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I.S.A. 960 (isa960-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: I.S.A. 960 (isa960-il)
Reynolds number: 500,000
Max Cl/Cd: 68.19 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-isa960-il-500000.txt
Download as CSV file: xf-isa960-il-500000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3419   0.08933   0.08725  -0.0349   0.9982   0.0254
  -9.250  -0.3346   0.08306   0.08101  -0.0434   0.9815   0.0266
  -8.750  -0.3839   0.02768   0.02438  -0.0931   0.9560   0.0176
  -8.500  -0.3568   0.02425   0.02051  -0.0953   0.9424   0.0181
  -8.250  -0.3307   0.02180   0.01766  -0.0962   0.9283   0.0188
  -7.750  -0.2814   0.01889   0.01400  -0.0956   0.8981   0.0204
  -7.500  -0.2583   0.01720   0.01191  -0.0950   0.8809   0.0214
  -7.250  -0.2346   0.01590   0.01044  -0.0944   0.8609   0.0225
  -7.000  -0.2097   0.01514   0.00950  -0.0937   0.8354   0.0235
  -6.750  -0.1850   0.01449   0.00857  -0.0929   0.7950   0.0247
  -6.500  -0.1604   0.01403   0.00776  -0.0920   0.7501   0.0259
  -6.250  -0.1351   0.01338   0.00680  -0.0913   0.7198   0.0274
  -6.000  -0.1100   0.01262   0.00583  -0.0908   0.6889   0.0297
  -5.750  -0.0840   0.01226   0.00525  -0.0904   0.6496   0.0316
  -5.500  -0.0597   0.01221   0.00474  -0.0896   0.5551   0.0334
  -5.250  -0.0363   0.01222   0.00421  -0.0888   0.4445   0.0360
  -5.000  -0.0149   0.01285   0.00403  -0.0880   0.2243   0.0392
  -4.750   0.0125   0.01266   0.00369  -0.0878   0.2075   0.0423
  -4.500   0.0401   0.01243   0.00344  -0.0876   0.1968   0.0497
  -4.250   0.0679   0.01234   0.00337  -0.0875   0.1873   0.0660
  -4.000   0.0958   0.01234   0.00329  -0.0874   0.1743   0.0801
  -3.750   0.1228   0.01249   0.00326  -0.0872   0.1278   0.0886
  -3.500   0.1504   0.01243   0.00317  -0.0871   0.1254   0.0956
  -3.250   0.1783   0.01243   0.00313  -0.0870   0.1235   0.1005
  -3.000   0.2061   0.01240   0.00306  -0.0869   0.1225   0.1055
  -2.750   0.2339   0.01238   0.00304  -0.0869   0.1217   0.1111
  -2.500   0.2617   0.01240   0.00302  -0.0868   0.1211   0.1159
  -2.250   0.2895   0.01235   0.00298  -0.0867   0.1207   0.1214
  -2.000   0.3173   0.01237   0.00299  -0.0866   0.1203   0.1289
  -1.750   0.3450   0.01236   0.00300  -0.0865   0.1198   0.1390
  -1.500   0.3726   0.01235   0.00301  -0.0865   0.1192   0.1529
  -1.250   0.4001   0.01235   0.00303  -0.0864   0.1188   0.1676
  -1.000   0.4277   0.01236   0.00305  -0.0863   0.1185   0.1806
  -0.750   0.4552   0.01237   0.00309  -0.0863   0.1184   0.1946
  -0.500   0.4825   0.01237   0.00315  -0.0862   0.1184   0.2151
  -0.250   0.5098   0.01233   0.00325  -0.0862   0.1183   0.2605
   0.000   0.5365   0.01206   0.00337  -0.0862   0.1183   0.4014
   0.250   0.5627   0.01075   0.00354  -0.0858   0.1183   1.0000
   0.500   0.5896   0.01092   0.00364  -0.0856   0.1183   1.0000
   0.750   0.6164   0.01109   0.00376  -0.0855   0.1184   1.0000
   1.000   0.6431   0.01127   0.00389  -0.0853   0.1184   1.0000
   1.250   0.6698   0.01146   0.00403  -0.0851   0.1185   1.0000
   1.500   0.6963   0.01166   0.00419  -0.0849   0.1186   1.0000
   1.750   0.7227   0.01186   0.00436  -0.0846   0.1187   1.0000
   2.000   0.7491   0.01207   0.00454  -0.0844   0.1188   1.0000
   2.250   0.7753   0.01229   0.00474  -0.0842   0.1190   1.0000
   2.500   0.8014   0.01252   0.00495  -0.0840   0.1191   1.0000
   2.750   0.8274   0.01275   0.00516  -0.0837   0.1193   1.0000
   3.000   0.8533   0.01298   0.00539  -0.0835   0.1194   1.0000
   3.250   0.8790   0.01323   0.00562  -0.0832   0.1196   1.0000
   3.500   0.9047   0.01348   0.00588  -0.0829   0.1198   1.0000
   3.750   0.9301   0.01373   0.00613  -0.0826   0.1200   1.0000
   4.000   0.9553   0.01401   0.00641  -0.0823   0.1201   1.0000
   4.250   0.9796   0.01437   0.00678  -0.0818   0.1196   1.0000
