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FX 73-CL1-152 (fx73cl1152-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: FX 73-CL1-152 (fx73cl1152-il)
Reynolds number: 200,000
Max Cl/Cd: 68.67 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx73cl1152-il-200000-n5.txt
Download as CSV file: xf-fx73cl1152-il-200000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.0561   0.09410   0.08828  -0.0685   0.5438   0.0386
  -9.250  -0.0526   0.09093   0.08508  -0.0698   0.5379   0.0387
  -7.250  -0.1728   0.03209   0.02539  -0.1116   0.5190   0.0419
  -7.000  -0.1571   0.02877   0.02155  -0.1131   0.5139   0.0427
  -6.750  -0.1371   0.02628   0.01859  -0.1139   0.5087   0.0436
  -6.500  -0.1149   0.02431   0.01610  -0.1142   0.5032   0.0448
  -6.250  -0.0897   0.02378   0.01552  -0.1140   0.4978   0.0455
  -5.750  -0.0384   0.02253   0.01401  -0.1136   0.4890   0.0473
  -5.500  -0.0125   0.02169   0.01297  -0.1135   0.4847   0.0483
  -5.250   0.0135   0.02088   0.01190  -0.1132   0.4806   0.0494
  -5.000   0.0397   0.02020   0.01101  -0.1130   0.4769   0.0504
  -4.750   0.0663   0.01983   0.01059  -0.1127   0.4734   0.0514
  -4.500   0.0934   0.01947   0.01019  -0.1125   0.4694   0.0527
  -4.250   0.1205   0.01905   0.00966  -0.1122   0.4655   0.0543
  -4.000   0.1477   0.01861   0.00903  -0.1119   0.4621   0.0559
  -3.750   0.1745   0.01826   0.00865  -0.1116   0.4591   0.0571
  -3.500   0.2016   0.01801   0.00832  -0.1113   0.4563   0.0586
  -3.250   0.2291   0.01774   0.00800  -0.1111   0.4536   0.0607
  -3.000   0.2567   0.01746   0.00766  -0.1108   0.4507   0.0630
  -2.750   0.2841   0.01723   0.00744  -0.1106   0.4476   0.0651
  -2.500   0.3115   0.01702   0.00719  -0.1103   0.4446   0.0676
  -2.250   0.3389   0.01683   0.00691  -0.1100   0.4418   0.0703
  -2.000   0.3662   0.01669   0.00674  -0.1097   0.4393   0.0736
  -1.750   0.3938   0.01661   0.00658  -0.1094   0.4371   0.0776
  -1.500   0.4214   0.01644   0.00647  -0.1092   0.4347   0.0818
  -1.250   0.4490   0.01635   0.00635  -0.1089   0.4321   0.0871
  -1.000   0.4765   0.01623   0.00628  -0.1087   0.4293   0.0934
  -0.750   0.5040   0.01614   0.00619  -0.1084   0.4267   0.1009
  -0.500   0.5315   0.01608   0.00612  -0.1081   0.4242   0.1105
  -0.250   0.5589   0.01605   0.00608  -0.1079   0.4220   0.1230
   0.000   0.5863   0.01604   0.00609  -0.1076   0.4197   0.1401
   0.250   0.6136   0.01601   0.00616  -0.1074   0.4174   0.1634
   0.500   0.6409   0.01600   0.00624  -0.1071   0.4148   0.1890
   0.750   0.6681   0.01601   0.00633  -0.1068   0.4123   0.2155
   1.000   0.6952   0.01603   0.00640  -0.1065   0.4097   0.2411
   1.250   0.7222   0.01604   0.00647  -0.1062   0.4073   0.2669
   1.500   0.7492   0.01607   0.00655  -0.1059   0.4051   0.2968
   1.750   0.7761   0.01611   0.00665  -0.1056   0.4031   0.3331
   2.000   0.8027   0.01615   0.00679  -0.1053   0.4010   0.3840
   2.250   0.8283   0.01605   0.00699  -0.1048   0.3987   0.4634
   2.500   0.8515   0.01578   0.00722  -0.1037   0.3962   0.6211
   2.750   0.8883   0.01530   0.00732  -0.1050   0.3935   1.0000
   3.000   0.9153   0.01550   0.00745  -0.1048   0.3913   1.0000
   3.250   0.9424   0.01570   0.00758  -0.1045   0.3892   1.0000
   3.500   0.9693   0.01591   0.00771  -0.1042   0.3871   1.0000
   3.750   0.9964   0.01614   0.00784  -0.1039   0.3851   1.0000
   4.000   1.0230   0.01639   0.00804  -0.1036   0.3829   1.0000
