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I.S.A. 960 (isa960-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: I.S.A. 960 (isa960-il)
Reynolds number: 1,000,000
Max Cl/Cd: 90.52 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-isa960-il-1000000.txt
Download as CSV file: xf-isa960-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.2532   0.09849   0.09604  -0.0379   0.7270   0.0150
 -11.000  -0.2579   0.09250   0.09010  -0.0405   0.7354   0.0162
 -10.750  -0.6093   0.02675   0.02405  -0.0895   0.9851   0.0095
 -10.500  -0.5932   0.02055   0.01716  -0.0927   0.9750   0.0101
 -10.250  -0.5616   0.01952   0.01602  -0.0942   0.9634   0.0104
 -10.000  -0.5295   0.01877   0.01515  -0.0955   0.9458   0.0108
  -9.750  -0.5026   0.01803   0.01424  -0.0956   0.9282   0.0112
  -9.250  -0.4542   0.01631   0.01209  -0.0946   0.8982   0.0120
  -9.000  -0.4295   0.01558   0.01116  -0.0941   0.8831   0.0123
  -8.750  -0.4039   0.01504   0.01044  -0.0936   0.8658   0.0126
  -8.500  -0.3808   0.01354   0.00867  -0.0931   0.8436   0.0133
  -8.250  -0.3560   0.01321   0.00812  -0.0923   0.7945   0.0138
  -8.000  -0.3317   0.01311   0.00770  -0.0915   0.7309   0.0144
  -7.750  -0.3056   0.01290   0.00727  -0.0911   0.6928   0.0151
  -7.500  -0.2793   0.01271   0.00683  -0.0907   0.6483   0.0158
  -7.250  -0.2554   0.01314   0.00667  -0.0900   0.4982   0.0163
  -7.000  -0.2348   0.01337   0.00595  -0.0892   0.2218   0.0175
  -6.750  -0.2073   0.01321   0.00569  -0.0891   0.2023   0.0185
  -6.500  -0.1797   0.01301   0.00537  -0.0889   0.1847   0.0195
  -6.250  -0.1525   0.01298   0.00513  -0.0887   0.1171   0.0205
  -6.000  -0.1250   0.01258   0.00463  -0.0886   0.1133   0.0217
  -5.750  -0.0974   0.01223   0.00424  -0.0885   0.1107   0.0234
  -5.500  -0.0694   0.01207   0.00403  -0.0884   0.1088   0.0251
  -5.250  -0.0413   0.01193   0.00384  -0.0883   0.1075   0.0264
  -5.000  -0.0135   0.01162   0.00346  -0.0882   0.1068   0.0283
  -4.750   0.0144   0.01138   0.00318  -0.0881   0.1062   0.0309
  -4.500   0.0424   0.01124   0.00299  -0.0880   0.1060   0.0331
  -4.250   0.0705   0.01113   0.00283  -0.0879   0.1059   0.0354
  -4.000   0.0985   0.01097   0.00267  -0.0878   0.1058   0.0416
  -3.750   0.1263   0.01084   0.00267  -0.0878   0.1058   0.0667
  -3.500   0.1545   0.01090   0.00271  -0.0877   0.1057   0.0745
  -3.250   0.1825   0.01091   0.00270  -0.0877   0.1056   0.0793
  -3.000   0.2105   0.01090   0.00267  -0.0877   0.1054   0.0840
  -2.750   0.2385   0.01092   0.00266  -0.0876   0.1052   0.0869
  -2.500   0.2664   0.01096   0.00267  -0.0876   0.1052   0.0889
  -2.250   0.2943   0.01096   0.00267  -0.0875   0.1051   0.0933
  -2.000   0.3221   0.01099   0.00269  -0.0875   0.1051   0.0973
  -1.750   0.3499   0.01103   0.00273  -0.0874   0.1051   0.1013
  -1.500   0.3777   0.01107   0.00279  -0.0873   0.1051   0.1097
  -1.250   0.4053   0.01111   0.00288  -0.0873   0.1052   0.1267
  -1.000   0.4329   0.01118   0.00298  -0.0872   0.1052   0.1430
  -0.750   0.4604   0.01126   0.00308  -0.0872   0.1052   0.1541
  -0.500   0.4879   0.01137   0.00318  -0.0871   0.1052   0.1611
  -0.250   0.5153   0.01146   0.00329  -0.0870   0.1053   0.1704
   0.000   0.5425   0.01157   0.00341  -0.0869   0.1053   0.1798
   0.250   0.5697   0.01167   0.00355  -0.0868   0.1054   0.1947
   0.500   0.5966   0.01172   0.00372  -0.0868   0.1054   0.2408
   0.750   0.6234   0.01172   0.00391  -0.0867   0.1055   0.3186
   1.000   0.6408   0.01042   0.00420  -0.0849   0.1055   0.9082
   1.250   0.6735   0.01055   0.00438  -0.0860   0.1056   1.0000
   1.500   0.6999   0.01079   0.00458  -0.0858   0.1056   1.0000
   1.750   0.7262   0.01103   0.00480  -0.0855   0.1057   1.0000
