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FX 73-CL1-152 (fx73cl1152-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: FX 73-CL1-152 (fx73cl1152-il)
Reynolds number: 200,000
Max Cl/Cd: 53.26 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx73cl1152-il-200000.txt
Download as CSV file: xf-fx73cl1152-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 73-CL1-152                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.0367   0.10547   0.10035  -0.0661   0.6394   0.0660
  -9.750  -0.0300   0.10307   0.09784  -0.0672   0.6279   0.0677
  -9.500  -0.0584   0.10121   0.09605  -0.0735   0.6248   0.0699
  -9.250  -0.0390   0.09774   0.09245  -0.0724   0.6122   0.0703
  -9.000  -0.0181   0.09501   0.08966  -0.0713   0.6005   0.0711
  -8.750  -0.0048   0.09282   0.08736  -0.0712   0.5917   0.0721
  -8.500   0.0054   0.09065   0.08519  -0.0716   0.5838   0.0739
  -8.250   0.0087   0.08838   0.08290  -0.0730   0.5778   0.0765
  -8.000  -0.0132   0.08513   0.07970  -0.0778   0.5753   0.0785
  -7.750   0.0088   0.08275   0.07724  -0.0763   0.5683   0.0792
  -7.500   0.0242   0.08067   0.07515  -0.0757   0.5617   0.0803
  -7.250   0.0347   0.07863   0.07308  -0.0758   0.5565   0.0818
  -7.000   0.0405   0.07650   0.07090  -0.0765   0.5522   0.0840
  -6.750  -0.0042   0.07235   0.06688  -0.0859   0.5524   0.0876
  -6.500   0.0168   0.07034   0.06488  -0.0817   0.5466   0.0882
  -6.250   0.0342   0.06862   0.06315  -0.0800   0.5412   0.0892
  -6.000   0.0482   0.06694   0.06142  -0.0795   0.5367   0.0907
  -5.750   0.0375   0.05995   0.05436  -0.0955   0.5356   0.0982
  -5.500   0.0546   0.05891   0.05330  -0.0917   0.5311   0.0990
  -5.250   0.0715   0.05770   0.05213  -0.0896   0.5267   0.1002
  -5.000   0.0665   0.03661   0.03009  -0.1111   0.5278   0.0790
  -4.750   0.0877   0.03325   0.02649  -0.1122   0.5239   0.0762
  -4.500   0.1093   0.02925   0.02195  -0.1138   0.5204   0.0757
  -4.250   0.1336   0.02655   0.01876  -0.1144   0.5170   0.0757
  -4.000   0.1595   0.02474   0.01647  -0.1146   0.5138   0.0763
  -3.750   0.1863   0.02358   0.01489  -0.1145   0.5105   0.0778
  -3.500   0.2123   0.02248   0.01372  -0.1144   0.5066   0.0798
  -3.250   0.2393   0.02192   0.01312  -0.1141   0.5027   0.0819
  -3.000   0.2668   0.02128   0.01230  -0.1139   0.4992   0.0840
  -2.750   0.2948   0.02076   0.01152  -0.1136   0.4962   0.0864
  -2.500   0.3223   0.02028   0.01092  -0.1135   0.4933   0.0895
  -2.250   0.3493   0.01995   0.01065  -0.1132   0.4904   0.0930
  -2.000   0.3768   0.01964   0.01025  -0.1128   0.4870   0.0967
  -1.750   0.4039   0.01915   0.00978  -0.1125   0.4836   0.1007
  -1.500   0.4315   0.01897   0.00957  -0.1122   0.4805   0.1065
  -1.250   0.4592   0.01867   0.00924  -0.1120   0.4779   0.1128
  -1.000   0.4872   0.01868   0.00917  -0.1118   0.4752   0.1208
  -0.750   0.5138   0.01850   0.00911  -0.1114   0.4724   0.1309
  -0.500   0.5404   0.01835   0.00907  -0.1110   0.4692   0.1434
  -0.250   0.5674   0.01827   0.00908  -0.1107   0.4661   0.1608
   0.000   0.5948   0.01823   0.00907  -0.1104   0.4632   0.1859
   0.250   0.6222   0.01815   0.00910  -0.1102   0.4605   0.2201
   0.500   0.6499   0.01817   0.00917  -0.1100   0.4579   0.2586
   0.750   0.6769   0.01836   0.00944  -0.1098   0.4553   0.2962