   4.250   1.0489   0.01662   0.00829  -0.1032   0.3804   1.0000
   4.500   1.0750   0.01685   0.00852  -0.1028   0.3778   1.0000
   4.750   1.1010   0.01709   0.00875  -0.1024   0.3755   1.0000
   5.000   1.1271   0.01733   0.00897  -0.1020   0.3732   1.0000
   5.250   1.1531   0.01756   0.00917  -0.1016   0.3712   1.0000
   5.500   1.1792   0.01781   0.00937  -0.1013   0.3693   1.0000
   5.750   1.2056   0.01809   0.00958  -0.1010   0.3673   1.0000
   6.000   1.2301   0.01838   0.00993  -0.1004   0.3649   1.0000
   6.250   1.2545   0.01867   0.01028  -0.0998   0.3621   1.0000
   6.500   1.2790   0.01895   0.01059  -0.0993   0.3595   1.0000
   6.750   1.3036   0.01922   0.01088  -0.0987   0.3570   1.0000
   7.000   1.3283   0.01950   0.01115  -0.0982   0.3549   1.0000
   7.250   1.3531   0.01977   0.01141  -0.0977   0.3530   1.0000
   7.500   1.3783   0.02007   0.01167  -0.0973   0.3511   1.0000
   7.750   1.4010   0.02045   0.01213  -0.0966   0.3488   1.0000
   8.000   1.4232   0.02084   0.01261  -0.0958   0.3462   1.0000
   8.250   1.4455   0.02121   0.01304  -0.0950   0.3436   1.0000
   8.500   1.4678   0.02154   0.01341  -0.0942   0.3410   1.0000
   8.750   1.4903   0.02184   0.01374  -0.0935   0.3387   1.0000
   9.000   1.5132   0.02216   0.01405  -0.0928   0.3367   1.0000
   9.250   1.5369   0.02250   0.01436  -0.0922   0.3349   1.0000
   9.500   1.5551   0.02303   0.01503  -0.0910   0.3324   1.0000
   9.750   1.5736   0.02354   0.01566  -0.0897   0.3299   1.0000
  10.000   1.5919   0.02402   0.01622  -0.0885   0.3274   1.0000
  10.250   1.6103   0.02446   0.01672  -0.0873   0.3250   1.0000
  10.500   1.6288   0.02486   0.01715  -0.0860   0.3227   1.0000
  10.750   1.6484   0.02524   0.01754  -0.0850   0.3208   1.0000
  11.000   1.6665   0.02572   0.01804  -0.0837   0.3189   1.0000
  11.250   1.6747   0.02647   0.01894  -0.0812   0.3165   1.0000
  11.500   1.6831   0.02723   0.01983  -0.0788   0.3141   1.0000
  11.750   1.6919   0.02798   0.02068  -0.0766   0.3117   1.0000
  12.000   1.7014   0.02872   0.02149  -0.0746   0.3093   1.0000
  12.250   1.7130   0.02942   0.02223  -0.0729   0.3072   1.0000
  12.500   1.7280   0.03004   0.02287  -0.0717   0.3054   1.0000
  12.750   1.7367   0.03102   0.02394  -0.0701   0.3033   1.0000
  13.000   1.7316   0.03283   0.02593  -0.0678   0.3005   1.0000
  13.250   1.7283   0.03473   0.02797  -0.0660   0.2976   1.0000
  13.500   1.7285   0.03654   0.02989  -0.0648   0.2949   1.0000
  13.750   1.7350   0.03794   0.03132  -0.0639   0.2921   1.0000
  14.000   1.7536   0.03839   0.03174  -0.0633   0.2895   1.0000
  14.250   1.7251   0.04308   0.03669  -0.0624   0.2856   1.0000
  14.500   1.7038   0.04759   0.04136  -0.0622   0.2816   1.0000
  14.750   1.7000   0.05044   0.04428  -0.0621   0.2783   1.0000
  15.000   1.7169   0.05106   0.04489  -0.0615   0.2758   1.0000
  15.250   1.6732   0.05867   0.05271  -0.0625   0.2712   1.0000
  15.500   1.6146   0.06875   0.06299  -0.0645   0.2650   1.0000
  15.750   1.6386   0.06842   0.06264  -0.0639   0.2623   1.0000
  16.000   1.4997   0.09083   0.08535  -0.0702   0.2501   1.0000
  16.250   1.5329   0.08905   0.08357  -0.0691   0.2486   1.0000
  16.500   1.5969   0.08279   0.07722  -0.0668   0.2467   1.0000
  16.750   1.4675   0.10541   0.10012  -0.0740   0.2342   1.0000
  17.000   1.5236   0.09989   0.09454  -0.0718   0.2329   1.0000
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