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FX 74-130 WP1 (fx74130wp1-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: FX 74-130 WP1 (fx74130wp1-il)
Reynolds number: 50,000
Max Cl/Cd: 23.75 at α=9.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx74130wp1-il-50000-n5.txt
Download as CSV file: xf-fx74130wp1-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 74-130 WP1                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3257   0.12155   0.11503  -0.0621   0.9675   0.1109
  -9.500  -0.3264   0.11863   0.11215  -0.0639   0.9642   0.1152
  -9.250  -0.3503   0.11709   0.11072  -0.0704   0.9597   0.1186
  -9.000  -0.3285   0.11198   0.10555  -0.0692   0.9583   0.1205
  -8.750  -0.3254   0.10906   0.10264  -0.0682   0.9548   0.1223
  -8.500  -0.3244   0.10616   0.09976  -0.0684   0.9514   0.1242
  -8.250  -0.3247   0.10301   0.09665  -0.0698   0.9481   0.1257
  -8.000  -0.3313   0.09520   0.08877  -0.0767   0.9440   0.0677
  -7.750  -0.3547   0.09202   0.08565  -0.0767   0.9379   0.0587
  -7.500  -0.3594   0.08859   0.08222  -0.0771   0.9341   0.0561
  -7.250  -0.3631   0.08403   0.07759  -0.0797   0.9304   0.0529
  -7.000  -0.3906   0.08042   0.07368  -0.0788   0.9234   0.0482
  -6.750  -0.3860   0.07724   0.07050  -0.0780   0.9205   0.0471
  -6.500  -0.3808   0.07369   0.06685  -0.0784   0.9176   0.0461
  -6.250  -0.3804   0.07056   0.06357  -0.0775   0.9139   0.0451
  -6.000  -0.3812   0.06768   0.06049  -0.0758   0.9099   0.0443
  -5.750  -0.3748   0.06443   0.05699  -0.0754   0.9068   0.0433
  -5.500  -0.3621   0.06082   0.05304  -0.0757   0.9041   0.0427
  -5.250  -0.3443   0.05752   0.04933  -0.0765   0.9017   0.0428
  -5.000  -0.3377   0.05515   0.04663  -0.0745   0.8980   0.0434
  -4.750  -0.3225   0.05262   0.04367  -0.0738   0.8951   0.0444
  -4.500  -0.3019   0.05013   0.04071  -0.0737   0.8926   0.0452
  -4.250  -0.2768   0.04767   0.03774  -0.0740   0.8904   0.0453
  -4.000  -0.2483   0.04545   0.03503  -0.0746   0.8886   0.0455
  -3.750  -0.2262   0.04377   0.03289  -0.0738   0.8861   0.0459
  -3.500  -0.2062   0.04239   0.03115  -0.0725   0.8834   0.0467
  -3.250  -0.1826   0.04131   0.02963  -0.0716   0.8809   0.0485
  -3.000  -0.1587   0.04006   0.02837  -0.0714   0.8785   0.0528
  -2.750  -0.1323   0.03926   0.02737  -0.0709   0.8764   0.0571
  -2.500  -0.1046   0.03857   0.02641  -0.0702   0.8745   0.0607
  -2.250  -0.0857   0.03797   0.02574  -0.0688   0.8718   0.0662
  -2.000  -0.0694   0.03762   0.02523  -0.0670   0.8684   0.0760
  -1.750  -0.0479   0.03705   0.02463  -0.0664   0.8654   0.0910
  -1.500   0.0673   0.03511   0.02587  -0.0748   0.8705   0.9991
  -1.250   0.0752   0.03529   0.02577  -0.0722   0.8661   1.0000
  -1.000   0.0896   0.03551   0.02569  -0.0706   0.8626   1.0000
  -0.750   0.1105   0.03578   0.02568  -0.0701   0.8597   1.0000
  -0.500   0.1063   0.03593   0.02570  -0.0653   0.8539   1.0000
  -0.250   0.1179   0.03616   0.02571  -0.0633   0.8497   1.0000
   0.000   0.1380   0.03646   0.02580  -0.0626   0.8463   1.0000
   0.250   0.1408   0.03666   0.02587  -0.0591   0.8410   1.0000
   0.500   0.1519   0.03692   0.02598  -0.0569   0.8360   1.0000
   0.750   0.1738   0.03729   0.02618  -0.0566   0.8324   1.0000
   1.000   0.1842   0.03760   0.02635  -0.0544   0.8271   1.0000
   1.250   0.1999   0.03797   0.02660  -0.0532   0.8220   1.0000
   1.500   0.2259   0.03844   0.02694  -0.0536   0.8183   1.0000
   1.750   0.2411   0.03888   0.02729  -0.0524   0.8128   1.0000
   2.000   0.2609   0.03936   0.02767  -0.0520   0.8075   1.0000
