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FX 66-182 AIRFOIL (fx66182-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: FX 66-182 AIRFOIL (fx66182-il)
Reynolds number: 100,000
Max Cl/Cd: 5.95 at α=9°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx66182-il-100000.txt
Download as CSV file: xf-fx66182-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 66-182 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.3048   0.13812   0.13372  -0.0530   1.0000   0.1039
 -12.750  -0.2701   0.13422   0.12983  -0.0497   1.0000   0.1081
 -12.500  -0.2650   0.13127   0.12698  -0.0505   1.0000   0.1125
 -12.250  -0.2918   0.12891   0.12480  -0.0554   1.0000   0.1173
 -12.000  -0.2932   0.12501   0.12109  -0.0563   1.0000   0.1189
 -11.750  -0.2395   0.11924   0.11522  -0.0602   0.9523   0.1250
 -11.250  -0.1906   0.10752   0.10326  -0.0763   0.9058   0.1395
 -11.000  -0.2082   0.10157   0.09727  -0.0874   0.8872   0.1486
 -10.750  -0.1584   0.09848   0.09389  -0.0871   0.8644   0.1588
 -10.500  -0.1596   0.09426   0.08960  -0.0906   0.8493   0.1661
 -10.250  -0.1440   0.09140   0.08660  -0.0915   0.8356   0.1732
 -10.000  -0.1516   0.08748   0.08270  -0.0940   0.8246   0.1814
  -9.750  -0.1387   0.08438   0.07951  -0.0946   0.8150   0.1857
  -9.500  -0.3756   0.05647   0.05074  -0.1138   0.8123   0.0752
  -9.250  -0.3613   0.05112   0.04537  -0.1143   0.8052   0.0715
  -9.000  -0.3680   0.04752   0.04143  -0.1128   0.7972   0.0681
  -8.750  -0.3827   0.04397   0.03695  -0.1096   0.7906   0.0640
  -8.500  -0.3700   0.04134   0.03415  -0.1088   0.7837   0.0652
  -8.250  -0.3539   0.03940   0.03208  -0.1081   0.7769   0.0674
  -8.000  -0.3393   0.03716   0.02943  -0.1068   0.7716   0.0680
  -7.750  -0.3232   0.03515   0.02711  -0.1056   0.7651   0.0688
  -7.500  -0.3036   0.03364   0.02527  -0.1046   0.7601   0.0717
  -7.250  -0.2822   0.03234   0.02356  -0.1037   0.7557   0.0744
  -7.000  -0.2598   0.03061   0.02172  -0.1031   0.7503   0.0773
  -6.750  -0.2356   0.02939   0.02051  -0.1027   0.7454   0.0817
  -6.500  -0.2088   0.02829   0.01927  -0.1021   0.7415   0.0853
  -6.250  -0.1864   0.02765   0.01851  -0.1012   0.7363   0.0893
  -6.000  -0.1653   0.02666   0.01773  -0.1003   0.7317   0.0960
  -5.750  -0.1434   0.02606   0.01708  -0.0991   0.7281   0.1034
  -5.500  -0.1257   0.02529   0.01642  -0.0975   0.7250   0.1153
  -5.250  -0.1160   0.02462   0.01601  -0.0954   0.7205   0.1389
  -5.000  -0.1219   0.02226   0.01512  -0.0921   0.7164   0.3393
  -4.750  -0.1058   0.02355   0.01703  -0.0881   0.7127   0.5474
  -4.500  -0.0803   0.02480   0.01808  -0.0860   0.7097   0.5819
  -4.250  -0.0619   0.02633   0.01964  -0.0831   0.7054   0.6044
  -4.000  -0.0439   0.02795   0.02126  -0.0795   0.7015   0.6312
  -3.750  -0.0237   0.02942   0.02272  -0.0755   0.6982   0.6566
  -3.500  -0.0010   0.03035   0.02356  -0.0721   0.6953   0.6773
  -3.250   0.0179   0.03101   0.02413  -0.0694   0.6922   0.6933
  -3.000   0.0264   0.03167   0.02479  -0.0667   0.6877   0.7070
  -2.750   0.0417   0.03219   0.02527  -0.0641   0.6842   0.7187
  -2.500   0.0617   0.03237   0.02535  -0.0624   0.6813   0.7291
