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FX 84-W-175 (fx84w175-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: FX 84-W-175 (fx84w175-il)
Reynolds number: 50,000
Max Cl/Cd: 10.29 at α=8.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx84w175-il-50000-n5.txt
Download as CSV file: xf-fx84w175-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 84-W-175                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.2405   0.11867   0.11142  -0.0807   0.9610   0.0792
 -11.500  -0.2366   0.11320   0.10593  -0.0855   0.9573   0.0795
 -11.250  -0.2414   0.10761   0.10035  -0.0895   0.9511   0.0800
 -11.000  -0.2313   0.10366   0.09640  -0.0925   0.9464   0.0811
 -10.750  -0.2270   0.09803   0.09074  -0.0974   0.9428   0.0814
 -10.500  -0.2441   0.09101   0.08374  -0.1018   0.9352   0.0809
 -10.250  -0.2906   0.07784   0.07045  -0.1129   0.9282   0.0800
 -10.000  -0.3217   0.07254   0.06507  -0.1152   0.9178   0.0797
  -9.750  -0.3548   0.06780   0.06014  -0.1166   0.9087   0.0797
  -9.500  -0.3858   0.06506   0.05725  -0.1138   0.8978   0.0797
  -9.250  -0.4128   0.06229   0.05423  -0.1108   0.8882   0.0799
  -9.000  -0.4147   0.06019   0.05201  -0.1094   0.8811   0.0812
  -8.750  -0.3978   0.05842   0.05017  -0.1100   0.8771   0.0835
  -8.500  -0.4150   0.05719   0.04880  -0.1052   0.8669   0.0843
  -8.250  -0.4113   0.05463   0.04591  -0.1044   0.8616   0.0862
  -8.000  -0.4193   0.05286   0.04385  -0.1008   0.8537   0.0875
  -7.750  -0.4191   0.05062   0.04118  -0.0985   0.8470   0.0895
  -7.500  -0.4011   0.04858   0.03882  -0.0985   0.8431   0.0926
  -7.250  -0.3996   0.04795   0.03813  -0.0952   0.8355   0.0947
  -7.000  -0.3867   0.04670   0.03668  -0.0937   0.8297   0.0978
  -6.750  -0.3644   0.04488   0.03438  -0.0938   0.8260   0.1023
  -6.500  -0.3536   0.04409   0.03351  -0.0917   0.8200   0.1056
  -6.250  -0.3431   0.04347   0.03283  -0.0895   0.8133   0.1092
  -6.000  -0.3178   0.04228   0.03130  -0.0896   0.8094   0.1153
  -5.750  -0.2862   0.04129   0.03027  -0.0906   0.8067   0.1217
  -5.500  -0.2887   0.04116   0.03008  -0.0862   0.7980   0.1254
  -5.250  -0.2657   0.04043   0.02917  -0.0857   0.7934   0.1330
  -5.000  -0.2353   0.03971   0.02840  -0.0864   0.7902   0.1424
  -4.750  -0.2256   0.03948   0.02811  -0.0838   0.7838   0.1495
  -4.500  -0.2104   0.03920   0.02780  -0.0822   0.7778   0.1587
  -4.250  -0.1833   0.03866   0.02725  -0.0822   0.7740   0.1716
  -4.000  -0.1511   0.03804   0.02661  -0.0830   0.7714   0.1886
  -3.750  -0.1539   0.03831   0.02685  -0.0788   0.7626   0.1984
  -3.500  -0.1313   0.03791   0.02652  -0.0783   0.7581   0.2180
  -3.250  -0.1023   0.03735   0.02604  -0.0787   0.7550   0.2469
  -3.000  -0.0960   0.03743   0.02623  -0.0761   0.7480   0.2708
  -2.750  -0.0805   0.03718   0.02619  -0.0748   0.7425   0.3085
  -2.500  -0.0568   0.03658   0.02598  -0.0743   0.7388   0.3756
  -2.250  -0.0315   0.03597   0.02596  -0.0734   0.7362   0.4832
  -2.000  -0.0380   0.03666   0.02697  -0.0684   0.7270   0.5488
  -1.750  -0.0207   0.03686   0.02741  -0.0654   0.7228   0.6399
  -1.500   0.0021   0.03706   0.02765  -0.0630   0.7198   0.7092
  -1.250  -0.0002   0.03794   0.02853  -0.0585   0.7115   0.7480
  -1.000   0.0152   0.03835   0.02891  -0.0555   0.7067   0.7909
  -0.750   0.0384   0.03859   0.02905  -0.0534   0.7034   0.8313
  -0.500   0.0450   0.03934   0.02976  -0.0501   0.6965   0.8645
  -0.250   0.0690   0.03988   0.03022  -0.0493   0.6911   0.8997
   0.000   0.1208   0.04038   0.03055  -0.0531   0.6880   0.9350
   0.250   0.2029   0.04096   0.03089  -0.0626   0.6861   0.9661
