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FX 68-H-120 (fx68h120-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: FX 68-H-120 (fx68h120-il)
Reynolds number: 50,000
Max Cl/Cd: 29.22 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx68h120-il-50000-n5.txt
Download as CSV file: xf-fx68h120-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 68-H-120                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.4564   0.09695   0.09051  -0.0311   1.0000   0.0432
 -10.250  -0.4635   0.09099   0.08464  -0.0343   1.0000   0.0433
 -10.000  -0.4736   0.08445   0.07819  -0.0381   1.0000   0.0432
  -9.750  -0.4858   0.07742   0.07125  -0.0426   1.0000   0.0427
  -9.500  -0.5066   0.06908   0.06295  -0.0493   1.0000   0.0419
  -9.250  -0.5317   0.06338   0.05723  -0.0523   1.0000   0.0413
  -9.000  -0.5572   0.05940   0.05318  -0.0515   1.0000   0.0409
  -8.750  -0.5813   0.05597   0.04961  -0.0490   1.0000   0.0407
  -8.500  -0.6023   0.05307   0.04653  -0.0453   1.0000   0.0407
  -8.250  -0.6190   0.05021   0.04343  -0.0415   1.0000   0.0408
  -8.000  -0.6314   0.04725   0.04013  -0.0377   1.0000   0.0414
  -7.750  -0.6377   0.04445   0.03696  -0.0342   1.0000   0.0422
  -7.500  -0.6395   0.04171   0.03373  -0.0309   1.0000   0.0437
  -7.250  -0.6363   0.03958   0.03141  -0.0280   1.0000   0.0461
  -7.000  -0.6292   0.03814   0.02989  -0.0255   1.0000   0.0490
  -6.750  -0.6206   0.03618   0.02761  -0.0230   1.0000   0.0523
  -6.500  -0.6092   0.03399   0.02495  -0.0205   1.0000   0.0558
  -6.250  -0.5975   0.03262   0.02360  -0.0183   1.0000   0.0608
  -6.000  -0.5836   0.03122   0.02197  -0.0163   1.0000   0.0699
  -5.750  -0.5687   0.03004   0.02070  -0.0143   1.0000   0.0817
  -5.500  -0.5543   0.02947   0.02019  -0.0125   1.0000   0.0989
  -5.250  -0.5385   0.02886   0.01942  -0.0106   1.0000   0.1229
  -5.000  -0.5198   0.02859   0.01887  -0.0095   0.9985   0.1493
  -4.750  -0.4935   0.02841   0.01861  -0.0099   0.9940   0.1741
  -4.500  -0.4667   0.02799   0.01801  -0.0102   0.9894   0.1950
  -4.250  -0.4369   0.02754   0.01742  -0.0110   0.9850   0.2123
  -4.000  -0.4070   0.02704   0.01673  -0.0117   0.9805   0.2269
  -3.750  -0.3752   0.02659   0.01612  -0.0127   0.9756   0.2411
  -3.500  -0.3391   0.02621   0.01555  -0.0146   0.9711   0.2551
  -3.250  -0.3061   0.02584   0.01507  -0.0158   0.9649   0.2699
  -3.000  -0.2656   0.02553   0.01466  -0.0185   0.9590   0.2873
  -2.750  -0.2319   0.02523   0.01429  -0.0198   0.9511   0.3071
  -2.500  -0.1922   0.02490   0.01401  -0.0223   0.9438   0.3344
  -2.250  -0.1589   0.02451   0.01378  -0.0235   0.9346   0.3698
  -2.000  -0.1264   0.02401   0.01362  -0.0246   0.9252   0.4327
  -1.750  -0.0895   0.02324   0.01360  -0.0258   0.9171   0.5724
  -1.500   0.0473   0.02286   0.01395  -0.0438   0.9161   0.9249
  -1.250   0.1326   0.02295   0.01371  -0.0544   0.9083   0.9914
  -1.000   0.1798   0.02292   0.01346  -0.0582   0.8971   1.0000
  -0.750   0.2121   0.02289   0.01325  -0.0590   0.8839   1.0000
  -0.500   0.2419   0.02284   0.01306  -0.0592   0.8700   1.0000
  -0.250   0.2697   0.02276   0.01287  -0.0588   0.8552   1.0000
   0.000   0.2961   0.02264   0.01265  -0.0581   0.8395   1.0000
   0.250   0.3217   0.02248   0.01240  -0.0571   0.8232   1.0000
   0.500   0.3471   0.02226   0.01211  -0.0559   0.8063   1.0000
