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FX 66-182 AIRFOIL (fx66182-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: FX 66-182 AIRFOIL (fx66182-il)
Reynolds number: 50,000
Max Cl/Cd: 8.19 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx66182-il-50000-n5.txt
Download as CSV file: xf-fx66182-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.3118   0.11475   0.10846  -0.0617   1.0000   0.0514
 -12.000  -0.3124   0.11070   0.10452  -0.0629   1.0000   0.0511
 -11.750  -0.3177   0.10598   0.09994  -0.0646   1.0000   0.0509
 -11.500  -0.3241   0.10040   0.09450  -0.0674   0.9957   0.0507
 -11.250  -0.3263   0.09159   0.08568  -0.0754   0.9483   0.0504
 -11.000  -0.3343   0.08281   0.07678  -0.0843   0.9216   0.0500
 -10.750  -0.3465   0.07451   0.06826  -0.0933   0.9003   0.0496
 -10.500  -0.3589   0.06776   0.06124  -0.1006   0.8794   0.0494
 -10.250  -0.3713   0.06264   0.05577  -0.1051   0.8589   0.0494
 -10.000  -0.3849   0.05883   0.05160  -0.1068   0.8409   0.0497
  -9.750  -0.3974   0.05594   0.04833  -0.1063   0.8261   0.0502
  -9.500  -0.4038   0.05317   0.04513  -0.1055   0.8137   0.0508
  -9.250  -0.4060   0.05047   0.04187  -0.1044   0.8034   0.0516
  -9.000  -0.3969   0.04800   0.03918  -0.1036   0.7931   0.0525
  -8.750  -0.3830   0.04589   0.03686  -0.1031   0.7846   0.0541
  -8.500  -0.3684   0.04416   0.03491  -0.1024   0.7762   0.0565
  -8.250  -0.3526   0.04233   0.03274  -0.1016   0.7689   0.0593
  -8.000  -0.3328   0.04049   0.03050  -0.1008   0.7616   0.0614
  -7.750  -0.3058   0.03873   0.02845  -0.1005   0.7558   0.0639
  -7.500  -0.2826   0.03759   0.02729  -0.1000   0.7487   0.0680
  -7.250  -0.2538   0.03651   0.02596  -0.0995   0.7431   0.0728
  -7.000  -0.2255   0.03556   0.02486  -0.0987   0.7376   0.0768
  -6.750  -0.2064   0.03477   0.02408  -0.0974   0.7317   0.0814
  -6.500  -0.1876   0.03405   0.02314  -0.0961   0.7270   0.0891
  -6.250  -0.1762   0.03325   0.02244  -0.0944   0.7218   0.0973
  -6.000  -0.1658   0.03244   0.02168  -0.0926   0.7163   0.1085
  -5.750  -0.1558   0.03140   0.02073  -0.0909   0.7118   0.1272
  -5.500  -0.1495   0.03018   0.01979  -0.0892   0.7075   0.1666
  -5.250  -0.1491   0.02882   0.01914  -0.0869   0.7023   0.2568
  -5.000  -0.1392   0.02939   0.02103  -0.0817   0.6982   0.4523
  -4.750  -0.1210   0.03049   0.02190  -0.0792   0.6946   0.5373
  -4.500  -0.1063   0.03181   0.02305  -0.0759   0.6900   0.5809
  -4.250  -0.0882   0.03308   0.02418  -0.0724   0.6853   0.6096
  -4.000  -0.0668   0.03386   0.02476  -0.0697   0.6815   0.6317
  -3.750  -0.0430   0.03430   0.02496  -0.0677   0.6785   0.6497
  -3.500  -0.0285   0.03469   0.02523  -0.0655   0.6742   0.6641
  -3.250  -0.0144   0.03493   0.02530  -0.0636   0.6698   0.6772
  -3.000   0.0052   0.03501   0.02520  -0.0623   0.6662   0.6879
  -2.750   0.0287   0.03496   0.02495  -0.0615   0.6633   0.6966
  -2.500   0.0417   0.03506   0.02489  -0.0603   0.6592   0.7064
  -2.250   0.0549   0.03540   0.02516  -0.0584   0.6546   0.7127
  -2.000   0.0723   0.03545   0.02503  -0.0577   0.6511   0.7209
  -1.750   0.0957   0.03544   0.02487  -0.0573   0.6483   0.7264
  -1.500   0.1175   0.03548   0.02473  -0.0569   0.6454   0.7328
  -1.250   0.1191   0.03621   0.02545  -0.0546   0.6395   0.7391
  -1.000   0.1363   0.03649   0.02564  -0.0536   0.6358   0.7445
  -0.750   0.1599   0.03659   0.02558  -0.0537   0.6330   0.7507