   0.750   0.2817   0.04257   0.03223  -0.0708   0.6738   1.0000
   1.000   0.2928   0.04251   0.03204  -0.0687   0.6698   1.0000
   1.250   0.2707   0.04324   0.03272  -0.0627   0.6611   1.0000
   1.500   0.2778   0.04354   0.03288  -0.0604   0.6555   1.0000
   1.750   0.3008   0.04363   0.03282  -0.0599   0.6522   1.0000
   2.000   0.2941   0.04484   0.03395  -0.0567   0.6434   1.0000
   2.250   0.3139   0.04533   0.03431  -0.0563   0.6384   1.0000
   2.500   0.3425   0.04556   0.03442  -0.0566   0.6353   1.0000
   2.750   0.3418   0.04702   0.03581  -0.0545   0.6265   1.0000
   3.000   0.3634   0.04764   0.03633  -0.0543   0.6217   1.0000
   3.250   0.3931   0.04792   0.03651  -0.0548   0.6185   1.0000
   3.500   0.3935   0.04956   0.03811  -0.0530   0.6097   1.0000
   3.750   0.4155   0.05025   0.03872  -0.0529   0.6048   1.0000
   4.000   0.4457   0.05054   0.03894  -0.0534   0.6017   1.0000
   4.250   0.4451   0.05239   0.04077  -0.0517   0.5925   1.0000
   4.500   0.4678   0.05309   0.04142  -0.0517   0.5878   1.0000
   4.750   0.4981   0.05340   0.04168  -0.0521   0.5847   1.0000
   5.000   0.4956   0.05549   0.04377  -0.0505   0.5750   1.0000
   5.250   0.5198   0.05614   0.04439  -0.0505   0.5706   1.0000
   5.500   0.5505   0.05642   0.04464  -0.0510   0.5677   1.0000
   5.750   0.5454   0.05880   0.04704  -0.0493   0.5572   1.0000
   6.000   0.5713   0.05937   0.04760  -0.0495   0.5532   1.0000
   6.250   0.6028   0.05957   0.04779  -0.0499   0.5505   1.0000
   6.500   0.5945   0.06229   0.05053  -0.0483   0.5392   1.0000
   6.750   0.6224   0.06271   0.05097  -0.0485   0.5356   1.0000
   7.000   0.6225   0.06502   0.05331  -0.0474   0.5264   1.0000
   7.250   0.6440   0.06585   0.05416  -0.0473   0.5211   1.0000
   7.500   0.6742   0.06606   0.05440  -0.0475   0.5179   1.0000
   7.750   0.6678   0.06892   0.05731  -0.0464   0.5069   1.0000
   8.000   0.6949   0.06931   0.05773  -0.0464   0.5028   1.0000
   8.500   0.7166   0.07259   0.06112  -0.0455   0.4879   1.0000
   8.750   0.7475   0.07261   0.06120  -0.0456   0.4847   1.0000
   9.000   0.7393   0.07588   0.06453  -0.0447   0.4730   1.0000
   9.250   0.7679   0.07602   0.06472  -0.0446   0.4691   1.0000
   9.500   0.7631   0.07912   0.06790  -0.0440   0.4582   1.0000
   9.750   0.7890   0.07943   0.06829  -0.0439   0.4535   1.0000
  10.000   0.7879   0.08228   0.07122  -0.0434   0.4433   1.0000
  10.250   0.8104   0.08288   0.07190  -0.0432   0.4378   1.0000
  10.750   0.8319   0.08636   0.07556  -0.0427   0.4220   1.0000
  11.000   0.8642   0.08585   0.07514  -0.0424   0.4188   1.0000
  11.250   0.8537   0.08983   0.07921  -0.0422   0.4060   1.0000
  11.500   0.8853   0.08926   0.07876  -0.0418   0.4026   1.0000
  11.750   0.8756   0.09328   0.08286  -0.0417   0.3898   1.0000
  12.000   0.9070   0.09260   0.08229  -0.0413   0.3863   1.0000
  12.250   0.8976   0.09670   0.08649  -0.0414   0.3734   1.0000
  12.500   0.9288   0.09586   0.08577  -0.0408   0.3697   1.0000
  12.750   0.9201   0.10001   0.09003  -0.0411   0.3569   1.0000
  13.250   0.9436   0.10306   0.09330  -0.0407   0.3401   1.0000
  13.750   0.9696   0.10549   0.09598  -0.0402   0.3232   1.0000
  14.250   0.9992   0.10709   0.09781  -0.0395   0.3064   1.0000
  14.750   0.9911   0.11477   0.10569  -0.0409   0.2813   1.0000
  15.250   1.0189   0.11638   0.10755  -0.0403   0.2629   1.0000
  15.500   1.0613   0.11195   0.10327  -0.0381   0.2588   1.0000
  15.750   1.0546   0.11631   0.10773  -0.0392   0.2453   1.0000
  16.000   1.0526   0.11998   0.11150  -0.0402   0.2328   1.0000
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