   0.750   0.3667   0.02211   0.01190  -0.0538   0.7865   1.0000
   1.000   0.3880   0.02186   0.01160  -0.0518   0.7659   1.0000
   1.250   0.4075   0.02165   0.01134  -0.0495   0.7429   1.0000
   1.500   0.4277   0.02139   0.01103  -0.0473   0.7176   1.0000
   1.750   0.4470   0.02120   0.01079  -0.0449   0.6875   1.0000
   2.000   0.4683   0.02096   0.01048  -0.0428   0.6541   1.0000
   2.250   0.4918   0.02070   0.01006  -0.0409   0.6175   1.0000
   2.500   0.5167   0.02049   0.00957  -0.0391   0.5791   1.0000
   2.750   0.5395   0.02054   0.00930  -0.0373   0.5411   1.0000
   3.000   0.5604   0.02084   0.00930  -0.0355   0.5069   1.0000
   3.250   0.5801   0.02129   0.00949  -0.0338   0.4766   1.0000
   3.500   0.5997   0.02181   0.00977  -0.0322   0.4509   1.0000
   3.750   0.6191   0.02235   0.01016  -0.0307   0.4272   1.0000
   4.000   0.6388   0.02291   0.01058  -0.0293   0.4069   1.0000
   4.250   0.6588   0.02348   0.01106  -0.0280   0.3881   1.0000
   4.500   0.6791   0.02405   0.01154  -0.0267   0.3713   1.0000
   4.750   0.6998   0.02464   0.01205  -0.0255   0.3561   1.0000
   5.000   0.7210   0.02524   0.01264  -0.0245   0.3425   1.0000
   5.250   0.7429   0.02586   0.01323  -0.0235   0.3305   1.0000
   5.500   0.7652   0.02649   0.01382  -0.0226   0.3195   1.0000
   5.750   0.7875   0.02712   0.01443  -0.0218   0.3092   1.0000
   6.000   0.8094   0.02780   0.01519  -0.0209   0.2991   1.0000
   6.250   0.8323   0.02850   0.01594  -0.0201   0.2911   1.0000
   6.500   0.8550   0.02926   0.01678  -0.0194   0.2836   1.0000
   6.750   0.8782   0.03005   0.01761  -0.0187   0.2772   1.0000
   7.000   0.8998   0.03089   0.01859  -0.0179   0.2704   1.0000
   7.250   0.9229   0.03168   0.01939  -0.0172   0.2649   1.0000
   7.500   0.9424   0.03267   0.02067  -0.0162   0.2586   1.0000
   7.750   0.9645   0.03355   0.02164  -0.0155   0.2537   1.0000
   8.000   0.9860   0.03460   0.02285  -0.0147   0.2497   1.0000
   8.250   1.0043   0.03586   0.02440  -0.0137   0.2455   1.0000
   8.500   1.0241   0.03704   0.02579  -0.0128   0.2419   1.0000
   8.750   1.0461   0.03811   0.02699  -0.0121   0.2387   1.0000
   9.000   1.0588   0.03938   0.02856  -0.0105   0.2333   1.0000
   9.250   1.0715   0.03933   0.02854  -0.0085   0.2218   1.0000
   9.500   1.0764   0.03927   0.02847  -0.0056   0.2084   1.0000
   9.750   1.0781   0.03971   0.02906  -0.0027   0.1972   1.0000
  10.000   1.0840   0.04068   0.03029  -0.0004   0.1904   1.0000
  10.250   1.0840   0.04108   0.03068   0.0027   0.1805   1.0000
  10.500   1.0793   0.04221   0.03204   0.0058   0.1718   1.0000
  10.750   1.0780   0.04338   0.03335   0.0082   0.1641   1.0000
  11.000   1.0745   0.04471   0.03479   0.0103   0.1548   1.0000
  11.250   1.0685   0.04674   0.03704   0.0119   0.1432   1.0000
  11.500   1.0666   0.04895   0.03949   0.0128   0.1339   1.0000
  11.750   1.0648   0.05132   0.04207   0.0135   0.1261   1.0000
  12.000   1.0588   0.05452   0.04557   0.0136   0.1140   1.0000
  12.250   1.0482   0.05875   0.05016   0.0129   0.1011   1.0000
  12.500   1.0305   0.06435   0.05609   0.0113   0.0913   1.0000
  13.000   0.9933   0.07575   0.06698   0.0063   0.0459   1.0000
  13.500   0.9259   0.09683   0.08908  -0.0030   0.1136   1.0000
  13.750   0.9025   0.10533   0.09761  -0.0067   0.1127   1.0000
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