   4.500   1.0034   0.01477   0.00719  -0.0813   0.1190   1.0000
   4.750   1.0271   0.01518   0.00760  -0.0807   0.1186   1.0000
   5.000   1.0513   0.01552   0.00796  -0.0803   0.1186   1.0000
   5.250   1.0744   0.01597   0.00844  -0.0797   0.1181   1.0000
   5.500   1.0971   0.01646   0.00896  -0.0790   0.1166   1.0000
   5.750   1.1210   0.01678   0.00932  -0.0786   0.1149   1.0000
   6.000   1.1440   0.01721   0.00977  -0.0780   0.1137   1.0000
   6.250   1.1662   0.01770   0.01030  -0.0773   0.1120   1.0000
   6.500   1.1867   0.01841   0.01099  -0.0764   0.1094   1.0000
   6.750   1.2067   0.01937   0.01191  -0.0756   0.1075   1.0000
   7.000   1.2283   0.02017   0.01274  -0.0749   0.1056   1.0000
   7.250   1.2508   0.02019   0.01288  -0.0742   0.1033   1.0000
   7.500   1.2722   0.02051   0.01326  -0.0735   0.1003   1.0000
   7.750   1.2917   0.02117   0.01391  -0.0726   0.0970   1.0000
   8.000   1.3124   0.02126   0.01413  -0.0717   0.0930   1.0000
   8.250   1.3475   0.02002   0.01300  -0.0729   0.0836   1.0000
   8.750   1.3876   0.02094   0.01346  -0.0710   0.0198   1.0000
   9.000   1.4011   0.02168   0.01428  -0.0689   0.0179   1.0000
   9.250   1.4138   0.02248   0.01517  -0.0668   0.0169   1.0000
   9.500   1.4245   0.02345   0.01623  -0.0646   0.0159   1.0000
   9.750   1.4323   0.02464   0.01751  -0.0621   0.0150   1.0000
  10.000   1.4355   0.02621   0.01921  -0.0593   0.0141   1.0000
  10.250   1.4422   0.02757   0.02068  -0.0572   0.0137   1.0000
  10.500   1.4493   0.02897   0.02218  -0.0553   0.0134   1.0000
  10.750   1.4546   0.03056   0.02388  -0.0534   0.0130   1.0000
  11.000   1.4583   0.03235   0.02579  -0.0516   0.0127   1.0000
  11.250   1.4606   0.03436   0.02790  -0.0500   0.0124   1.0000
  11.500   1.4615   0.03658   0.03025  -0.0485   0.0121   1.0000
  11.750   1.4612   0.03905   0.03283  -0.0473   0.0118   1.0000
  12.000   1.4594   0.04178   0.03567  -0.0463   0.0116   1.0000
  12.250   1.4561   0.04481   0.03881  -0.0456   0.0114   1.0000
  12.500   1.4507   0.04816   0.04226  -0.0450   0.0112   1.0000
  12.750   1.4430   0.05188   0.04609  -0.0446   0.0110   1.0000
  13.000   1.4334   0.05592   0.05023  -0.0443   0.0108   1.0000
  13.250   1.4212   0.06034   0.05476  -0.0441   0.0106   1.0000
  13.500   1.4107   0.06466   0.05919  -0.0439   0.0105   1.0000
  13.750   1.4104   0.06809   0.06276  -0.0446   0.0103   1.0000
  14.000   1.4080   0.07182   0.06661  -0.0453   0.0102   1.0000
  14.250   1.4043   0.07580   0.07070  -0.0461   0.0100   1.0000
  14.500   1.3996   0.07995   0.07498  -0.0469   0.0099   1.0000
  14.750   1.3947   0.08419   0.07933  -0.0478   0.0098   1.0000
  15.000   1.3894   0.08853   0.08380  -0.0489   0.0097   1.0000
  15.250   1.3840   0.09298   0.08837  -0.0501   0.0096   1.0000
  15.500   1.3784   0.09752   0.09303  -0.0513   0.0095   1.0000
  15.750   1.3725   0.10215   0.09777  -0.0527   0.0094   1.0000
  16.000   1.3664   0.10689   0.10263  -0.0543   0.0093   1.0000
  16.250   1.3601   0.11175   0.10760  -0.0560   0.0092   1.0000
  16.500   1.3536   0.11674   0.11272  -0.0579   0.0092   1.0000
  16.750   1.3469   0.12188   0.11798  -0.0601   0.0091   1.0000
  17.000   1.3399   0.12716   0.12338  -0.0624   0.0090   1.0000
  17.250   1.3323   0.13265   0.12901  -0.0650   0.0090   1.0000
  17.500   1.3245   0.13838   0.13486  -0.0679   0.0090   1.0000
  17.750   1.3160   0.14441   0.14103  -0.0712   0.0089   1.0000
  18.000   1.3071   0.15071   0.14746  -0.0748   0.0089   1.0000
  18.250   1.2970   0.15748   0.15438  -0.0788   0.0089   1.0000
  18.500   1.2857   0.16474   0.16179  -0.0832   0.0090   1.0000
  18.750   1.2730   0.17258   0.16978  -0.0881   0.0090   1.0000
  19.000   1.2595   0.18103   0.17838  -0.0936   0.0091   1.0000
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