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I.S.A. 960 (isa960-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: I.S.A. 960 (isa960-il)
Reynolds number: 500,000
Max Cl/Cd: 72.08 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-isa960-il-500000-n5.txt
Download as CSV file: xf-isa960-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.3620   0.11454   0.11161  -0.0282   0.7899   0.0075
 -11.500  -0.3606   0.11071   0.10751  -0.0294   0.7339   0.0075
 -10.500  -0.5373   0.02897   0.02566  -0.0967   0.9147   0.0075
 -10.250  -0.5184   0.02529   0.02156  -0.0983   0.9025   0.0077
 -10.000  -0.4972   0.02306   0.01900  -0.0988   0.8912   0.0079
  -9.750  -0.4748   0.02133   0.01697  -0.0989   0.8797   0.0082
  -9.500  -0.4513   0.01998   0.01536  -0.0988   0.8676   0.0087
  -9.250  -0.4272   0.01884   0.01394  -0.0986   0.8526   0.0090
  -9.000  -0.4032   0.01778   0.01261  -0.0982   0.8295   0.0094
  -8.750  -0.3806   0.01679   0.01126  -0.0975   0.7816   0.0099
  -8.500  -0.3573   0.01630   0.01041  -0.0967   0.7301   0.0104
  -8.250  -0.3325   0.01585   0.00966  -0.0962   0.6941   0.0109
  -8.000  -0.3072   0.01540   0.00894  -0.0957   0.6526   0.0115
  -7.750  -0.2909   0.01645   0.00852  -0.0942   0.2545   0.0121
  -7.500  -0.2646   0.01611   0.00791  -0.0939   0.2091   0.0127
  -7.250  -0.2378   0.01559   0.00725  -0.0938   0.1959   0.0138
  -7.000  -0.2106   0.01534   0.00689  -0.0937   0.1776   0.0151
  -6.750  -0.1837   0.01518   0.00652  -0.0935   0.1179   0.0164
  -6.250  -0.1288   0.01447   0.00561  -0.0933   0.1112   0.0192
  -6.000  -0.1012   0.01424   0.00532  -0.0932   0.1101   0.0213
  -5.750  -0.0734   0.01405   0.00504  -0.0931   0.1091   0.0235
  -5.500  -0.0456   0.01391   0.00481  -0.0930   0.1082   0.0247
  -5.250  -0.0181   0.01354   0.00436  -0.0929   0.1073   0.0277
  -5.000   0.0096   0.01332   0.00408  -0.0928   0.1066   0.0304
  -4.750   0.0373   0.01318   0.00384  -0.0927   0.1058   0.0326
  -4.500   0.0651   0.01305   0.00365  -0.0926   0.1052   0.0351
  -4.250   0.0928   0.01290   0.00348  -0.0924   0.1045   0.0400
  -4.000   0.1203   0.01275   0.00343  -0.0924   0.1040   0.0574
  -3.750   0.1481   0.01275   0.00340  -0.0923   0.1035   0.0684
  -3.500   0.1758   0.01278   0.00338  -0.0922   0.1030   0.0737
  -3.250   0.2035   0.01282   0.00337  -0.0920   0.1027   0.0767
  -3.000   0.2310   0.01279   0.00332  -0.0920   0.1024   0.0811
  -2.750   0.2586   0.01281   0.00332  -0.0919   0.1021   0.0840
  -2.500   0.2860   0.01285   0.00332  -0.0917   0.1018   0.0867
  -2.250   0.3135   0.01290   0.00334  -0.0916   0.1016   0.0892
  -2.000   0.3409   0.01295   0.00336  -0.0915   0.1016   0.0915
  -1.750   0.3682   0.01300   0.00340  -0.0914   0.1015   0.0952
  -1.500   0.3955   0.01306   0.00345  -0.0913   0.1014   0.0997
  -1.250   0.4227   0.01311   0.00353  -0.0912   0.1012   0.1101
  -1.000   0.4499   0.01318   0.00363  -0.0911   0.1011   0.1286
  -0.750   0.4770   0.01328   0.00373  -0.0910   0.1009   0.1417
  -0.500   0.5040   0.01338   0.00384  -0.0909   0.1008   0.1494
  -0.250   0.5309   0.01351   0.00395  -0.0907   0.1008   0.1568
   0.000   0.5576   0.01364   0.00408  -0.0906   0.1007   0.1634
   0.250   0.5843   0.01377   0.00423  -0.0904   0.1007   0.1711
   0.500   0.6108   0.01392   0.00439  -0.0903   0.1007   0.1806
   0.750   0.6372   0.01406   0.00457  -0.0901   0.1006   0.1965
   1.000   0.6634   0.01414   0.00479  -0.0899   0.1006   0.2488
   1.250   0.6894   0.01422   0.00501  -0.0898   0.1006   0.3132
