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I.S.A. 960 (isa960-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: I.S.A. 960 (isa960-il)
Reynolds number: 200,000
Max Cl/Cd: 53.68 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-isa960-il-200000-n5.txt
Download as CSV file: xf-isa960-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: I.S.A. 960                                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3406   0.09873   0.09536  -0.0340   1.0000   0.0167
 -10.000  -0.3403   0.09518   0.09185  -0.0350   1.0000   0.0166
  -9.750  -0.3418   0.09168   0.08841  -0.0357   1.0000   0.0165
  -9.500  -0.3387   0.08737   0.08414  -0.0386   0.9931   0.0164
  -9.250  -0.3324   0.08224   0.07902  -0.0432   0.9755   0.0164
  -9.000  -0.3269   0.07681   0.07361  -0.0487   0.9540   0.0164
  -8.750  -0.3163   0.06993   0.06671  -0.0574   0.9384   0.0165
  -8.500  -0.3052   0.06091   0.05762  -0.0688   0.9259   0.0167
  -8.250  -0.3116   0.02946   0.02480  -0.0964   0.9205   0.0169
  -8.000  -0.2867   0.02543   0.02001  -0.0984   0.9096   0.0180
  -7.750  -0.2608   0.02338   0.01771  -0.0992   0.8980   0.0190
  -7.500  -0.2344   0.02185   0.01590  -0.0995   0.8853   0.0200
  -7.250  -0.2086   0.02042   0.01412  -0.0994   0.8697   0.0213
  -7.000  -0.1829   0.01926   0.01262  -0.0991   0.8505   0.0231
  -6.750  -0.1566   0.01850   0.01153  -0.0986   0.8289   0.0248
  -6.500  -0.1321   0.01704   0.00983  -0.0981   0.7993   0.0271
  -6.250  -0.1072   0.01634   0.00879  -0.0973   0.7594   0.0294
  -6.000  -0.0823   0.01585   0.00790  -0.0964   0.7221   0.0325
  -5.750  -0.0571   0.01527   0.00701  -0.0958   0.6900   0.0354
  -5.500  -0.0312   0.01482   0.00636  -0.0953   0.6575   0.0394
  -5.250  -0.0054   0.01452   0.00579  -0.0947   0.6138   0.0440
  -5.000   0.0188   0.01449   0.00545  -0.0939   0.5412   0.0501
  -4.750   0.0436   0.01462   0.00526  -0.0933   0.4801   0.0608
  -4.500   0.0627   0.01559   0.00525  -0.0920   0.2593   0.0711
  -4.250   0.0886   0.01566   0.00506  -0.0916   0.2233   0.0804
  -4.000   0.1158   0.01561   0.00485  -0.0915   0.2141   0.0894
  -3.750   0.1429   0.01553   0.00472  -0.0913   0.2066   0.0968
  -3.500   0.1702   0.01547   0.00455  -0.0912   0.2007   0.1024
  -3.250   0.1975   0.01540   0.00443  -0.0910   0.1940   0.1072
  -3.000   0.2248   0.01537   0.00432  -0.0909   0.1871   0.1132
  -2.500   0.2781   0.01550   0.00418  -0.0904   0.1297   0.1262
  -2.250   0.3051   0.01551   0.00413  -0.0903   0.1265   0.1344
  -2.000   0.3322   0.01553   0.00409  -0.0901   0.1246   0.1434
  -1.750   0.3591   0.01549   0.00405  -0.0899   0.1233   0.1516
  -1.250   0.4129   0.01549   0.00400  -0.0896   0.1217   0.1715
  -1.000   0.4398   0.01549   0.00402  -0.0894   0.1212   0.1827
  -0.750   0.4665   0.01551   0.00406  -0.0893   0.1209   0.1964
  -0.500   0.4931   0.01553   0.00414  -0.0891   0.1205   0.2172
  -0.250   0.5196   0.01552   0.00424  -0.0890   0.1202   0.2595
   0.000   0.5457   0.01542   0.00435  -0.0888   0.1200   0.3334
   0.500   0.5978   0.01421   0.00462  -0.0879   0.1196   1.0000
   0.750   0.6240   0.01442   0.00475  -0.0876   0.1195   1.0000
   1.000   0.6500   0.01463   0.00490  -0.0873   0.1194   1.0000
   1.250   0.6759   0.01486   0.00507  -0.0870   0.1192   1.0000
   1.500   0.7016   0.01509   0.00526  -0.0867   0.1190   1.0000