   1.000   0.7025   0.01838   0.00966  -0.1093   0.4527   0.3348
   1.250   0.7282   0.01840   0.00988  -0.1088   0.4497   0.3823
   1.500   0.7534   0.01830   0.01008  -0.1082   0.4466   0.4556
   1.750   0.7757   0.01791   0.01027  -0.1069   0.4439   0.6377
   2.000   0.8143   0.01746   0.01028  -0.1084   0.4412   1.0000
   2.250   0.8427   0.01781   0.01045  -0.1084   0.4389   1.0000
   2.500   0.8695   0.01829   0.01084  -0.1081   0.4365   1.0000
   2.750   0.8948   0.01860   0.01117  -0.1076   0.4337   1.0000
   3.000   0.9206   0.01892   0.01147  -0.1072   0.4305   1.0000
   3.250   0.9470   0.01919   0.01169  -0.1068   0.4275   1.0000
   3.500   0.9740   0.01944   0.01186  -0.1065   0.4247   1.0000
   3.750   1.0018   0.01971   0.01203  -0.1064   0.4224   1.0000
   4.000   1.0299   0.02013   0.01233  -0.1063   0.4202   1.0000
   4.250   1.0544   0.02065   0.01287  -0.1058   0.4176   1.0000
   4.500   1.0780   0.02108   0.01338  -0.1051   0.4146   1.0000
   4.750   1.1025   0.02149   0.01381  -0.1046   0.4116   1.0000
   5.000   1.1281   0.02181   0.01412  -0.1042   0.4087   1.0000
   5.250   1.1547   0.02206   0.01432  -0.1039   0.4061   1.0000
   5.500   1.1826   0.02232   0.01449  -0.1038   0.4039   1.0000
   5.750   1.2107   0.02288   0.01493  -0.1039   0.4016   1.0000
   6.000   1.2306   0.02343   0.01565  -0.1027   0.3986   1.0000
   6.250   1.2523   0.02399   0.01630  -0.1019   0.3954   1.0000
   6.500   1.2756   0.02446   0.01681  -0.1013   0.3925   1.0000
   6.750   1.3004   0.02482   0.01718  -0.1008   0.3900   1.0000
   7.000   1.3266   0.02513   0.01746  -0.1005   0.3878   1.0000
   7.250   1.3545   0.02543   0.01768  -0.1005   0.3858   1.0000
   7.500   1.3798   0.02606   0.01830  -0.1002   0.3834   1.0000
   7.750   1.3945   0.02685   0.01929  -0.0986   0.3800   1.0000
   8.000   1.4137   0.02753   0.02007  -0.0975   0.3769   1.0000
   8.250   1.4353   0.02806   0.02066  -0.0967   0.3742   1.0000
   8.500   1.4595   0.02845   0.02106  -0.0963   0.3720   1.0000
   8.750   1.4853   0.02878   0.02137  -0.0960   0.3701   1.0000
   9.000   1.5135   0.02912   0.02166  -0.0961   0.3683   1.0000
   9.250   1.5317   0.03003   0.02265  -0.0950   0.3658   1.0000
   9.500   1.5379   0.03126   0.02412  -0.0925   0.3623   1.0000
   9.750   1.5518   0.03218   0.02515  -0.0910   0.3594   1.0000
  10.000   1.5699   0.03285   0.02589  -0.0899   0.3570   1.0000
  10.250   1.5925   0.03328   0.02634  -0.0893   0.3550   1.0000
  10.500   1.6184   0.03356   0.02662  -0.0891   0.3533   1.0000
  10.750   1.6488   0.03376   0.02678  -0.0894   0.3517   1.0000
  11.000   1.6509   0.03533   0.02853  -0.0867   0.3489   1.0000
  11.250   1.6269   0.03794   0.03143  -0.0813   0.3452   1.0000
  11.500   1.6113   0.03992   0.03355  -0.0767   0.3424   1.0000
  11.750   1.6168   0.04096   0.03465  -0.0745   0.3401   1.0000
  12.000   1.6463   0.04086   0.03454  -0.0746   0.3384   1.0000
  12.250   1.6840   0.04048   0.03415  -0.0754   0.3369   1.0000
  12.500   1.7302   0.04008   0.03369  -0.0774   0.3354   1.0000
  12.750   1.0332   0.12777   0.12224  -0.0891   0.2775   1.0000
  13.000   1.0606   0.12704   0.12153  -0.0880   0.2764   1.0000
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