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FX 61-147 AIRFOIL (fx61147-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: FX 61-147 AIRFOIL (fx61147-il)
Reynolds number: 500,000
Max Cl/Cd: 99.21 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx61147-il-500000.txt
Download as CSV file: xf-fx61147-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4052   0.08401   0.08198  -0.0480   1.0000   0.0179
  -9.500  -0.4417   0.07219   0.07016  -0.0551   1.0000   0.0176
  -9.250  -0.4540   0.06393   0.06177  -0.0646   0.9970   0.0177
  -9.000  -0.4596   0.05766   0.05534  -0.0726   0.9911   0.0177
  -8.750  -0.4563   0.05285   0.05038  -0.0795   0.9838   0.0180
  -8.250  -0.4611   0.03106   0.02702  -0.0899   0.9649   0.0130
  -8.000  -0.4278   0.02972   0.02566  -0.0930   0.9629   0.0136
  -7.750  -0.4012   0.03088   0.02687  -0.0939   0.9553   0.0179
  -7.500  -0.3799   0.02163   0.01647  -0.0945   0.9516   0.0128
  -7.250  -0.3453   0.02017   0.01495  -0.0968   0.9495   0.0137
  -7.000  -0.3199   0.01929   0.01400  -0.0968   0.9416   0.0145
  -6.750  -0.2862   0.01775   0.01229  -0.0982   0.9380   0.0151
  -6.500  -0.2501   0.01631   0.01071  -0.1000   0.9347   0.0158
  -6.250  -0.2197   0.01542   0.00970  -0.1006   0.9260   0.0166
  -6.000  -0.1799   0.01376   0.00798  -0.1037   0.9215   0.0181
  -5.750  -0.1427   0.01308   0.00727  -0.1061   0.9120   0.0200
  -5.500  -0.0955   0.01240   0.00651  -0.1106   0.9048   0.0229
  -5.250  -0.0530   0.01157   0.00563  -0.1143   0.8928   0.0264
  -5.000  -0.0143   0.01121   0.00517  -0.1168   0.8775   0.0295
  -4.750   0.0199   0.01057   0.00445  -0.1187   0.8593   0.0357
  -4.500   0.0519   0.01015   0.00395  -0.1198   0.8387   0.0456
  -4.250   0.0827   0.00952   0.00343  -0.1211   0.8174   0.0981
  -4.000   0.1148   0.00790   0.00275  -0.1242   0.7953   0.3725
  -3.750   0.1460   0.00735   0.00258  -0.1256   0.7741   0.5200
  -3.500   0.1738   0.00735   0.00259  -0.1255   0.7538   0.5680
  -3.250   0.2009   0.00746   0.00261  -0.1253   0.7338   0.5962
  -3.000   0.2273   0.00766   0.00273  -0.1247   0.7150   0.6187
  -2.750   0.2538   0.00791   0.00287  -0.1242   0.6978   0.6369
  -2.500   0.2798   0.00820   0.00306  -0.1236   0.6821   0.6504
  -2.250   0.3058   0.00846   0.00323  -0.1229   0.6673   0.6603
  -2.000   0.3325   0.00867   0.00332  -0.1226   0.6533   0.6675
  -1.750   0.3597   0.00879   0.00334  -0.1224   0.6402   0.6723
  -1.500   0.3861   0.00892   0.00342  -0.1220   0.6280   0.6760
  -1.250   0.4133   0.00905   0.00346  -0.1218   0.6167   0.6802
  -1.000   0.4417   0.00918   0.00346  -0.1220   0.6059   0.6852
  -0.750   0.4681   0.00928   0.00351  -0.1217   0.5957   0.6880
  -0.500   0.4951   0.00938   0.00358  -0.1215   0.5863   0.6910
  -0.250   0.5223   0.00952   0.00363  -0.1213   0.5777   0.6946
   0.000   0.5507   0.00961   0.00366  -0.1215   0.5687   0.6988
   0.250   0.5781   0.00970   0.00370  -0.1215   0.5607   0.7020
   0.500   0.6050   0.00980   0.00378  -0.1213   0.5528   0.7044
   0.750   0.6321   0.00991   0.00386  -0.1212   0.5456   0.7071
   1.000   0.6597   0.01001   0.00392  -0.1212   0.5379   0.7104
   1.250   0.6880   0.01013   0.00397  -0.1214   0.5310   0.7140
   1.500   0.7156   0.01020   0.00403  -0.1215   0.5238   0.7166
   1.750   0.7422   0.01032   0.00412  -0.1212   0.5171   0.7189
   2.000   0.7692   0.01040   0.00422  -0.1211   0.5099   0.7214
   2.250   0.7962   0.01056   0.00432  -0.1210   0.5035   0.7243
   2.500   0.8242   0.01062   0.00441  -0.1212   0.4968   0.7274
