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FX 66-S-161 AIRFOIL (fx66s161-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: FX 66-S-161 AIRFOIL (fx66s161-il)
Reynolds number: 200,000
Max Cl/Cd: 75.66 at α=9.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx66s161-il-200000-n5.txt
Download as CSV file: xf-fx66s161-il-200000-n5.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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.4528   0.05344   0.04935  -0.0929   0.8731   0.0137
 -11.000  -0.4647   0.04655   0.04194  -0.1010   0.8270   0.0136
 -10.750  -0.4746   0.04238   0.03740  -0.1041   0.7959   0.0137
 -10.500  -0.4833   0.03951   0.03422  -0.1047   0.7725   0.0138
 -10.250  -0.4926   0.03722   0.03164  -0.1034   0.7541   0.0138
 -10.000  -0.4940   0.03523   0.02936  -0.1021   0.7393   0.0140
  -9.750  -0.4893   0.03337   0.02721  -0.1010   0.7266   0.0143
  -9.250  -0.4692   0.02984   0.02309  -0.0989   0.7049   0.0149
  -9.000  -0.4550   0.02821   0.02117  -0.0980   0.6959   0.0154
  -8.750  -0.4385   0.02671   0.01938  -0.0971   0.6874   0.0160
  -8.500  -0.4202   0.02537   0.01778  -0.0962   0.6797   0.0165
  -8.250  -0.4007   0.02424   0.01641  -0.0955   0.6723   0.0172
  -8.000  -0.3810   0.02327   0.01538  -0.0949   0.6655   0.0181
  -7.750  -0.3596   0.02258   0.01459  -0.0945   0.6588   0.0193
  -7.500  -0.3380   0.02177   0.01362  -0.0939   0.6530   0.0205
  -7.250  -0.3162   0.02089   0.01260  -0.0932   0.6469   0.0216
  -7.000  -0.2952   0.02000   0.01158  -0.0925   0.6414   0.0228
  -6.750  -0.2731   0.01928   0.01079  -0.0921   0.6360   0.0243
  -6.500  -0.2497   0.01871   0.01014  -0.0917   0.6303   0.0265
  -6.250  -0.2261   0.01817   0.00946  -0.0913   0.6257   0.0293
  -6.000  -0.2025   0.01757   0.00882  -0.0911   0.6210   0.0323
  -5.750  -0.1775   0.01715   0.00829  -0.0908   0.6163   0.0363
  -5.500  -0.1533   0.01658   0.00765  -0.0906   0.6122   0.0413
  -5.250  -0.1279   0.01618   0.00714  -0.0904   0.6086   0.0476
  -5.000  -0.1024   0.01572   0.00666  -0.0903   0.6043   0.0582
  -4.750  -0.0770   0.01524   0.00621  -0.0902   0.6004   0.0760
  -4.250  -0.0274   0.01405   0.00535  -0.0902   0.5935   0.1864
  -4.000  -0.0037   0.01327   0.00507  -0.0902   0.5895   0.3105
  -3.750   0.0221   0.01301   0.00504  -0.0901   0.5859   0.3856
  -3.500   0.0493   0.01302   0.00505  -0.0900   0.5828   0.4281
  -3.250   0.0772   0.01308   0.00501  -0.0899   0.5801   0.4532
  -3.000   0.1049   0.01316   0.00505  -0.0899   0.5768   0.4746
  -2.750   0.1326   0.01324   0.00508  -0.0898   0.5733   0.4938
  -2.500   0.1602   0.01332   0.00510  -0.0897   0.5700   0.5103
  -2.250   0.1880   0.01337   0.00508  -0.0897   0.5671   0.5212
  -2.000   0.2162   0.01343   0.00498  -0.0898   0.5646   0.5292
  -1.750   0.2442   0.01341   0.00495  -0.0898   0.5614   0.5339
  -1.500   0.2722   0.01342   0.00492  -0.0899   0.5583   0.5388
  -1.250   0.3005   0.01346   0.00486  -0.0901   0.5557   0.5443
  -1.000   0.3285   0.01347   0.00484  -0.0902   0.5531   0.5490
  -0.750   0.3567   0.01351   0.00481  -0.0903   0.5508   0.5543
  -0.500   0.3849   0.01357   0.00479  -0.0905   0.5483   0.5600
  -0.250   0.4126   0.01359   0.00483  -0.0905   0.5453   0.5642
   0.000   0.4405   0.01364   0.00487  -0.0906   0.5427   0.5691
   0.250   0.4686   0.01370   0.00489  -0.0908   0.5403   0.5745
   0.500   0.4964   0.01374   0.00493  -0.0909   0.5381   0.5791
   0.750   0.5244   0.01381   0.00498  -0.0910   0.5361   0.5846
   1.000   0.5524   0.01390   0.00504  -0.0911   0.5338   0.5912
   1.250   0.5796   0.01396   0.00517  -0.0911   0.5309   0.5974