   2.000   0.7523   0.01129   0.00503  -0.0853   0.1057   1.0000
   2.250   0.7782   0.01156   0.00528  -0.0850   0.1058   1.0000
   2.500   0.8040   0.01184   0.00555  -0.0847   0.1058   1.0000
   2.750   0.8296   0.01214   0.00583  -0.0845   0.1059   1.0000
   3.000   0.8551   0.01245   0.00612  -0.0841   0.1059   1.0000
   3.250   0.8817   0.01261   0.00627  -0.0840   0.1056   1.0000
   3.500   0.9083   0.01276   0.00642  -0.0839   0.1051   1.0000
   3.750   0.9341   0.01301   0.00666  -0.0837   0.1049   1.0000
   4.000   0.9594   0.01330   0.00695  -0.0834   0.1048   1.0000
   4.250   0.9846   0.01361   0.00727  -0.0831   0.1048   1.0000
   4.500   1.0097   0.01391   0.00757  -0.0827   0.1047   1.0000
   4.750   1.0357   0.01408   0.00775  -0.0826   0.1035   1.0000
   5.000   1.0613   0.01429   0.00796  -0.0824   0.1016   1.0000
   5.250   1.0861   0.01458   0.00826  -0.0821   0.1003   1.0000
   5.500   1.1105   0.01490   0.00858  -0.0817   0.0990   1.0000
   5.750   1.1341   0.01531   0.00899  -0.0812   0.0980   1.0000
   6.000   1.1546   0.01613   0.00977  -0.0803   0.0963   1.0000
   6.250   1.1785   0.01645   0.01014  -0.0799   0.0948   1.0000
   6.500   1.2064   0.01620   0.00994  -0.0801   0.0935   1.0000
   6.750   1.2339   0.01609   0.00987  -0.0802   0.0915   1.0000
   7.000   1.2632   0.01583   0.00964  -0.0807   0.0884   1.0000
   7.250   1.2943   0.01549   0.00925  -0.0815   0.0844   1.0000
   7.500   1.3307   0.01470   0.00810  -0.0831   0.0446   1.0000
   7.750   1.3439   0.01593   0.00915  -0.0811   0.0174   1.0000
   8.000   1.3632   0.01659   0.00982  -0.0799   0.0144   1.0000
   8.250   1.3835   0.01712   0.01040  -0.0789   0.0134   1.0000
   8.500   1.4031   0.01767   0.01101  -0.0778   0.0125   1.0000
   8.750   1.4209   0.01834   0.01172  -0.0765   0.0115   1.0000
   9.000   1.4353   0.01924   0.01269  -0.0746   0.0106   1.0000
   9.250   1.4517   0.01987   0.01339  -0.0731   0.0103   1.0000
   9.500   1.4660   0.02048   0.01406  -0.0711   0.0099   1.0000
   9.750   1.4789   0.02119   0.01483  -0.0690   0.0095   1.0000
  10.000   1.4910   0.02198   0.01568  -0.0669   0.0091   1.0000
  10.250   1.5023   0.02284   0.01661  -0.0649   0.0088   1.0000
  10.500   1.5121   0.02384   0.01768  -0.0628   0.0085   1.0000
  10.750   1.5189   0.02510   0.01902  -0.0605   0.0082   1.0000
  11.000   1.5176   0.02703   0.02108  -0.0576   0.0078   1.0000
  11.250   1.5210   0.02870   0.02286  -0.0555   0.0076   1.0000
  11.500   1.5310   0.02990   0.02412  -0.0542   0.0075   1.0000
  11.750   1.5391   0.03130   0.02560  -0.0529   0.0073   1.0000
  12.000   1.5443   0.03301   0.02740  -0.0515   0.0071   1.0000
  12.250   1.5482   0.03492   0.02940  -0.0502   0.0069   1.0000
  12.500   1.5512   0.03701   0.03159  -0.0491   0.0068   1.0000
  12.750   1.5527   0.03935   0.03402  -0.0482   0.0066   1.0000
  13.000   1.5532   0.04189   0.03667  -0.0475   0.0065   1.0000
  13.250   1.5529   0.04463   0.03950  -0.0471   0.0063   1.0000
  13.500   1.5506   0.04765   0.04261  -0.0467   0.0062   1.0000
  13.750   1.5470   0.05093   0.04599  -0.0465   0.0061   1.0000
  14.000   1.5417   0.05455   0.04971  -0.0466   0.0060   1.0000
  14.250   1.5343   0.05860   0.05387  -0.0469   0.0059   1.0000
  14.500   1.5246   0.06315   0.05853  -0.0476   0.0059   1.0000
  14.750   1.5134   0.06813   0.06362  -0.0486   0.0058   1.0000
  15.000   1.5002   0.07354   0.06915  -0.0499   0.0057   1.0000
  15.250   1.4858   0.07929   0.07502  -0.0515   0.0057   1.0000
  15.500   1.4697   0.08543   0.08128  -0.0532   0.0056   1.0000
  15.750   1.4534   0.09167   0.08765  -0.0551   0.0056   1.0000
  16.000   1.4365   0.09806   0.09415  -0.0571   0.0055   1.0000
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