   1.750   0.7376   0.01315   0.00554  -0.0887   0.1006   1.0000
   2.000   0.7632   0.01342   0.00578  -0.0884   0.1006   1.0000
   2.250   0.7886   0.01370   0.00603  -0.0881   0.1007   1.0000
   2.500   0.8139   0.01400   0.00630  -0.0877   0.1007   1.0000
   2.750   0.8390   0.01431   0.00659  -0.0874   0.1007   1.0000
   3.000   0.8639   0.01462   0.00689  -0.0870   0.1008   1.0000
   3.250   0.8886   0.01495   0.00720  -0.0866   0.1008   1.0000
   3.500   0.9132   0.01529   0.00754  -0.0862   0.1008   1.0000
   3.750   0.9375   0.01565   0.00788  -0.0857   0.1009   1.0000
   4.000   0.9619   0.01599   0.00822  -0.0853   0.1008   1.0000
   4.250   0.9868   0.01625   0.00850  -0.0850   0.1005   1.0000
   4.500   1.0116   0.01652   0.00877  -0.0846   0.1000   1.0000
   4.750   1.0358   0.01683   0.00910  -0.0842   0.0997   1.0000
   5.000   1.0597   0.01717   0.00946  -0.0838   0.0995   1.0000
   5.250   1.0837   0.01749   0.00980  -0.0833   0.0989   1.0000
   5.500   1.1075   0.01780   0.01014  -0.0828   0.0982   1.0000
   5.750   1.1315   0.01804   0.01041  -0.0825   0.0964   1.0000
   6.000   1.1547   0.01834   0.01072  -0.0820   0.0939   1.0000
   6.250   1.1745   0.01905   0.01140  -0.0810   0.0923   1.0000
   6.500   1.2016   0.01886   0.01131  -0.0810   0.0910   1.0000
   6.750   1.2281   0.01880   0.01133  -0.0810   0.0886   1.0000
   7.000   1.2553   0.01870   0.01128  -0.0811   0.0856   1.0000
   7.250   1.2819   0.01867   0.01132  -0.0811   0.0818   1.0000
   7.500   1.3141   0.01823   0.01063  -0.0821   0.0465   1.0000
   7.750   1.3245   0.01950   0.01171  -0.0797   0.0176   1.0000
   8.000   1.3421   0.02014   0.01237  -0.0784   0.0136   1.0000
   8.250   1.3601   0.02069   0.01298  -0.0771   0.0119   1.0000
   8.500   1.3759   0.02126   0.01363  -0.0754   0.0109   1.0000
   8.750   1.3904   0.02193   0.01438  -0.0735   0.0100   1.0000
   9.000   1.4029   0.02277   0.01529  -0.0715   0.0092   1.0000
   9.250   1.4152   0.02363   0.01623  -0.0695   0.0086   1.0000
   9.500   1.4283   0.02445   0.01714  -0.0678   0.0081   1.0000
   9.750   1.4403   0.02537   0.01813  -0.0661   0.0076   1.0000
  10.000   1.4515   0.02638   0.01922  -0.0644   0.0072   1.0000
  10.250   1.4615   0.02751   0.02042  -0.0627   0.0068   1.0000
  10.500   1.4691   0.02887   0.02188  -0.0609   0.0065   1.0000
  10.750   1.4729   0.03059   0.02371  -0.0589   0.0062   1.0000
  11.000   1.4798   0.03211   0.02534  -0.0574   0.0060   1.0000
  11.250   1.4859   0.03375   0.02708  -0.0560   0.0058   1.0000
  11.500   1.4907   0.03557   0.02901  -0.0546   0.0057   1.0000
  11.750   1.4941   0.03761   0.03117  -0.0534   0.0055   1.0000
  12.000   1.4961   0.03985   0.03353  -0.0524   0.0054   1.0000
  12.250   1.4971   0.04232   0.03611  -0.0515   0.0052   1.0000
  12.500   1.4971   0.04497   0.03888  -0.0509   0.0051   1.0000
  12.750   1.4963   0.04780   0.04182  -0.0504   0.0049   1.0000
  13.000   1.4945   0.05083   0.04496  -0.0501   0.0048   1.0000
  13.250   1.4913   0.05412   0.04836  -0.0500   0.0047   1.0000
  13.500   1.4868   0.05769   0.05204  -0.0501   0.0046   1.0000
  13.750   1.4802   0.06172   0.05621  -0.0505   0.0045   1.0000
  14.000   1.4719   0.06620   0.06081  -0.0513   0.0044   1.0000
  14.250   1.4609   0.07122   0.06596  -0.0523   0.0043   1.0000
  14.500   1.4478   0.07676   0.07164  -0.0537   0.0043   1.0000
  14.750   1.4326   0.08280   0.07782  -0.0555   0.0042   1.0000
  15.000   1.4218   0.08828   0.08342  -0.0572   0.0042   1.0000
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