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FX 66-S-161 AIRFOIL (fx66s161-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: FX 66-S-161 AIRFOIL (fx66s161-il)
Reynolds number: 500,000
Max Cl/Cd: 116.01 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx66s161-il-500000.txt
Download as CSV file: xf-fx66s161-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 66-S-161 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.3764   0.06081   0.05841  -0.0908   0.9105   0.0157
 -11.000  -0.3965   0.04925   0.04620  -0.1068   0.8359   0.0155
 -10.750  -0.4353   0.04294   0.03945  -0.1093   0.7925   0.0147
 -10.500  -0.5235   0.03369   0.02928  -0.1067   0.7656   0.0134
 -10.250  -0.5258   0.03158   0.02686  -0.1048   0.7469   0.0134
 -10.000  -0.5210   0.02975   0.02478  -0.1033   0.7317   0.0136
  -9.750  -0.5126   0.02791   0.02269  -0.1020   0.7188   0.0138
  -9.500  -0.5005   0.02623   0.02077  -0.1009   0.7075   0.0139
  -9.250  -0.4855   0.02481   0.01913  -0.0999   0.6976   0.0142
  -9.000  -0.4674   0.02376   0.01792  -0.0991   0.6878   0.0145
  -8.750  -0.4471   0.02306   0.01709  -0.0985   0.6789   0.0153
  -8.500  -0.4276   0.02188   0.01570  -0.0977   0.6708   0.0157
  -8.250  -0.4070   0.02069   0.01431  -0.0970   0.6630   0.0161
  -8.000  -0.3857   0.01965   0.01308  -0.0963   0.6561   0.0165
  -7.750  -0.3627   0.01889   0.01217  -0.0957   0.6494   0.0169
  -7.500  -0.3438   0.01737   0.01051  -0.0947   0.6433   0.0177
  -7.250  -0.3220   0.01655   0.00962  -0.0941   0.6377   0.0185
  -7.000  -0.2982   0.01599   0.00902  -0.0937   0.6318   0.0196
  -6.750  -0.2743   0.01546   0.00838  -0.0933   0.6266   0.0208
  -6.500  -0.2491   0.01506   0.00788  -0.0930   0.6216   0.0220
  -6.250  -0.2267   0.01421   0.00701  -0.0925   0.6166   0.0247
  -6.000  -0.2010   0.01388   0.00661  -0.0923   0.6121   0.0273
  -5.750  -0.1764   0.01334   0.00596  -0.0920   0.6079   0.0304
  -5.500  -0.1504   0.01293   0.00553  -0.0919   0.6034   0.0342
  -5.250  -0.1241   0.01258   0.00510  -0.0917   0.5991   0.0386
  -5.000  -0.0978   0.01227   0.00473  -0.0916   0.5953   0.0459
  -4.750  -0.0714   0.01185   0.00434  -0.0916   0.5917   0.0599
  -4.500  -0.0457   0.01127   0.00394  -0.0916   0.5881   0.1032
  -4.250  -0.0214   0.01045   0.00352  -0.0916   0.5847   0.2067
  -4.000   0.0032   0.00976   0.00325  -0.0916   0.5813   0.3346
  -3.750   0.0302   0.00955   0.00318  -0.0917   0.5780   0.3921
  -3.500   0.0583   0.00949   0.00318  -0.0917   0.5745   0.4284
  -3.250   0.0867   0.00950   0.00316  -0.0918   0.5712   0.4489
  -3.000   0.1152   0.00956   0.00317  -0.0919   0.5683   0.4671
  -2.750   0.1437   0.00967   0.00319  -0.0920   0.5656   0.4820
  -2.500   0.1722   0.00973   0.00322  -0.0921   0.5630   0.4932
  -2.250   0.2006   0.00977   0.00325  -0.0922   0.5602   0.5056
  -2.000   0.2291   0.00983   0.00327  -0.0923   0.5574   0.5172
  -1.750   0.2575   0.00989   0.00330  -0.0924   0.5546   0.5274
  -1.500   0.2859   0.00992   0.00330  -0.0925   0.5522   0.5350
  -1.250   0.3146   0.01002   0.00333  -0.0927   0.5498   0.5411
  -1.000   0.3433   0.01005   0.00332  -0.0929   0.5477   0.5459
  -0.750   0.3717   0.01003   0.00332  -0.0931   0.5454   0.5501
  -0.500   0.4003   0.01005   0.00333  -0.0933   0.5430   0.5547
  -0.250   0.4289   0.01009   0.00332  -0.0935   0.5407   0.5593
   0.000   0.4573   0.01009   0.00331  -0.0937   0.5382   0.5635
   0.250   0.4858   0.01017   0.00334  -0.0939   0.5354   0.5682
   0.500   0.5141   0.01020   0.00338  -0.0940   0.5328   0.5732
   0.750   0.5424   0.01021   0.00340  -0.0942   0.5302   0.5777
   1.000   0.5706   0.01022   0.00345  -0.0943   0.5278   0.5823
   1.250   0.5991   0.01027   0.00348  -0.0945   0.5255   0.5873