   2.750   0.8521   0.01076   0.00449  -0.1214   0.4905   0.7304
   3.000   0.8789   0.01084   0.00460  -0.1212   0.4846   0.7324
   3.250   0.9056   0.01094   0.00472  -0.1211   0.4784   0.7346
   3.500   0.9322   0.01110   0.00486  -0.1210   0.4726   0.7370
   3.750   0.9594   0.01118   0.00498  -0.1210   0.4663   0.7398
   4.000   0.9867   0.01133   0.00511  -0.1210   0.4606   0.7425
   4.250   1.0144   0.01146   0.00525  -0.1212   0.4549   0.7451
   4.500   1.0406   0.01155   0.00539  -0.1210   0.4488   0.7471
   4.750   1.0665   0.01172   0.00556  -0.1207   0.4430   0.7492
   5.000   1.0931   0.01181   0.00573  -0.1206   0.4368   0.7514
   5.250   1.1192   0.01198   0.00590  -0.1204   0.4311   0.7539
   5.500   1.1458   0.01212   0.00608  -0.1204   0.4247   0.7566
   5.750   1.1719   0.01229   0.00625  -0.1202   0.4170   0.7591
   6.000   1.1972   0.01239   0.00641  -0.1199   0.4087   0.7610
   6.250   1.2211   0.01258   0.00660  -0.1193   0.4000   0.7631
   6.500   1.2461   0.01269   0.00678  -0.1189   0.3905   0.7654
   6.750   1.2705   0.01288   0.00701  -0.1184   0.3821   0.7678
   7.000   1.2940   0.01309   0.00721  -0.1178   0.3705   0.7703
   7.250   1.3178   0.01330   0.00743  -0.1173   0.3569   0.7729
   7.500   1.3413   0.01352   0.00767  -0.1167   0.3443   0.7751
   7.750   1.3629   0.01378   0.00795  -0.1157   0.3290   0.7771
   8.000   1.3834   0.01412   0.00827  -0.1146   0.3122   0.7793
   8.250   1.4037   0.01449   0.00862  -0.1135   0.2935   0.7818
   8.500   1.4213   0.01501   0.00905  -0.1119   0.2699   0.7845
   8.750   1.4363   0.01561   0.00954  -0.1100   0.2429   0.7869
   9.000   1.4482   0.01634   0.01015  -0.1075   0.2140   0.7892
   9.250   1.4571   0.01722   0.01089  -0.1046   0.1815   0.7915
   9.500   1.4615   0.01836   0.01183  -0.1011   0.1455   0.7941
   9.750   1.4640   0.01962   0.01292  -0.0975   0.1153   0.7968
  10.000   1.4659   0.02092   0.01408  -0.0939   0.0889   0.7995
  10.250   1.4688   0.02221   0.01527  -0.0907   0.0685   0.8021
  10.500   1.4717   0.02352   0.01653  -0.0877   0.0546   0.8045
  10.750   1.4744   0.02486   0.01786  -0.0849   0.0432   0.8072
  11.000   1.4777   0.02626   0.01928  -0.0823   0.0349   0.8101
  11.250   1.4811   0.02775   0.02080  -0.0800   0.0287   0.8131
  11.500   1.4830   0.02948   0.02257  -0.0779   0.0230   0.8160
  11.750   1.4816   0.03156   0.02469  -0.0758   0.0171   0.8187
  12.000   1.4774   0.03400   0.02719  -0.0738   0.0122   0.8215
  12.250   1.4732   0.03667   0.02993  -0.0722   0.0095   0.8246
  12.500   1.4731   0.03916   0.03252  -0.0712   0.0082   0.8281
  12.750   1.4708   0.04205   0.03550  -0.0705   0.0074   0.8315
  13.000   1.4685   0.04506   0.03864  -0.0699   0.0068   0.8347
  13.250   1.4676   0.04805   0.04176  -0.0697   0.0065   0.8381
  13.500   1.4661   0.05128   0.04512  -0.0697   0.0061   0.8417
  13.750   1.4636   0.05478   0.04875  -0.0700   0.0059   0.8454
  14.000   1.4600   0.05851   0.05260  -0.0704   0.0057   0.8491
  14.250   1.4553   0.06249   0.05672  -0.0710   0.0055   0.8532
  14.500   1.4495   0.06679   0.06116  -0.0718   0.0054   0.8579
  14.750   1.4423   0.07142   0.06592  -0.0729   0.0052   0.8628
  15.000   1.4340   0.07634   0.07101  -0.0742   0.0051   0.8685
  15.250   1.4244   0.08161   0.07642  -0.0757   0.0050   0.8749
  15.500   1.4143   0.08698   0.08196  -0.0773   0.0049   0.8836
  15.750   1.4046   0.09175   0.08690  -0.0782   0.0049   0.9034
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