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FX 66-S-171 AIRFOIL (fx66s171-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: FX 66-S-171 AIRFOIL (fx66s171-il)
Reynolds number: 200,000
Max Cl/Cd: 72.42 at α=9.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx66s171-il-200000-n5.txt
Download as CSV file: xf-fx66s171-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 66-S-171 AIRFOIL                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.4437   0.08604   0.08258  -0.0595   1.0000   0.0143
 -12.500  -0.4916   0.07240   0.06876  -0.0684   1.0000   0.0140
 -12.250  -0.5186   0.06207   0.05818  -0.0778   0.9425   0.0138
 -12.000  -0.5176   0.05165   0.04718  -0.0942   0.8842   0.0139
 -11.750  -0.5169   0.04563   0.04062  -0.1023   0.8334   0.0140
 -11.500  -0.5209   0.04174   0.03629  -0.1052   0.7999   0.0141
 -11.250  -0.5255   0.03869   0.03289  -0.1062   0.7752   0.0143
 -11.000  -0.5288   0.03620   0.03006  -0.1061   0.7561   0.0145
 -10.750  -0.5290   0.03414   0.02771  -0.1053   0.7404   0.0147
 -10.500  -0.5288   0.03230   0.02556  -0.1039   0.7270   0.0150
 -10.250  -0.5247   0.03088   0.02388  -0.1020   0.7155   0.0152
 -10.000  -0.5154   0.02949   0.02237  -0.1008   0.7055   0.0156
  -9.750  -0.5033   0.02848   0.02123  -0.0998   0.6962   0.0161
  -9.500  -0.4889   0.02754   0.02017  -0.0988   0.6875   0.0167
  -9.250  -0.4732   0.02663   0.01909  -0.0979   0.6798   0.0175
  -9.000  -0.4562   0.02564   0.01791  -0.0970   0.6722   0.0184
  -8.750  -0.4384   0.02465   0.01671  -0.0961   0.6653   0.0193
  -8.500  -0.4215   0.02356   0.01553  -0.0951   0.6587   0.0200
  -8.250  -0.4033   0.02271   0.01460  -0.0943   0.6522   0.0208
  -8.000  -0.3840   0.02196   0.01375  -0.0935   0.6464   0.0219
  -7.750  -0.3639   0.02120   0.01290  -0.0928   0.6404   0.0232
  -7.500  -0.3431   0.02054   0.01207  -0.0921   0.6352   0.0248
  -7.250  -0.3225   0.01985   0.01134  -0.0916   0.6304   0.0271
  -7.000  -0.3000   0.01930   0.01071  -0.0912   0.6253   0.0296
  -6.750  -0.2781   0.01867   0.00997  -0.0906   0.6208   0.0324
  -6.500  -0.2550   0.01817   0.00940  -0.0903   0.6169   0.0361
  -6.250  -0.2313   0.01765   0.00879  -0.0900   0.6124   0.0403
  -6.000  -0.2075   0.01713   0.00823  -0.0897   0.6082   0.0462
  -5.750  -0.1834   0.01665   0.00769  -0.0894   0.6044   0.0541
  -5.500  -0.1587   0.01620   0.00720  -0.0892   0.6009   0.0663
  -5.250  -0.1340   0.01571   0.00675  -0.0891   0.5967   0.0868
  -5.000  -0.1096   0.01516   0.00631  -0.0890   0.5928   0.1232
  -4.750  -0.0860   0.01447   0.00585  -0.0889   0.5895   0.1903
  -4.500  -0.0632   0.01371   0.00550  -0.0888   0.5868   0.3011
  -4.250  -0.0375   0.01343   0.00543  -0.0887   0.5834   0.3683
  -4.000  -0.0107   0.01339   0.00547  -0.0885   0.5801   0.4087
  -3.750   0.0170   0.01344   0.00545  -0.0885   0.5770   0.4340
  -3.500   0.0448   0.01351   0.00543  -0.0884   0.5741   0.4537
  -3.250   0.0727   0.01363   0.00542  -0.0884   0.5715   0.4713
  -3.000   0.1004   0.01371   0.00547  -0.0884   0.5682   0.4870
  -2.750   0.1282   0.01379   0.00550  -0.0883   0.5650   0.4996
  -2.500   0.1560   0.01384   0.00547  -0.0883   0.5620   0.5094
  -2.250   0.1840   0.01386   0.00542  -0.0884   0.5593   0.5161
  -2.000   0.2125   0.01390   0.00530  -0.0885   0.5570   0.5218
  -1.750   0.2405   0.01390   0.00528  -0.0886   0.5546   0.5256
  -1.500   0.2685   0.01391   0.00527  -0.0887   0.5518   0.5300
  -1.250   0.2966   0.01394   0.00523  -0.0889   0.5490   0.5348
  -1.000   0.3247   0.01396   0.00519  -0.0890   0.5463   0.5391
  -0.750   0.3527   0.01399   0.00518  -0.0891   0.5440   0.5433
  -0.500   0.3810   0.01404   0.00516  -0.0892   0.5420   0.5483
  -0.250   0.4092   0.01411   0.00518  -0.0894   0.5399   0.5533
   0.000   0.4368   0.01415   0.00525  -0.0895   0.5375   0.5571
   0.250   0.4646   0.01421   0.00531  -0.0896   0.5350   0.5615
   0.500   0.4925   0.01427   0.00535  -0.0898   0.5326   0.5663
