.1190
  -3.750   0.1305   0.01616   0.00888  -0.0953   0.9300   0.1258
  -3.500   0.1618   0.01573   0.00835  -0.0956   0.9216   0.1305
  -3.250   0.2001   0.01508   0.00754  -0.0971   0.9156   0.1342
  -3.000   0.2299   0.01438   0.00685  -0.0969   0.9044   0.1380
  -2.750   0.2599   0.01388   0.00634  -0.0966   0.8925   0.1429
  -2.500   0.2885   0.01353   0.00585  -0.0959   0.8792   0.1493
  -2.250   0.3149   0.01301   0.00539  -0.0950   0.8649   0.1564
  -2.000   0.3414   0.01263   0.00498  -0.0941   0.8511   0.1661
  -1.750   0.3679   0.01222   0.00463  -0.0934   0.8388   0.1827
  -1.500   0.3937   0.01186   0.00438  -0.0927   0.8260   0.2125
  -1.250   0.4196   0.01156   0.00422  -0.0921   0.8131   0.2498
  -1.000   0.4456   0.01126   0.00409  -0.0915   0.7998   0.3004
  -0.750   0.4870   0.00935   0.00398  -0.0940   0.7863   1.0000
  -0.500   0.5132   0.00938   0.00382  -0.0932   0.7709   1.0000
  -0.250   0.5393   0.00942   0.00370  -0.0925   0.7545   1.0000
   0.000   0.5654   0.00947   0.00361  -0.0918   0.7374   1.0000
   0.250   0.5914   0.00956   0.00354  -0.0912   0.7193   1.0000
   0.500   0.6169   0.00965   0.00351  -0.0904   0.6982   1.0000
   0.750   0.6423   0.00978   0.00347  -0.0896   0.6753   1.0000
   1.000   0.6672   0.00994   0.00347  -0.0888   0.6485   1.0000
   1.250   0.6918   0.01013   0.00349  -0.0880   0.6192   1.0000
   1.500   0.7160   0.01036   0.00353  -0.0871   0.5877   1.0000
   1.750   0.7399   0.01063   0.00362  -0.0862   0.5558   1.0000
   2.000   0.7639   0.01091   0.00373  -0.0854   0.5258   1.0000
   2.250   0.7877   0.01123   0.00387  -0.0846   0.4960   1.0000
   2.500   0.8112   0.01157   0.00405  -0.0838   0.4674   1.0000
   2.750   0.8349   0.01192   0.00425  -0.0830   0.4421   1.0000
   3.000   0.8587   0.01228   0.00448  -0.0823   0.4214   1.0000
   3.250   0.8830   0.01260   0.00472  -0.0817   0.4024   1.0000
   3.500   0.9071   0.01293   0.00498  -0.0811   0.3834   1.0000
   3.750   0.9310   0.01327   0.00524  -0.0805   0.3650   1.0000
   4.000   0.9552   0.01360   0.00551  -0.0800   0.3493   1.0000
   4.250   0.9793   0.01392   0.00579  -0.0794   0.3348   1.0000
   4.500   1.0034   0.01425   0.00610  -0.0789   0.3208   1.0000
   4.750   1.0273   0.01459   0.00641  -0.0783   0.3077   1.0000
   5.000   1.0511   0.01493   0.00674  -0.0777   0.2953   1.0000
   5.250   1.0744   0.01530   0.00709  -0.0771   0.2826   1.0000
   5.500   1.0975   0.01568   0.00745  -0.0764   0.2707   1.0000
   5.750   1.1210   0.01604   0.00783  -0.0759   0.2605   1.0000
   6.000   1.1444   0.01640   0.00823  -0.0752   0.2511   1.0000
   6.250   1.1669   0.01682   0.00867  -0.0745   0.2402   1.0000
   6.500   1.1888   0.01726   0.00911  -0.0737   0.2274   1.0000
   6.750   1.2105   0.01771   0.00956  -0.0729   0.2124   1.0000
   7.000   1.2320   0.01817   0.01002  -0.0721   0.1924   1.0000
   7.250   1.2520   0.01874   0.01052  -0.0711   0.1660   1.0000
   7.500   1.2695   0.01949   0.01112  -0.0698   0.1446   1.0000
   7.750   1.2867   0.02027   0.01184  -0.0684   0.1341   1.0000
   8.000   1.3040   0.02100   0.01260  -0.0671   0.1262   1.0000
   8.250   1.3187   0.02189   0.01348  -0.0654   0.1191   1.0000
   8.500   1.3367   0.02251   0.01423  -0.0641   0.1125   1.0000
   8.750   1.3491   0.02345   0.01519  -0.0621   0.1059   1.0000
   9.000   1.3684   0.02386   0.01575  -0.0609   0.0977   1.0000
   9.250   1.3871   0.02431   0.01633  -0.0597   0.0821   1.0000
   9.500   1.3956   0.02544   0.01719  -0.0574   0.0647   1.0000
   9.750   1.4012   0.02678   0.01854  -0.0547   0.0576   1.0000
  10.000   1.4031   0.02842   0.02027  -0.0517   0.0525   1.0000
  10.250   1.4115   0.02967   0.02171  -0.0496   0.0469   1.0000
  10.750   1.4244   0.03262   0.02490  -0.0456   0.0334   1.0000
  11.000   1.4318   0.03409   0.02643  -0.0440   0.0280   1.0000
  11.250   1.4357   0.03592   0.02827  -0.0424   0.0253   1.0000
  11.500   1.4374   0.03801   0.03047  -0.0408   0.0239   1.0000
  11.750   1.4370   0.04040   0.03297  -0.0394   0.0229   1.0000
  12.000   1.4346   0.04311   0.03581  -0.0382   0.0221   1.0000
  12.250   1.4295   0.04625   0.03909  -0.0374   0.0215   1.0000
  12.500   1.4222   0.04983   0.04283  -0.0369   0.0211   1.0000
  12.750   1.4128   0.05384   0.04699  -0.0368   0.0207   1.0000
  13.000   1.4020   0.05823   0.05153  -0.0371   0.0205   1.0000
  13.250   1.3906   0.06285   0.05629  -0.0376   0.0202   1.0000
  13.500   1.3818   0.06731   0.06089  -0.0382   0.0201   1.0000
  13.750   1.3734   0.07182   0.06554  -0.0391   0.0199   1.0000
  14.000   1.3655   0.07636   0.07022  -0.0400   0.0196   1.0000
  14.250   1.3583   0.08087   0.07486  -0.0409   0.0194   1.0000
  14.500   1.3514   0.08539   0.07951  -0.0419   0.0191   1.0000
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