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FX 63-158 AIRFOIL (fx63158-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: FX 63-158 AIRFOIL (fx63158-il)
Reynolds number: 200,000
Max Cl/Cd: 67.88 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx63158-il-200000-n5.txt
Download as CSV file: xf-fx63158-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 63-158 AIRFOIL                               
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3302   0.05602   0.05227  -0.0897   0.9262   0.0144
  -8.500  -0.3242   0.05182   0.04791  -0.0947   0.9054   0.0141
  -8.000  -0.2889   0.03808   0.03286  -0.1094   0.8657   0.0115
  -7.750  -0.2539   0.03459   0.02899  -0.1147   0.8422   0.0114
  -7.500  -0.2221   0.03140   0.02533  -0.1184   0.8183   0.0113
  -7.250  -0.1952   0.02893   0.02241  -0.1200   0.7944   0.0112
  -7.000  -0.1703   0.02694   0.02000  -0.1206   0.7732   0.0111
  -6.500  -0.1237   0.02372   0.01603  -0.1199   0.7370   0.0111
  -6.250  -0.1001   0.02241   0.01443  -0.1192   0.7229   0.0113
  -6.000  -0.0765   0.02132   0.01309  -0.1184   0.7104   0.0114
  -5.750  -0.0531   0.02038   0.01198  -0.1176   0.6987   0.0117
  -5.500  -0.0302   0.01962   0.01114  -0.1168   0.6877   0.0120
  -5.250  -0.0068   0.01899   0.01042  -0.1162   0.6781   0.0126
  -5.000   0.0171   0.01847   0.00978  -0.1157   0.6695   0.0138
  -4.750   0.0410   0.01794   0.00914  -0.1152   0.6606   0.0151
  -4.500   0.0644   0.01735   0.00850  -0.1148   0.6508   0.0159
  -4.250   0.0891   0.01677   0.00786  -0.1147   0.6416   0.0164
  -3.750   0.1417   0.01583   0.00667  -0.1151   0.6222   0.0178
  -3.500   0.1692   0.01541   0.00609  -0.1156   0.6132   0.0190
  -3.250   0.1974   0.01507   0.00564  -0.1161   0.6040   0.0209
  -3.000   0.2260   0.01477   0.00529  -0.1166   0.5957   0.0256
  -2.750   0.2553   0.01450   0.00493  -0.1172   0.5873   0.0439
  -2.500   0.2869   0.01393   0.00460  -0.1189   0.5801   0.1371
  -2.250   0.3286   0.01244   0.00423  -0.1241   0.5727   0.4430
  -2.000   0.3533   0.01256   0.00488  -0.1231   0.5653   0.5790
  -1.750   0.3807   0.01274   0.00500  -0.1229   0.5575   0.6054
  -1.500   0.4102   0.01284   0.00491  -0.1234   0.5490   0.6201
  -1.250   0.4379   0.01299   0.00496  -0.1233   0.5409   0.6318
  -1.000   0.4649   0.01318   0.00507  -0.1231   0.5330   0.6423
  -0.750   0.4934   0.01335   0.00511  -0.1233   0.5269   0.6522
  -0.500   0.5211   0.01346   0.00519  -0.1232   0.5212   0.6569
  -0.250   0.5480   0.01359   0.00528  -0.1230   0.5154   0.6612
   0.000   0.5764   0.01372   0.00533  -0.1232   0.5104   0.6669
   0.250   0.6046   0.01384   0.00543  -0.1233   0.5052   0.6732
   0.500   0.6297   0.01404   0.00563  -0.1226   0.5003   0.6793
   0.750   0.6580   0.01423   0.00575  -0.1227   0.4955   0.6887
   1.000   0.6803   0.01447   0.00605  -0.1213   0.4909   0.6949
   1.250   0.7078   0.01467   0.00621  -0.1212   0.4861   0.7034
   1.500   0.7326   0.01482   0.00636  -0.1205   0.4816   0.7078
   1.750   0.7572   0.01497   0.00650  -0.1199   0.4773   0.7110
   2.000   0.7843   0.01506   0.00661  -0.1198   0.4722   0.7140
   2.250   0.8120   0.01516   0.00670  -0.1200   0.4663   0.7172
   2.500   0.8404   0.01527   0.00675  -0.1204   0.4606   0.7203
   2.750   0.8701   0.01533   0.00684  -0.1211   0.4544   0.7227
   3.000   0.8964   0.01541   0.00695  -0.1210   0.4473   0.7239