   0.750   0.5204   0.01432   0.00538  -0.0899   0.5302   0.5704
   1.000   0.5483   0.01438   0.00543  -0.0900   0.5281   0.5751
   1.250   0.5766   0.01448   0.00548  -0.0902   0.5263   0.5812
   1.500   0.6035   0.01456   0.00564  -0.0902   0.5236   0.5868
   1.750   0.6305   0.01463   0.00576  -0.0901   0.5204   0.5925
   2.000   0.6579   0.01470   0.00583  -0.0902   0.5173   0.5985
   2.250   0.6852   0.01476   0.00592  -0.0902   0.5146   0.6036
   2.500   0.7130   0.01485   0.00601  -0.0903   0.5125   0.6095
   2.750   0.7409   0.01498   0.00613  -0.0905   0.5107   0.6156
   3.000   0.7671   0.01509   0.00637  -0.0904   0.5081   0.6220
   3.500   0.8203   0.01532   0.00675  -0.0903   0.5028   0.6375
   3.750   0.8473   0.01542   0.00691  -0.0903   0.5003   0.6460
   4.000   0.8743   0.01552   0.00706  -0.0903   0.4981   0.6545
   4.250   0.9019   0.01564   0.00721  -0.0904   0.4962   0.6637
   4.500   0.9273   0.01580   0.00751  -0.0902   0.4936   0.6742
   4.750   0.9526   0.01595   0.00780  -0.0899   0.4908   0.6860
   5.000   0.9780   0.01609   0.00807  -0.0897   0.4881   0.7001
   5.250   1.0034   0.01619   0.00829  -0.0894   0.4855   0.7175
   5.750   1.0554   0.01636   0.00867  -0.0889   0.4809   0.7667
   6.000   1.0772   0.01648   0.00905  -0.0879   0.4777   0.8057
   6.250   1.1006   0.01649   0.00936  -0.0871   0.4744   0.8847
   6.500   1.1335   0.01663   0.00961  -0.0885   0.4712   1.0000
   6.750   1.1598   0.01681   0.00982  -0.0885   0.4684   1.0000
   7.000   1.1872   0.01700   0.01001  -0.0886   0.4660   1.0000
   7.250   1.2089   0.01733   0.01050  -0.0879   0.4621   1.0000
   7.500   1.2324   0.01762   0.01089  -0.0875   0.4587   1.0000
   7.750   1.2568   0.01786   0.01121  -0.0872   0.4557   1.0000
   8.000   1.2824   0.01806   0.01147  -0.0870   0.4528   1.0000
   8.250   1.3061   0.01834   0.01184  -0.0866   0.4496   1.0000
   8.500   1.3264   0.01872   0.01238  -0.0857   0.4457   1.0000
   8.750   1.3486   0.01902   0.01279  -0.0851   0.4419   1.0000
   9.000   1.3726   0.01916   0.01299  -0.0846   0.4379   1.0000
   9.250   1.3878   0.01938   0.01336  -0.0827   0.4293   1.0000
   9.500   1.4003   0.01936   0.01340  -0.0802   0.4150   1.0000
   9.750   1.4071   0.01943   0.01343  -0.0768   0.3956   1.0000
  10.000   1.4077   0.01984   0.01379  -0.0726   0.3753   1.0000
  10.250   1.4081   0.02056   0.01447  -0.0688   0.3553   1.0000
  10.500   1.4062   0.02157   0.01542  -0.0652   0.3363   1.0000
  10.750   1.4025   0.02290   0.01673  -0.0619   0.3185   1.0000
  11.000   1.3964   0.02463   0.01842  -0.0590   0.2995   1.0000
  11.250   1.3852   0.02697   0.02070  -0.0562   0.2759   1.0000
  11.500   1.3694   0.02998   0.02362  -0.0538   0.2516   1.0000
  11.750   1.3513   0.03351   0.02706  -0.0519   0.2258   1.0000
  12.000   1.3311   0.03747   0.03092  -0.0503   0.2025   1.0000
  12.250   1.3116   0.04158   0.03494  -0.0490   0.1805   1.0000
  12.500   1.2918   0.04590   0.03916  -0.0480   0.1576   1.0000
  12.750   1.2735   0.05028   0.04344  -0.0473   0.1360   1.0000
  13.000   1.2586   0.05452   0.04761  -0.0469   0.1156   1.0000
  13.250   1.2440   0.05891   0.05189  -0.0468   0.0949   1.0000
  13.500   1.2310   0.06327   0.05615  -0.0468   0.0757   1.0000
  13.750   1.2221   0.06729   0.06011  -0.0469   0.0600   1.0000
  14.000   1.2145   0.07127   0.06403  -0.0471   0.0471   1.0000
  14.250   1.2100   0.07497   0.06773  -0.0475   0.0389   1.0000
  14.500   1.2066   0.07861   0.07137  -0.0478   0.0326   1.0000
  14.750   1.2034   0.08229   0.07506  -0.0483   0.0278   1.0000
  15.000   1.2031   0.08568   0.07853  -0.0488   0.0249   1.0000
  15.250   1.2016   0.08926   0.08216  -0.0494   0.0224   1.0000
  15.500   1.2004   0.09287   0.08584  -0.0501   0.0206   1.0000
  15.750   1.2011   0.09625   0.08932  -0.0508   0.0192   1.0000
  16.000   1.2002   0.09991   0.09305  -0.0517   0.0178   1.0000
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