  -2.250   0.0850   0.03226   0.02507  -0.0618   0.6788   0.7400
  -2.000   0.0920   0.03290   0.02571  -0.0594   0.6747   0.7482
  -1.750   0.0920   0.03370   0.02653  -0.0570   0.6702   0.7557
  -1.500   0.1052   0.03414   0.02690  -0.0555   0.6670   0.7624
  -1.250   0.1284   0.03414   0.02676  -0.0557   0.6644   0.7699
  -1.000   0.1583   0.03396   0.02646  -0.0557   0.6624   0.7752
  -0.750   0.1086   0.03717   0.02987  -0.0493   0.6551   0.7815
  -0.500   0.1026   0.03859   0.03128  -0.0469   0.6516   0.7866
  -0.250   0.1290   0.03873   0.03133  -0.0470   0.6490   0.7914
   0.000   0.1710   0.03835   0.03079  -0.0491   0.6472   0.7967
   0.250   0.1036   0.04263   0.03521  -0.0417   0.6431   0.8020
   0.500   0.0907   0.04469   0.03728  -0.0392   0.6410   0.8068
   0.750   0.0927   0.04628   0.03884  -0.0384   0.6400   0.8120
   1.000   0.0982   0.04788   0.04041  -0.0380   0.6409   0.8169
   1.250   0.1036   0.04934   0.04185  -0.0372   0.6415   0.8214
   1.500   0.1187   0.05079   0.04327  -0.0376   0.6437   0.8264
   1.750   0.1499   0.05208   0.04447  -0.0396   0.6466   0.8313
   2.000   0.0569   0.05734   0.05001  -0.0343   0.6977   0.8358
   2.250   0.0899   0.05876   0.05136  -0.0361   0.6949   0.8409
   2.500   0.0893   0.05937   0.05193  -0.0345   0.6871   0.8460
   2.750   0.1141   0.06033   0.05286  -0.0351   0.6815   0.8512
   3.000   0.1520   0.06205   0.05452  -0.0373   0.6786   0.8566
   3.250   0.1472   0.06245   0.05490  -0.0354   0.6688   0.8624
   3.500   0.1756   0.06370   0.05614  -0.0365   0.6648   0.8689
   3.750   0.2120   0.06563   0.05803  -0.0387   0.6626   0.8758
   4.000   0.2037   0.06591   0.05834  -0.0364   0.6523   0.8828
   4.250   0.2362   0.06738   0.05982  -0.0381   0.6484   0.8923
   4.500   0.2759   0.06962   0.06210  -0.0407   0.6465   0.9031
   4.750   0.2661   0.06982   0.06238  -0.0390   0.6355   0.9168
   5.000   0.3113   0.07191   0.06454  -0.0433   0.6320   0.9391
   5.250   0.3116   0.07302   0.06567  -0.0433   0.6236   1.0000
   5.500   0.3414   0.07465   0.06727  -0.0455   0.6182   1.0000
   5.750   0.3817   0.07701   0.06960  -0.0485   0.6157   1.0000
   6.000   0.3724   0.07797   0.07056  -0.0475   0.6059   1.0000
   6.250   0.4038   0.07986   0.07241  -0.0495   0.6018   1.0000
   6.500   0.4452   0.08253   0.07505  -0.0524   0.5996   1.0000
   6.750   0.4305   0.08323   0.07576  -0.0508   0.5885   1.0000
   7.000   0.4639   0.08538   0.07790  -0.0528   0.5853   1.0000
   7.250   0.4606   0.08706   0.07958  -0.0523   0.5774   1.0000
   7.500   0.4861   0.08877   0.08129  -0.0534   0.5712   1.0000
   7.750   0.5234   0.09131   0.08384  -0.0554   0.5687   1.0000
   8.000   0.5092   0.09256   0.08511  -0.0541   0.5582   1.0000
   8.250   0.5418   0.09465   0.08721  -0.0555   0.5541   1.0000
   8.500   0.5369   0.09669   0.08927  -0.0550   0.5466   1.0000
   8.750   0.5608   0.09842   0.09103  -0.0557   0.5399   1.0000
   9.000   0.6018   0.10117   0.09381  -0.0575   0.5372   1.0000
   9.250   0.5820   0.10248   0.09516  -0.0562   0.5261   1.0000
   9.500   0.6217   0.10483   0.09755  -0.0576   0.5222   1.0000
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