   3.250   0.9226   0.01550   0.00706  -0.1209   0.4405   0.7253
   3.500   0.9489   0.01561   0.00719  -0.1207   0.4332   0.7268
   3.750   0.9747   0.01573   0.00733  -0.1206   0.4261   0.7285
   4.000   1.0002   0.01588   0.00746  -0.1204   0.4172   0.7303
   4.250   1.0256   0.01605   0.00760  -0.1202   0.4080   0.7319
   4.500   1.0516   0.01622   0.00777  -0.1202   0.3977   0.7335
   4.750   1.0783   0.01638   0.00797  -0.1203   0.3891   0.7350
   5.000   1.1048   0.01656   0.00818  -0.1204   0.3768   0.7369
   5.250   1.1300   0.01681   0.00840  -0.1203   0.3636   0.7388
   5.500   1.1530   0.01709   0.00866  -0.1198   0.3527   0.7401
   5.750   1.1753   0.01738   0.00894  -0.1190   0.3433   0.7412
   6.000   1.1981   0.01765   0.00925  -0.1184   0.3320   0.7423
   6.250   1.2194   0.01800   0.00962  -0.1176   0.3098   0.7435
   6.500   1.2350   0.01860   0.01010  -0.1158   0.2900   0.7448
   6.750   1.2533   0.01909   0.01057  -0.1146   0.2751   0.7462
   7.000   1.2688   0.01969   0.01114  -0.1129   0.2455   0.7476
   7.250   1.2787   0.02046   0.01180  -0.1103   0.2294   0.7492
   7.500   1.2946   0.02100   0.01237  -0.1087   0.2183   0.7507
   7.750   1.3133   0.02145   0.01290  -0.1076   0.2013   0.7523
   8.000   1.3220   0.02240   0.01377  -0.1051   0.1844   0.7540
   8.250   1.3348   0.02317   0.01456  -0.1033   0.1782   0.7559
   8.500   1.3447   0.02403   0.01545  -0.1011   0.1721   0.7575
   8.750   1.3601   0.02461   0.01617  -0.0996   0.1630   0.7590
   9.000   1.3679   0.02564   0.01724  -0.0974   0.1418   0.7606
   9.250   1.3709   0.02701   0.01859  -0.0948   0.1337   0.7621
   9.500   1.3764   0.02832   0.01995  -0.0927   0.1289   0.7639
   9.750   1.3843   0.02956   0.02129  -0.0910   0.1246   0.7659
  10.000   1.3947   0.03073   0.02260  -0.0897   0.1175   0.7679
  10.250   1.3999   0.03235   0.02429  -0.0882   0.0998   0.7698
  10.500   1.3977   0.03469   0.02660  -0.0866   0.0940   0.7714
  10.750   1.3963   0.03716   0.02907  -0.0853   0.0898   0.7731
  11.000   1.3993   0.03934   0.03138  -0.0845   0.0852   0.7745
  11.750   1.4022   0.04700   0.03921  -0.0826   0.0612   0.7791
  12.000   1.3984   0.05027   0.04250  -0.0823   0.0580   0.7807
  12.250   1.3974   0.05335   0.04569  -0.0821   0.0555   0.7824
  12.500   1.3946   0.05674   0.04920  -0.0821   0.0535   0.7841
  12.750   1.3898   0.06047   0.05303  -0.0822   0.0518   0.7860
  13.000   1.3911   0.06356   0.05625  -0.0825   0.0502   0.7881
  13.250   1.3975   0.06610   0.05896  -0.0828   0.0481   0.7903
  13.500   1.4013   0.06897   0.06199  -0.0831   0.0460   0.7922
  13.750   1.4029   0.07215   0.06531  -0.0835   0.0441   0.7939
  14.000   1.4098   0.07467   0.06799  -0.0839   0.0418   0.7959
  14.250   1.4162   0.07732   0.07081  -0.0844   0.0386   0.7980
  14.500   1.4202   0.08033   0.07394  -0.0850   0.0359   0.8001
  14.750   1.4233   0.08354   0.07720  -0.0857   0.0338   0.8024
  15.000   1.4253   0.08695   0.08066  -0.0866   0.0319   0.8047
  15.250   1.4262   0.09059   0.08435  -0.0876   0.0303   0.8070
  15.500   1.4275   0.09418   0.08807  -0.0886   0.0290   0.8091
  15.750   1.4285   0.09778   0.09180  -0.0896   0.0276   0.8113
  16.000   1.4285   0.10162   0.09576  -0.0908   0.0260   0.8137
  16.250   1.4273   0.10569   0.09992  -0.0921   0.0247   0.8162
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