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FX 61-168 AIRFOIL (fx61168-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: FX 61-168 AIRFOIL (fx61168-il)
Reynolds number: 100,000
Max Cl/Cd: 44.66 at α=11.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx61168-il-100000.txt
Download as CSV file: xf-fx61168-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 61-168 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3495   0.09962   0.09534  -0.0486   1.0000   0.1500
  -9.500  -0.3513   0.09672   0.09253  -0.0475   1.0000   0.1587
  -9.250  -0.3670   0.09390   0.08986  -0.0475   1.0000   0.1657
  -9.000  -0.4139   0.09152   0.08776  -0.0465   1.0000   0.1672
  -8.750  -0.4071   0.09190   0.08825  -0.0407   0.9983   0.1734
  -7.750  -0.4693   0.04915   0.04337  -0.0866   0.9252   0.0830
  -7.500  -0.4335   0.04337   0.03668  -0.0891   0.9199   0.0647
  -7.250  -0.4083   0.03960   0.03256  -0.0901   0.9098   0.0626
  -7.000  -0.3681   0.03539   0.02778  -0.0928   0.9058   0.0586
  -6.750  -0.3368   0.03273   0.02463  -0.0934   0.8971   0.0574
  -6.500  -0.2926   0.03023   0.02188  -0.0959   0.8926   0.0583
  -6.250  -0.2501   0.02847   0.01995  -0.0983   0.8876   0.0635
  -6.000  -0.2159   0.02720   0.01847  -0.0987   0.8793   0.0665
  -5.750  -0.1740   0.02514   0.01667  -0.1003   0.8754   0.0735
  -5.500  -0.1514   0.02430   0.01587  -0.0993   0.8661   0.0827
  -5.250  -0.1200   0.02292   0.01458  -0.1005   0.8603   0.1000
  -5.000  -0.1089   0.02158   0.01356  -0.0990   0.8502   0.1452
  -4.750  -0.0952   0.02183   0.01607  -0.0943   0.8442   0.5942
  -4.500  -0.0791   0.02441   0.01854  -0.0883   0.8353   0.6240
  -4.250  -0.0423   0.02832   0.02233  -0.0818   0.8310   0.6541
  -4.000   0.0251   0.03187   0.02561  -0.0790   0.8288   0.6851
  -3.750   0.0293   0.03191   0.02557  -0.0756   0.8195   0.6982
  -3.500   0.0747   0.03172   0.02514  -0.0777   0.8149   0.7050
  -3.250   0.0812   0.03160   0.02493  -0.0748   0.8073   0.7155
  -3.000   0.0944   0.03132   0.02451  -0.0737   0.8007   0.7274
  -2.750   0.1347   0.03114   0.02416  -0.0749   0.7961   0.7330
  -2.500   0.1314   0.03111   0.02411  -0.0708   0.7881   0.7437
  -2.250   0.1708   0.03085   0.02366  -0.0724   0.7838   0.7503
  -2.000   0.1674   0.03090   0.02371  -0.0681   0.7767   0.7596
  -1.750   0.1918   0.03077   0.02348  -0.0676   0.7712   0.7665
  -1.500   0.2185   0.03043   0.02299  -0.0682   0.7671   0.7747
  -1.250   0.2129   0.03076   0.02337  -0.0630   0.7592   0.7814
  -1.000   0.2321   0.03052   0.02303  -0.0625   0.7542   0.7892
  -0.750   0.2519   0.03053   0.02298  -0.0612   0.7488   0.7953
  -0.500   0.2479   0.03075   0.02320  -0.0570   0.7414   0.8039
  -0.250   0.2872   0.03040   0.02274  -0.0587   0.7377   0.8099
   0.000   0.2687   0.03097   0.02336  -0.0527   0.7290   0.8177
   0.250   0.2956   0.03078   0.02312  -0.0525   0.7243   0.8224
   0.500   0.3365   0.03038   0.02260  -0.0550   0.7211   0.8276
   0.750   0.3084   0.03133   0.02363  -0.0477   0.7110   0.8339
   1.000   0.3452   0.03097   0.02320  -0.0491   0.7074   0.8383
   1.250   0.3337   0.03183   0.02412  -0.0444   0.6986   0.8441
   1.500   0.3592   0.03179   0.02404  -0.0448   0.6935   0.8488
   1.750   0.4032   0.03128   0.02345  -0.0471   0.6907   0.8526
   2.000   0.3798   0.03265   0.02490  -0.0411   0.6796   0.8583
   2.250   0.4255   0.03220   0.02439  -0.0443   0.6764   0.8625
   2.500   0.4036   0.03360   0.02587  -0.0383   0.6653   0.8672
   2.750   0.4480   0.03306   0.02529  -0.0407   0.6618   0.8710
   3.000   0.5017   0.03236   0.02453  -0.0446   0.6596   0.8750