   1.500   0.6071   0.01404   0.00527  -0.0912   0.5280   0.6047
   1.750   0.6345   0.01410   0.00536  -0.0912   0.5251   0.6111
   2.000   0.6621   0.01416   0.00541  -0.0912   0.5223   0.6181
   2.250   0.6899   0.01424   0.00548  -0.0913   0.5199   0.6246
   2.500   0.7166   0.01433   0.00566  -0.0913   0.5168   0.6321
   2.750   0.7435   0.01442   0.00583  -0.0913   0.5140   0.6404
   3.000   0.7705   0.01452   0.00599  -0.0913   0.5115   0.6503
   3.250   0.7975   0.01461   0.00615  -0.0912   0.5092   0.6601
   3.500   0.8248   0.01471   0.00629  -0.0913   0.5071   0.6705
   4.000   0.8778   0.01494   0.00671  -0.0911   0.5018   0.6959
   4.250   0.9034   0.01504   0.00695  -0.0908   0.4988   0.7122
   4.500   0.9290   0.01513   0.00717  -0.0905   0.4961   0.7314
   4.750   0.9546   0.01521   0.00738  -0.0902   0.4937   0.7557
   5.000   0.9804   0.01528   0.00756  -0.0898   0.4915   0.7883
   5.250   1.0044   0.01532   0.00779  -0.0891   0.4890   0.8386
   5.500   1.0373   0.01533   0.00809  -0.0903   0.4854   1.0000
   5.750   1.0632   0.01554   0.00836  -0.0902   0.4820   1.0000
   6.000   1.0897   0.01574   0.00859  -0.0902   0.4791   1.0000
   6.250   1.1168   0.01592   0.00878  -0.0903   0.4765   1.0000
   6.500   1.1418   0.01618   0.00913  -0.0900   0.4732   1.0000
   6.750   1.1660   0.01644   0.00951  -0.0897   0.4694   1.0000
   7.000   1.1911   0.01666   0.00981  -0.0895   0.4659   1.0000
   7.250   1.2171   0.01687   0.01008  -0.0894   0.4631   1.0000
   7.500   1.2433   0.01710   0.01037  -0.0893   0.4604   1.0000
   7.750   1.2652   0.01743   0.01088  -0.0886   0.4561   1.0000
   8.000   1.2888   0.01770   0.01126  -0.0881   0.4522   1.0000
   8.250   1.3136   0.01791   0.01156  -0.0878   0.4488   1.0000
   8.500   1.3359   0.01812   0.01190  -0.0871   0.4433   1.0000
   8.750   1.3558   0.01812   0.01196  -0.0858   0.4332   1.0000
   9.000   1.3694   0.01810   0.01201  -0.0835   0.4143   1.0000
   9.250   1.3793   0.01823   0.01207  -0.0805   0.3886   1.0000
   9.500   1.3855   0.01870   0.01246  -0.0773   0.3619   1.0000
   9.750   1.3881   0.01936   0.01306  -0.0735   0.3383   1.0000
  10.000   1.3855   0.02033   0.01395  -0.0693   0.3156   1.0000
  10.250   1.3799   0.02165   0.01518  -0.0653   0.2902   1.0000
  10.500   1.3679   0.02355   0.01697  -0.0613   0.2609   1.0000
  10.750   1.3519   0.02612   0.01941  -0.0580   0.2310   1.0000
  11.000   1.3323   0.02943   0.02259  -0.0553   0.2019   1.0000
  11.250   1.3134   0.03311   0.02615  -0.0533   0.1753   1.0000
  11.500   1.2940   0.03711   0.03004  -0.0518   0.1500   1.0000
  11.750   1.2775   0.04103   0.03387  -0.0507   0.1263   1.0000
  12.000   1.2605   0.04515   0.03788  -0.0498   0.1033   1.0000
  12.250   1.2463   0.04911   0.04176  -0.0491   0.0831   1.0000
  12.500   1.2341   0.05306   0.04562  -0.0487   0.0650   1.0000
  12.750   1.2241   0.05693   0.04943  -0.0484   0.0501   1.0000
  13.000   1.2176   0.06057   0.05304  -0.0484   0.0398   1.0000
  13.500   1.2109   0.06741   0.05991  -0.0485   0.0276   1.0000
  13.750   1.2084   0.07085   0.06340  -0.0488   0.0244   1.0000
  14.000   1.2085   0.07404   0.06667  -0.0490   0.0216   1.0000
  14.250   1.2074   0.07746   0.07016  -0.0494   0.0200   1.0000
  14.500   1.2058   0.08099   0.07376  -0.0499   0.0185   1.0000
  14.750   1.2064   0.08430   0.07718  -0.0504   0.0170   1.0000
  15.000   1.2070   0.08764   0.08060  -0.0510   0.0158   1.0000
  15.250   1.2055   0.09133   0.08436  -0.0517   0.0149   1.0000
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