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FX 61-147 AIRFOIL (fx61147-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: FX 61-147 AIRFOIL (fx61147-il)
Reynolds number: 200,000
Max Cl/Cd: 71.87 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx61147-il-200000-n5.txt
Download as CSV file: xf-fx61147-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 61-147 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4443   0.07016   0.06676  -0.0588   1.0000   0.0089
  -9.750  -0.4692   0.06435   0.06090  -0.0611   1.0000   0.0088
  -9.500  -0.4858   0.06152   0.05807  -0.0609   1.0000   0.0087
  -9.250  -0.4988   0.05558   0.05195  -0.0664   0.9954   0.0087
  -9.000  -0.5103   0.04925   0.04531  -0.0723   0.9844   0.0086
  -8.750  -0.5090   0.04283   0.03844  -0.0776   0.9729   0.0087
  -8.500  -0.5032   0.03643   0.03136  -0.0806   0.9631   0.0088
  -8.250  -0.4893   0.03257   0.02704  -0.0815   0.9537   0.0090
  -8.000  -0.4617   0.03019   0.02438  -0.0839   0.9491   0.0094
  -7.750  -0.4398   0.02838   0.02235  -0.0843   0.9403   0.0097
  -7.500  -0.4092   0.02647   0.02017  -0.0861   0.9358   0.0105
  -7.250  -0.3845   0.02479   0.01819  -0.0862   0.9272   0.0115
  -7.000  -0.3525   0.02322   0.01640  -0.0878   0.9220   0.0130
  -6.750  -0.3239   0.02217   0.01522  -0.0885   0.9135   0.0142
  -6.500  -0.2896   0.02071   0.01357  -0.0901   0.9078   0.0156
  -6.250  -0.2588   0.01951   0.01224  -0.0910   0.8991   0.0174
  -6.000  -0.2200   0.01867   0.01137  -0.0938   0.8925   0.0200
  -5.750  -0.1865   0.01779   0.01037  -0.0952   0.8820   0.0222
  -5.500  -0.1487   0.01679   0.00933  -0.0979   0.8722   0.0254
  -5.250  -0.1082   0.01593   0.00837  -0.1010   0.8619   0.0282
  -5.000  -0.0703   0.01515   0.00749  -0.1037   0.8485   0.0322
  -4.750  -0.0328   0.01453   0.00675  -0.1061   0.8334   0.0376
  -4.500   0.0031   0.01393   0.00606  -0.1083   0.8171   0.0467
  -4.250   0.0369   0.01338   0.00548  -0.1100   0.7999   0.0699
  -4.000   0.0700   0.01235   0.00487  -0.1124   0.7821   0.1831
  -3.750   0.1047   0.01088   0.00439  -0.1158   0.7643   0.4479
  -3.500   0.1332   0.01082   0.00460  -0.1158   0.7468   0.5529
  -3.250   0.1607   0.01108   0.00482  -0.1152   0.7300   0.5985
  -3.000   0.1869   0.01151   0.00514  -0.1143   0.7134   0.6294
  -2.750   0.2130   0.01186   0.00535  -0.1134   0.6978   0.6452
  -2.500   0.2402   0.01204   0.00536  -0.1131   0.6833   0.6530
  -2.250   0.2678   0.01215   0.00531  -0.1130   0.6698   0.6590
  -2.000   0.2943   0.01229   0.00532  -0.1126   0.6570   0.6635
  -1.750   0.3226   0.01237   0.00525  -0.1128   0.6448   0.6695
  -1.500   0.3499   0.01248   0.00523  -0.1126   0.6336   0.6737
  -1.250   0.3763   0.01261   0.00525  -0.1123   0.6234   0.6773
  -1.000   0.4039   0.01271   0.00524  -0.1123   0.6132   0.6819
  -0.750   0.4329   0.01278   0.00518  -0.1127   0.6034   0.6871
  -0.250   0.4857   0.01301   0.00527  -0.1120   0.5851   0.6931
   0.000   0.5134   0.01311   0.00528  -0.1121   0.5767   0.6971
   0.250   0.5426   0.01319   0.00526  -0.1126   0.5677   0.7017
   0.500   0.5687   0.01330   0.00533  -0.1123   0.5596   0.7041
   0.750   0.5952   0.01342   0.00541  -0.1120   0.5519   0.7068
   1.000   0.6224   0.01352   0.00548  -0.1120   0.5444   0.7102
   1.250   0.6507   0.01363   0.00552  -0.1123   0.5371   0.7142
   1.500   0.6786   0.01374   0.00559  -0.1125   0.5301   0.7174