  -0.500   0.1868   0.03660   0.02543  -0.0540   0.6309   0.7559
  -0.250   0.1794   0.03790   0.02679  -0.0507   0.6242   0.7614
   0.000   0.1946   0.03842   0.02721  -0.0501   0.6201   0.7674
   0.250   0.2176   0.03868   0.02737  -0.0500   0.6174   0.7719
   0.500   0.2449   0.03881   0.02738  -0.0503   0.6154   0.7769
   0.750   0.2302   0.04073   0.02934  -0.0472   0.6079   0.7830
   1.000   0.2457   0.04139   0.02996  -0.0464   0.6040   0.7877
   1.250   0.2696   0.04175   0.03024  -0.0465   0.6014   0.7928
   1.500   0.2985   0.04200   0.03038  -0.0473   0.5995   0.7983
   1.750   0.2677   0.04481   0.03330  -0.0429   0.5906   0.8041
   2.000   0.2882   0.04545   0.03389  -0.0428   0.5872   0.8097
   2.250   0.3158   0.04584   0.03420  -0.0435   0.5850   0.8156
   2.750   0.3182   0.04938   0.03778  -0.0412   0.5742   0.8283
   3.000   0.3403   0.05005   0.03844  -0.0413   0.5711   0.8347
   3.250   0.3673   0.05050   0.03887  -0.0418   0.5689   0.8418
   3.500   0.3610   0.05279   0.04122  -0.0405   0.5626   0.8503
   3.750   0.3734   0.05405   0.04252  -0.0402   0.5581   0.8592
   4.000   0.3968   0.05477   0.04328  -0.0405   0.5551   0.8689
   4.250   0.4243   0.05539   0.04393  -0.0412   0.5530   0.8807
   4.500   0.4213   0.05786   0.04652  -0.0410   0.5467   0.8979
   4.750   0.4431   0.05926   0.04803  -0.0426   0.5422   0.9242
   5.000   0.4701   0.06013   0.04891  -0.0442   0.5391   1.0000
   5.250   0.4999   0.06101   0.04975  -0.0457   0.5371   1.0000
   5.500   0.4901   0.06404   0.05278  -0.0454   0.5303   1.0000
   5.750   0.5080   0.06550   0.05424  -0.0462   0.5262   1.0000
   6.000   0.5341   0.06655   0.05527  -0.0472   0.5233   1.0000
   6.250   0.5539   0.06801   0.05671  -0.0479   0.5203   1.0000
   6.500   0.5489   0.07074   0.05947  -0.0476   0.5136   1.0000
   6.750   0.5690   0.07209   0.06083  -0.0482   0.5099   1.0000
   7.000   0.5955   0.07311   0.06186  -0.0489   0.5072   1.0000
   7.500   0.6071   0.07737   0.06617  -0.0488   0.4959   1.0000
   7.750   0.6315   0.07849   0.06733  -0.0493   0.4928   1.0000
   8.000   0.6346   0.08080   0.06969  -0.0492   0.4868   1.0000
   8.250   0.6455   0.08265   0.07159  -0.0493   0.4814   1.0000
   8.500   0.6688   0.08383   0.07281  -0.0496   0.4780   1.0000
   8.750   0.6722   0.08616   0.07522  -0.0495   0.4718   1.0000
   9.000   0.6839   0.08796   0.07709  -0.0496   0.4662   1.0000
   9.250   0.7086   0.08902   0.07822  -0.0499   0.4628   1.0000
   9.500   0.7065   0.09169   0.08097  -0.0498   0.4550   1.0000
   9.750   0.7246   0.09309   0.08245  -0.0499   0.4500   1.0000
  10.000   0.7525   0.09387   0.08335  -0.0502   0.4470   1.0000
  10.250   0.7442   0.09698   0.08654  -0.0500   0.4374   1.0000
  10.500   0.7690   0.09789   0.08756  -0.0501   0.4335   1.0000
  10.750   0.7665   0.10072   0.09048  -0.0502   0.4248   1.0000
  11.000   0.7881   0.10177   0.09168  -0.0502   0.4198   1.0000
  11.250   0.7904   0.10428   0.09429  -0.0503   0.4117   1.0000
  11.500   0.8094   0.10542   0.09557  -0.0503   0.4058   1.0000
  12.000   0.8321   0.10891   0.09931  -0.0504   0.3914   1.0000
  12.250   0.8361   0.11127   0.10182  -0.0506   0.3827   1.0000
  12.500   0.8563   0.11212   0.10283  -0.0505   0.3765   1.0000
  12.750   0.8579   0.11472   0.10556  -0.0507   0.3667   1.0000
  13.000   0.8826   0.11493   0.10594  -0.0504   0.3610   1.0000
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