   1.750   0.7273   0.01533   0.00547  -0.0864   0.1188   1.0000
   2.000   0.7528   0.01559   0.00569  -0.0861   0.1186   1.0000
   2.250   0.7781   0.01585   0.00593  -0.0857   0.1184   1.0000
   2.500   0.8033   0.01613   0.00619  -0.0854   0.1183   1.0000
   2.750   0.8283   0.01641   0.00647  -0.0850   0.1182   1.0000
   3.000   0.8532   0.01670   0.00675  -0.0846   0.1181   1.0000
   3.250   0.8779   0.01700   0.00705  -0.0842   0.1182   1.0000
   3.500   0.9023   0.01731   0.00738  -0.0838   0.1183   1.0000
   3.750   0.9266   0.01763   0.00771  -0.0833   0.1183   1.0000
   4.000   0.9506   0.01797   0.00806  -0.0828   0.1185   1.0000
   4.250   0.9743   0.01832   0.00845  -0.0823   0.1186   1.0000
   4.500   0.9977   0.01868   0.00883  -0.0817   0.1187   1.0000
   4.750   1.0208   0.01906   0.00924  -0.0811   0.1189   1.0000
   5.000   1.0436   0.01945   0.00967  -0.0805   0.1190   1.0000
   5.250   1.0660   0.01986   0.01013  -0.0798   0.1192   1.0000
   5.500   1.0882   0.02029   0.01059  -0.0791   0.1193   1.0000
   5.750   1.1099   0.02074   0.01108  -0.0783   0.1195   1.0000
   6.000   1.1313   0.02121   0.01160  -0.0775   0.1194   1.0000
   6.250   1.1519   0.02173   0.01219  -0.0766   0.1188   1.0000
   6.500   1.1718   0.02232   0.01283  -0.0756   0.1177   1.0000
   6.750   1.1896   0.02312   0.01363  -0.0744   0.1152   1.0000
   7.000   1.2057   0.02458   0.01494  -0.0732   0.1115   1.0000
   7.250   1.2243   0.02496   0.01549  -0.0720   0.1082   1.0000
   7.500   1.2425   0.02565   0.01627  -0.0709   0.1053   1.0000
   7.750   1.2614   0.02674   0.01729  -0.0700   0.1023   1.0000
   8.000   1.2766   0.02724   0.01795  -0.0684   0.0999   1.0000
   8.250   1.2902   0.02762   0.01854  -0.0664   0.0965   1.0000
   8.500   1.3031   0.02838   0.01935  -0.0647   0.0925   1.0000
   8.750   1.3210   0.02825   0.01960  -0.0635   0.0858   1.0000
   9.000   1.3495   0.02771   0.01909  -0.0639   0.0423   1.0000
   9.250   1.3515   0.02957   0.02074  -0.0612   0.0220   1.0000
   9.500   1.3597   0.03100   0.02216  -0.0592   0.0182   1.0000
   9.750   1.3698   0.03227   0.02356  -0.0576   0.0167   1.0000
  10.000   1.3783   0.03369   0.02511  -0.0560   0.0153   1.0000
  10.250   1.3848   0.03533   0.02688  -0.0544   0.0141   1.0000
  10.500   1.3885   0.03725   0.02897  -0.0527   0.0132   1.0000
  10.750   1.3900   0.03944   0.03133  -0.0511   0.0126   1.0000
  11.000   1.3936   0.04148   0.03355  -0.0499   0.0123   1.0000
  11.250   1.3952   0.04380   0.03605  -0.0489   0.0120   1.0000
  11.500   1.3948   0.04644   0.03890  -0.0480   0.0117   1.0000
  11.750   1.3928   0.04935   0.04199  -0.0473   0.0114   1.0000
  12.000   1.3893   0.05256   0.04536  -0.0470   0.0111   1.0000
  12.250   1.3843   0.05605   0.04901  -0.0468   0.0108   1.0000
  12.500   1.3780   0.05983   0.05295  -0.0469   0.0105   1.0000
  12.750   1.3707   0.06390   0.05717  -0.0473   0.0102   1.0000
  13.000   1.3624   0.06830   0.06171  -0.0480   0.0100   1.0000
  13.250   1.3532   0.07303   0.06659  -0.0490   0.0098   1.0000
  13.500   1.3434   0.07803   0.07172  -0.0503   0.0096   1.0000
  13.750   1.3330   0.08328   0.07708  -0.0518   0.0094   1.0000
  14.000   1.3223   0.08865   0.08258  -0.0534   0.0093   1.0000
  14.250   1.3119   0.09405   0.08809  -0.0551   0.0092   1.0000
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