   1.750   0.7048   0.01386   0.00571  -0.1122   0.5233   0.7198
   2.000   0.7316   0.01399   0.00582  -0.1121   0.5172   0.7224
   2.250   0.7589   0.01410   0.00593  -0.1121   0.5103   0.7255
   2.500   0.7869   0.01425   0.00603  -0.1124   0.5041   0.7290
   2.750   0.8146   0.01436   0.00615  -0.1126   0.4971   0.7320
   3.000   0.8404   0.01451   0.00629  -0.1123   0.4908   0.7341
   3.250   0.8668   0.01463   0.00647  -0.1121   0.4840   0.7365
   3.500   0.8933   0.01479   0.00663  -0.1120   0.4777   0.7394
   3.750   0.9206   0.01494   0.00679  -0.1121   0.4715   0.7424
   4.000   0.9485   0.01510   0.00698  -0.1124   0.4649   0.7456
   4.250   0.9740   0.01527   0.00717  -0.1121   0.4595   0.7477
   4.500   0.9998   0.01542   0.00740  -0.1118   0.4530   0.7500
   4.750   1.0256   0.01560   0.00761  -0.1116   0.4470   0.7525
   5.000   1.0520   0.01578   0.00786  -0.1115   0.4409   0.7552
   5.250   1.0786   0.01597   0.00811  -0.1115   0.4348   0.7583
   5.500   1.1050   0.01620   0.00835  -0.1115   0.4295   0.7610
   5.750   1.1298   0.01637   0.00866  -0.1111   0.4228   0.7630
   6.000   1.1544   0.01659   0.00893  -0.1107   0.4169   0.7654
   6.250   1.1796   0.01681   0.00925  -0.1104   0.4107   0.7680
   6.500   1.2044   0.01704   0.00956  -0.1100   0.4040   0.7708
   6.750   1.2289   0.01728   0.00988  -0.1097   0.3955   0.7736
   7.000   1.2515   0.01753   0.01017  -0.1089   0.3865   0.7761
   7.250   1.2733   0.01775   0.01051  -0.1080   0.3758   0.7784
   7.500   1.2944   0.01801   0.01084  -0.1070   0.3643   0.7809
   7.750   1.3154   0.01831   0.01121  -0.1060   0.3535   0.7835
   8.000   1.3355   0.01865   0.01161  -0.1049   0.3416   0.7864
   8.500   1.3698   0.01944   0.01248  -0.1016   0.3061   0.7918
   8.750   1.3812   0.01996   0.01298  -0.0991   0.2856   0.7944
   9.000   1.3922   0.02058   0.01358  -0.0965   0.2622   0.7972
   9.250   1.4005   0.02141   0.01433  -0.0937   0.2358   0.8004
   9.500   1.4056   0.02249   0.01531  -0.0907   0.2050   0.8039
   9.750   1.4054   0.02383   0.01650  -0.0870   0.1708   0.8066
  10.000   1.4031   0.02542   0.01795  -0.0834   0.1400   0.8097
  10.250   1.4011   0.02713   0.01956  -0.0803   0.1153   0.8128
  10.500   1.4002   0.02892   0.02129  -0.0775   0.0952   0.8161
  10.750   1.3995   0.03078   0.02315  -0.0751   0.0801   0.8194
  11.250   1.3957   0.03497   0.02738  -0.0709   0.0566   0.8264
  11.500   1.3939   0.03734   0.02979  -0.0694   0.0468   0.8303
  11.750   1.3913   0.03993   0.03242  -0.0682   0.0385   0.8338
  12.000   1.3879   0.04270   0.03525  -0.0672   0.0323   0.8373
  12.250   1.3843   0.04568   0.03830  -0.0665   0.0273   0.8412
  12.500   1.3824   0.04868   0.04139  -0.0662   0.0234   0.8457
  12.750   1.3786   0.05195   0.04479  -0.0659   0.0201   0.8502
  13.000   1.3759   0.05520   0.04818  -0.0659   0.0175   0.8555
  13.250   1.3717   0.05878   0.05188  -0.0660   0.0148   0.8612
  13.500   1.3668   0.06245   0.05568  -0.0662   0.0127   0.8677
  14.000   1.3544   0.07025   0.06375  -0.0669   0.0097   0.8868
  14.250   1.3446   0.07362   0.06732  -0.0661   0.0089   0.9376
  14.500   1.3400   0.07787   0.07171  -0.0673   0.0081   1.0000
  14.750   1.3356   0.08238   0.07634  -0.0687   0.0075   1.0000
  15.000   1.3303   0.08711   0.08118  -0.0703   0.0070   1.0000
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