   3.250   0.4763   0.03413   0.02640  -0.0387   0.6471   0.8798
   3.500   0.4618   0.03575   0.02809  -0.0345   0.6363   0.8846
   3.750   0.5033   0.03536   0.02769  -0.0366   0.6322   0.8886
   4.000   0.5583   0.03458   0.02691  -0.0403   0.6300   0.8920
   4.250   0.5284   0.03691   0.02932  -0.0345   0.6170   0.8970
   4.500   0.5797   0.03594   0.02836  -0.0372   0.6148   0.9005
   4.750   0.6409   0.03484   0.02725  -0.0413   0.6132   0.9040
   5.000   0.5546   0.04071   0.03326  -0.0319   0.5900   0.9107
   5.250   0.5947   0.03993   0.03251  -0.0329   0.5861   0.9146
   5.500   0.6482   0.03849   0.03112  -0.0351   0.5843   0.9184
   5.750   0.7058   0.03696   0.02961  -0.0379   0.5829   0.9218
   6.000   0.6237   0.04417   0.03694  -0.0315   0.5584   0.9294
   6.250   0.6674   0.04315   0.03597  -0.0326   0.5552   0.9338
   6.500   0.6869   0.04370   0.03661  -0.0322   0.5486   0.9392
   6.750   0.7572   0.04053   0.03351  -0.0344   0.5503   0.9432
   7.000   0.8447   0.03697   0.03002  -0.0393   0.5517   0.9459
   7.250   0.8017   0.04107   0.03424  -0.0341   0.5349   0.9555
   7.500   0.8914   0.03706   0.03033  -0.0387   0.5361   0.9589
   7.750   0.8034   0.04585   0.03924  -0.0339   0.5098   0.9746
   8.000   0.8694   0.04275   0.03629  -0.0359   0.5091   0.9856
   8.250   0.9541   0.03851   0.03217  -0.0395   0.5087   1.0000
   8.500   1.0564   0.03412   0.02788  -0.0462   0.5070   1.0000
   8.750   1.0474   0.03614   0.03005  -0.0437   0.4946   1.0000
   9.000   1.0550   0.03758   0.03163  -0.0431   0.4835   1.0000
   9.250   1.1563   0.03299   0.02714  -0.0496   0.4789   1.0000
   9.500   1.1733   0.03340   0.02771  -0.0492   0.4674   1.0000
   9.750   1.2195   0.03229   0.02672  -0.0514   0.4571   1.0000
  10.000   1.2719   0.03078   0.02528  -0.0543   0.4449   1.0000
  10.250   1.3048   0.03017   0.02473  -0.0551   0.4303   1.0000
  10.500   1.3286   0.03006   0.02469  -0.0549   0.4144   1.0000
  10.750   1.3457   0.03026   0.02496  -0.0541   0.3969   1.0000
  11.000   1.3615   0.03057   0.02532  -0.0533   0.3780   1.0000
  11.250   1.3791   0.03088   0.02556  -0.0526   0.3579   1.0000
  11.500   1.3795   0.03233   0.02710  -0.0509   0.3394   1.0000
  11.750   1.3809   0.03395   0.02878  -0.0495   0.3207   1.0000
  12.000   1.3825   0.03569   0.03051  -0.0484   0.3017   1.0000
  12.250   1.3833   0.03767   0.03243  -0.0475   0.2828   1.0000
  12.500   1.3783   0.04031   0.03511  -0.0468   0.2645   1.0000
  12.750   1.3733   0.04310   0.03790  -0.0462   0.2462   1.0000
  13.000   1.3685   0.04600   0.04072  -0.0457   0.2283   1.0000
  13.250   1.3632   0.04907   0.04368  -0.0454   0.2108   1.0000
  13.500   1.3545   0.05267   0.04732  -0.0453   0.1937   1.0000
  13.750   1.3460   0.05637   0.05097  -0.0454   0.1770   1.0000
  14.000   1.3373   0.06024   0.05478  -0.0456   0.1607   1.0000
  14.250   1.3286   0.06426   0.05874  -0.0459   0.1457   1.0000
  14.500   1.3212   0.06828   0.06270  -0.0464   0.1318   1.0000
  14.750   1.3158   0.07222   0.06659  -0.0469   0.1193   1.0000
  15.000   1.3112   0.07615   0.07049  -0.0476   0.1084   1.0000
  15.250   1.3076   0.07998   0.07425  -0.0485   0.0990   1.0000
  15.500   1.3017   0.08436   0.07871  -0.0498   0.0909   1.0000
  15.750   1.2986   0.08841   0.08282  -0.0509   0.0833   1.0000
  16.000   1.2965   0.09222   0.08655  -0.0520   0.0763   1.0000
  16.250   1.2902   0.09703   0.09157  -0.0538   0.0702   1.0000
  16.500   1.2887   0.10081   0.09521  -0.0551   0.0637   1.0000
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