   2.250   0.2901   0.03991   0.02813  -0.0530   0.8037   1.0000
   2.500   0.3044   0.04043   0.02860  -0.0518   0.7973   1.0000
   2.750   0.3287   0.04097   0.02910  -0.0521   0.7921   1.0000
   3.000   0.3614   0.04157   0.02965  -0.0535   0.7886   1.0000
   3.250   0.3721   0.04212   0.03020  -0.0519   0.7804   1.0000
   3.500   0.4022   0.04270   0.03077  -0.0530   0.7758   1.0000
   3.750   0.4186   0.04331   0.03141  -0.0522   0.7684   1.0000
   4.000   0.4461   0.04388   0.03200  -0.0529   0.7628   1.0000
   4.250   0.4665   0.04450   0.03265  -0.0527   0.7557   1.0000
   4.500   0.4924   0.04506   0.03326  -0.0532   0.7493   1.0000
   4.750   0.5132   0.04567   0.03393  -0.0530   0.7417   1.0000
   5.000   0.5405   0.04619   0.03456  -0.0536   0.7351   1.0000
   5.250   0.5593   0.04681   0.03526  -0.0531   0.7264   1.0000
   5.500   0.5910   0.04721   0.03577  -0.0542   0.7204   1.0000
   5.750   0.6077   0.04783   0.03650  -0.0535   0.7103   1.0000
   6.000   0.6334   0.04827   0.03711  -0.0537   0.7023   1.0000
   6.250   0.6603   0.04862   0.03761  -0.0541   0.6940   1.0000
   6.500   0.6792   0.04915   0.03828  -0.0535   0.6832   1.0000
   6.750   0.7030   0.04951   0.03881  -0.0534   0.6734   1.0000
   7.000   0.7361   0.04944   0.03901  -0.0541   0.6655   1.0000
   7.250   0.7555   0.04980   0.03956  -0.0534   0.6530   1.0000
   7.500   0.7769   0.05001   0.03998  -0.0528   0.6404   1.0000
   7.750   0.7997   0.05006   0.04026  -0.0522   0.6272   1.0000
   8.000   0.8234   0.04995   0.04044  -0.0515   0.6133   1.0000
   8.250   0.8485   0.04955   0.04032  -0.0507   0.5983   1.0000
   8.500   0.8771   0.04861   0.03968  -0.0497   0.5821   1.0000
   8.750   0.8963   0.04808   0.03943  -0.0480   0.5603   1.0000
   9.000   0.9236   0.04636   0.03806  -0.0460   0.5363   1.0000
   9.250   0.9427   0.04522   0.03715  -0.0433   0.4991   1.0000
   9.500   0.9723   0.04299   0.03495  -0.0406   0.4351   1.0000
   9.750   0.9957   0.04192   0.03317  -0.0375   0.3215   1.0000
  10.000   0.9928   0.04415   0.03476  -0.0348   0.2397   1.0000
  10.250   0.9874   0.04700   0.03710  -0.0326   0.1805   1.0000
  10.500   0.9852   0.04985   0.03963  -0.0309   0.1405   1.0000
  10.750   0.9866   0.05252   0.04209  -0.0296   0.1143   1.0000
  11.000   0.9914   0.05494   0.04440  -0.0284   0.0977   1.0000
  11.250   0.9994   0.05716   0.04659  -0.0272   0.0867   1.0000
  11.500   1.0123   0.05899   0.04854  -0.0262   0.0764   1.0000
  11.750   1.0295   0.06059   0.05029  -0.0253   0.0680   1.0000
  12.000   1.0595   0.06160   0.05125  -0.0246   0.0614   1.0000
  12.250   1.0871   0.06310   0.05321  -0.0240   0.0546   1.0000
  12.500   1.1257   0.06485   0.05495  -0.0241   0.0496   1.0000
  12.750   1.1461   0.06777   0.05845  -0.0235   0.0466   1.0000
  13.000   1.1540   0.07093   0.06199  -0.0227   0.0437   1.0000
  13.250   1.1580   0.07415   0.06546  -0.0221   0.0415   1.0000
  13.500   1.1621   0.07774   0.06930  -0.0215   0.0401   1.0000
  13.750   1.1636   0.08188   0.07368  -0.0211   0.0392   1.0000
  14.000   1.1576   0.08654   0.07859  -0.0207   0.0387   1.0000
  14.250   1.1423   0.09136   0.08378  -0.0205   0.0384   1.0000
  14.500   1.1251   0.09653   0.08927  -0.0209   0.0383   1.0000
  14.750   1.1068   0.10210   0.09513  -0.0220   0.0382   1.0000
  15.000   1.0875   0.10815   0.10143  -0.0239   0.0382   1.0000
  15.250   1.0682   0.11468   0.10818  -0.0266   0.0383   1.0000
  15.500   1.0490   0.12181   0.11550  -0.0301   0.0384   1.0000
  15.750   1.0308   0.12944   0.12328  -0.0344   0.0386   1.0000
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