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FX 61-168 AIRFOIL (fx61168-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: FX 61-168 AIRFOIL (fx61168-il)
Reynolds number: 500,000
Max Cl/Cd: 104.48 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx61168-il-500000.txt
Download as CSV file: xf-fx61168-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 61-168 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
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.3622   0.11434   0.11212  -0.0454   1.0000   0.0178
 -11.750  -0.3703   0.10710   0.10492  -0.0487   1.0000   0.0190
  -9.250  -0.4812   0.03413   0.03008  -0.0975   0.9140   0.0145
  -9.000  -0.4349   0.02554   0.02057  -0.1068   0.8933   0.0127
  -8.750  -0.3779   0.02229   0.01677  -0.1141   0.8581   0.0128
  -8.500  -0.3473   0.02134   0.01551  -0.1155   0.8182   0.0134
  -8.250  -0.3259   0.02050   0.01439  -0.1147   0.7898   0.0139
  -8.000  -0.3059   0.01996   0.01360  -0.1137   0.7684   0.0147
  -7.750  -0.2855   0.01939   0.01280  -0.1126   0.7516   0.0151
  -7.500  -0.2651   0.01788   0.01119  -0.1111   0.7387   0.0156
  -7.250  -0.2471   0.01707   0.01034  -0.1098   0.7277   0.0164
  -7.000  -0.2281   0.01648   0.00965  -0.1087   0.7184   0.0168
  -6.750  -0.2084   0.01595   0.00906  -0.1078   0.7099   0.0178
  -6.500  -0.1881   0.01542   0.00844  -0.1070   0.7028   0.0186
  -6.250  -0.1654   0.01507   0.00801  -0.1065   0.6958   0.0198
  -5.750  -0.1242   0.01367   0.00651  -0.1056   0.6841   0.0233
  -5.500  -0.0993   0.01329   0.00604  -0.1055   0.6789   0.0254
  -5.250  -0.0742   0.01274   0.00542  -0.1057   0.6744   0.0298
  -5.000  -0.0480   0.01229   0.00498  -0.1059   0.6698   0.0383
  -4.750  -0.0220   0.01143   0.00439  -0.1067   0.6653   0.1018
  -4.500   0.0091   0.00930   0.00342  -0.1106   0.6610   0.3983
  -4.250   0.0417   0.00877   0.00327  -0.1124   0.6569   0.5195
  -4.000   0.0717   0.00873   0.00331  -0.1130   0.6527   0.5625
  -3.750   0.1011   0.00883   0.00340  -0.1132   0.6486   0.5874
  -3.500   0.1313   0.00904   0.00350  -0.1137   0.6449   0.6067
  -3.250   0.1602   0.00934   0.00378  -0.1136   0.6415   0.6229
  -3.000   0.1882   0.00961   0.00405  -0.1134   0.6379   0.6333
  -2.750   0.2169   0.00975   0.00414  -0.1135   0.6343   0.6395
  -2.500   0.2457   0.00986   0.00420  -0.1137   0.6311   0.6429
  -2.250   0.2755   0.00999   0.00423  -0.1141   0.6278   0.6469
  -2.000   0.3055   0.01001   0.00418  -0.1147   0.6242   0.6517
  -1.750   0.3333   0.01005   0.00422  -0.1147   0.6202   0.6542
  -1.500   0.3616   0.01013   0.00428  -0.1148   0.6167   0.6570
  -1.250   0.3912   0.01026   0.00433  -0.1152   0.6136   0.6602
  -1.000   0.4205   0.01032   0.00436  -0.1156   0.6104   0.6644
  -0.750   0.4496   0.01036   0.00437  -0.1159   0.6070   0.6680
  -0.500   0.4775   0.01043   0.00445  -0.1159   0.6038   0.6705
  -0.250   0.5060   0.01053   0.00453  -0.1161   0.6008   0.6734
   0.000   0.5356   0.01068   0.00461  -0.1166   0.5978   0.6768
   0.250   0.5647   0.01071   0.00464  -0.1170   0.5945   0.6805
   0.500   0.5934   0.01071   0.00464  -0.1173   0.5906   0.6831
   0.750   0.6212   0.01074   0.00468  -0.1173   0.5869   0.6852
   1.000   0.6497   0.01083   0.00474  -0.1175   0.5834   0.6873
   1.250   0.6780   0.01089   0.00481  -0.1177   0.5799   0.6897
   1.500   0.7063   0.01092   0.00486  -0.1180   0.5760   0.6926
   1.750   0.7354   0.01096   0.00488  -0.1184   0.5723   0.6955
   2.000   0.7648   0.01101   0.00490  -0.1189   0.5690   0.6978
   2.250   0.7930   0.01107   0.00498  -0.1191   0.5656   0.6996
   2.500   0.8201   0.01109   0.00506  -0.1190   0.5616   0.7016
   2.750   0.8476   0.01112   0.00511  -0.1191   0.5571   0.7038
   3.000   0.8759   0.01119   0.00516  -0.1193   0.5528   0.7062