   1.500   0.6275   0.01032   0.00353  -0.0948   0.5233   0.5922
   1.750   0.6559   0.01041   0.00361  -0.0950   0.5212   0.5972
   2.000   0.6843   0.01052   0.00372  -0.0952   0.5191   0.6031
   2.250   0.7121   0.01054   0.00381  -0.0953   0.5169   0.6089
   2.500   0.7400   0.01058   0.00390  -0.0954   0.5143   0.6155
   2.750   0.7681   0.01063   0.00398  -0.0956   0.5119   0.6232
   3.000   0.7961   0.01068   0.00408  -0.0957   0.5096   0.6314
   3.250   0.8242   0.01077   0.00418  -0.0959   0.5075   0.6398
   3.500   0.8527   0.01094   0.00436  -0.0962   0.5051   0.6490
   3.750   0.8797   0.01096   0.00450  -0.0962   0.5031   0.6597
   4.000   0.9070   0.01099   0.00464  -0.0962   0.5006   0.6727
   4.250   0.9342   0.01103   0.00477  -0.0962   0.4979   0.6876
   4.500   0.9615   0.01106   0.00489  -0.0963   0.4952   0.7052
   4.750   0.9887   0.01110   0.00501  -0.0963   0.4927   0.7283
   5.000   1.0156   0.01121   0.00523  -0.0962   0.4900   0.7613
   5.250   1.0392   0.01110   0.00539  -0.0954   0.4873   0.8142
   5.500   1.0705   0.01086   0.00552  -0.0961   0.4842   1.0000
   5.750   1.0979   0.01097   0.00564  -0.0962   0.4813   1.0000
   6.000   1.1255   0.01110   0.00577  -0.0963   0.4786   1.0000
   6.250   1.1534   0.01131   0.00597  -0.0966   0.4760   1.0000
   6.500   1.1796   0.01145   0.00619  -0.0965   0.4731   1.0000
   6.750   1.2057   0.01155   0.00637  -0.0964   0.4698   1.0000
   7.000   1.2323   0.01167   0.00653  -0.0963   0.4664   1.0000
   7.250   1.2590   0.01178   0.00666  -0.0963   0.4629   1.0000
   7.500   1.2840   0.01187   0.00682  -0.0959   0.4579   1.0000
   7.750   1.3076   0.01180   0.00680  -0.0952   0.4500   1.0000
   8.000   1.3295   0.01172   0.00677  -0.0942   0.4379   1.0000
   8.250   1.3513   0.01173   0.00680  -0.0932   0.4235   1.0000
   8.500   1.3735   0.01184   0.00694  -0.0924   0.4097   1.0000
   8.750   1.3953   0.01204   0.00716  -0.0915   0.3968   1.0000
   9.000   1.4145   0.01236   0.00744  -0.0903   0.3796   1.0000
   9.250   1.4301   0.01283   0.00785  -0.0884   0.3567   1.0000
   9.500   1.4396   0.01356   0.00845  -0.0857   0.3253   1.0000
   9.750   1.4406   0.01451   0.00923  -0.0815   0.2913   1.0000
  10.000   1.4279   0.01592   0.01039  -0.0754   0.2472   1.0000
  10.250   1.4108   0.01770   0.01195  -0.0694   0.2057   1.0000
  10.500   1.3905   0.02000   0.01406  -0.0641   0.1691   1.0000
  10.750   1.3713   0.02278   0.01670  -0.0602   0.1392   1.0000
  11.000   1.3510   0.02618   0.01997  -0.0573   0.1099   1.0000
  11.250   1.3331   0.02981   0.02349  -0.0552   0.0846   1.0000
  11.500   1.3152   0.03368   0.02726  -0.0535   0.0619   1.0000
  11.750   1.3004   0.03741   0.03092  -0.0522   0.0442   1.0000
  12.000   1.2883   0.04101   0.03448  -0.0511   0.0324   1.0000
  12.250   1.2809   0.04425   0.03773  -0.0503   0.0262   1.0000
  12.500   1.2776   0.04720   0.04073  -0.0498   0.0225   1.0000
  12.750   1.2724   0.05044   0.04400  -0.0493   0.0200   1.0000
  13.000   1.2707   0.05344   0.04708  -0.0490   0.0181   1.0000
  13.250   1.2709   0.05629   0.04999  -0.0489   0.0167   1.0000
  13.500   1.2682   0.05953   0.05328  -0.0488   0.0154   1.0000
  13.750   1.2618   0.06332   0.05716  -0.0489   0.0142   1.0000
  14.000   1.2640   0.06614   0.06007  -0.0490   0.0131   1.0000
  14.250   1.2641   0.06926   0.06327  -0.0492   0.0128   1.0000
  14.500   1.2638   0.07251   0.06657  -0.0495   0.0120   1.0000
  14.750   1.2616   0.07604   0.07017  -0.0498   0.0114   1.0000
  15.000   1.2548   0.08026   0.07446  -0.0504   0.0109   1.0000
  15.250   1.2495   0.08430   0.07858  -0.0509   0.0105   1.0000
  15.500   1.2528   0.08728   0.08164  -0.0514   0.0102   1.0000
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