   3.250   0.9037   0.01122   0.00524  -0.1195   0.5481   0.7086
   3.500   0.9320   0.01125   0.00529  -0.1197   0.5433   0.7110
   3.750   0.9600   0.01129   0.00531  -0.1200   0.5386   0.7131
   4.000   0.9866   0.01132   0.00540  -0.1198   0.5333   0.7150
   4.250   1.0131   0.01134   0.00548  -0.1197   0.5276   0.7169
   4.500   1.0402   0.01141   0.00555  -0.1197   0.5223   0.7188
   4.750   1.0666   0.01143   0.00564  -0.1195   0.5152   0.7210
   5.000   1.0931   0.01148   0.00569  -0.1194   0.5083   0.7235
   5.250   1.1201   0.01154   0.00581  -0.1195   0.5011   0.7258
   5.500   1.1464   0.01162   0.00587  -0.1194   0.4931   0.7277
   5.750   1.1719   0.01165   0.00598  -0.1191   0.4841   0.7295
   6.000   1.1967   0.01177   0.00611  -0.1186   0.4760   0.7314
   6.250   1.2221   0.01186   0.00628  -0.1184   0.4668   0.7334
   6.500   1.2469   0.01200   0.00644  -0.1180   0.4568   0.7355
   6.750   1.2709   0.01218   0.00662  -0.1175   0.4453   0.7378
   7.000   1.2945   0.01239   0.00682  -0.1169   0.4328   0.7401
   7.250   1.3177   0.01263   0.00705  -0.1163   0.4188   0.7421
   7.500   1.3385   0.01291   0.00731  -0.1153   0.4020   0.7438
   7.750   1.3585   0.01323   0.00762  -0.1141   0.3828   0.7458
   8.000   1.3765   0.01364   0.00798  -0.1125   0.3621   0.7478
   8.250   1.3928   0.01413   0.00841  -0.1108   0.3401   0.7498
   8.500   1.4069   0.01467   0.00886  -0.1086   0.3152   0.7519
   8.750   1.4176   0.01527   0.00936  -0.1059   0.2897   0.7542
   9.000   1.4271   0.01600   0.00998  -0.1031   0.2641   0.7565
   9.250   1.4343   0.01682   0.01069  -0.1000   0.2382   0.7585
   9.500   1.4403   0.01770   0.01148  -0.0969   0.2141   0.7604
   9.750   1.4446   0.01869   0.01239  -0.0936   0.1912   0.7624
  10.000   1.4475   0.01979   0.01343  -0.0903   0.1717   0.7646
  10.250   1.4501   0.02099   0.01456  -0.0873   0.1542   0.7671
  10.500   1.4524   0.02230   0.01583  -0.0845   0.1374   0.7696
  10.750   1.4529   0.02384   0.01731  -0.0818   0.1213   0.7719
  11.000   1.4528   0.02552   0.01896  -0.0794   0.1061   0.7740
  11.250   1.4525   0.02737   0.02080  -0.0773   0.0930   0.7762
  11.500   1.4520   0.02941   0.02283  -0.0755   0.0803   0.7784
  11.750   1.4504   0.03170   0.02509  -0.0740   0.0677   0.7808
  12.000   1.4487   0.03415   0.02752  -0.0727   0.0576   0.7833
  12.250   1.4486   0.03658   0.02997  -0.0717   0.0491   0.7859
  12.500   1.4464   0.03931   0.03270  -0.0709   0.0403   0.7884
  13.000   1.4434   0.04483   0.03828  -0.0696   0.0282   0.7932
  13.250   1.4430   0.04762   0.04112  -0.0692   0.0233   0.7958
  13.500   1.4405   0.05073   0.04426  -0.0689   0.0183   0.7984
  13.750   1.4382   0.05394   0.04750  -0.0687   0.0140   0.8011
  14.000   1.4346   0.05738   0.05099  -0.0687   0.0102   0.8036
  14.250   1.4321   0.06080   0.05447  -0.0688   0.0079   0.8062
  14.500   1.4322   0.06401   0.05779  -0.0691   0.0069   0.8092
  14.750   1.4315   0.06744   0.06130  -0.0695   0.0062   0.8124
  15.000   1.4304   0.07102   0.06497  -0.0701   0.0057   0.8159
  15.250   1.4305   0.07450   0.06858  -0.0707   0.0055   0.8194
  15.500   1.4302   0.07813   0.07234  -0.0715   0.0052   0.8232
  15.750   1.4295   0.08190   0.07625  -0.0724   0.0050   0.8275
  16.000   1.4284   0.08584   0.08031  -0.0734   0.0049   0.8319
  16.250   1.4260   0.09001   0.08460  -0.0746   0.0047   0.8363
  16.500   1.4231   0.09436   0.08908  -0.0760   0.0046   0.8416
  17.000   1.4144   0.10379   0.09879  -0.0793   0.0044   0.8540
  17.250   1.4086   0.10882   0.10397  -0.0812   0.0043   0.8619
  17.500   1.4003   0.11429   0.10959  -0.0833   0.0042   0.8715
  17.750   1.3926   0.11949   0.11496  -0.0853   0.0041   0.8873
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