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Fage & Collins 3 (fg3-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: Fage & Collins 3 (fg3-il)
Reynolds number: 1,000,000
Max Cl/Cd: 108.33 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fg3-il-1000000-n5.txt
Download as CSV file: xf-fg3-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Fage & Collins 3                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2867   0.09210   0.09047  -0.0511   0.9893   0.0045
  -9.500  -0.2649   0.08976   0.08813  -0.0553   0.9867   0.0050
  -9.000  -0.2758   0.08116   0.07956  -0.0573   0.9430   0.0048
  -8.750  -0.2507   0.07602   0.07439  -0.0659   0.9354   0.0051
  -8.500  -0.2229   0.06952   0.06785  -0.0782   0.9284   0.0057
  -8.250  -0.2033   0.05108   0.04912  -0.1066   0.9119   0.0066
  -7.750  -0.1483   0.04396   0.04171  -0.1171   0.8937   0.0071
  -7.500  -0.1389   0.03958   0.03713  -0.1181   0.8839   0.0074
  -7.000  -0.1581   0.02637   0.02312  -0.1102   0.8687   0.0092
  -6.750  -0.1399   0.02540   0.02204  -0.1088   0.8613   0.0095
  -6.250  -0.1325   0.01769   0.01350  -0.1001   0.8486   0.0121
  -6.000  -0.1109   0.01726   0.01298  -0.0990   0.8413   0.0123
  -5.750  -0.0872   0.01731   0.01302  -0.0982   0.8331   0.0126
  -5.500  -0.0649   0.01713   0.01276  -0.0971   0.8233   0.0131
  -5.250  -0.0556   0.01339   0.00841  -0.0931   0.8138   0.0159
  -5.000  -0.0335   0.01317   0.00811  -0.0918   0.8020   0.0161
  -4.750  -0.0104   0.01339   0.00830  -0.0908   0.7881   0.0164
  -4.500   0.0111   0.01337   0.00821  -0.0894   0.7709   0.0167
  -4.250   0.0317   0.01317   0.00787  -0.0879   0.7497   0.0172
  -4.000   0.0516   0.01297   0.00751  -0.0861   0.7261   0.0178
  -3.750   0.0718   0.01259   0.00694  -0.0843   0.7018   0.0187
  -3.500   0.0916   0.01212   0.00623  -0.0825   0.6745   0.0196
  -3.250   0.1102   0.01194   0.00582  -0.0804   0.6363   0.0201
  -3.000   0.1285   0.01200   0.00563  -0.0782   0.5893   0.0205
  -2.750   0.1459   0.01181   0.00517  -0.0760   0.5388   0.0209
  -2.500   0.1656   0.01139   0.00458  -0.0743   0.5048   0.0213
  -2.250   0.1856   0.01123   0.00425  -0.0727   0.4704   0.0215
  -2.000   0.2071   0.01108   0.00399  -0.0713   0.4474   0.0218
  -1.750   0.2290   0.01090   0.00372  -0.0701   0.4296   0.0220
  -1.500   0.2512   0.01078   0.00353  -0.0689   0.4140   0.0225
  -1.250   0.2735   0.01065   0.00333  -0.0677   0.4007   0.0229
  -1.000   0.2954   0.01049   0.00310  -0.0664   0.3883   0.0232
  -0.750   0.3174   0.01036   0.00291  -0.0651   0.3768   0.0236
  -0.250   0.3619   0.01016   0.00260  -0.0627   0.3585   0.0247
   0.000   0.3841   0.01011   0.00250  -0.0615   0.3505   0.0252
   0.250   0.4070   0.01003   0.00239  -0.0604   0.3441   0.0255
   0.500   0.4292   0.00998   0.00230  -0.0593   0.3372   0.0256
   0.750   0.4522   0.00993   0.00223  -0.0582   0.3317   0.0259
   1.000   0.4749   0.00991   0.00217  -0.0571   0.3258   0.0261
   1.250   0.4976   0.00991   0.00215  -0.0561   0.3197   0.0264
   1.500   0.5209   0.00991   0.00213  -0.0551   0.3150   0.0266
   1.750   0.5435   0.00990   0.00210  -0.0540   0.3096   0.0267
   2.000   0.5660   0.00991   0.00208  -0.0529   0.3047   0.0268
   2.250   0.5891   0.00990   0.00207  -0.0520   0.3009   0.0268
   2.500   0.6117   0.00990   0.00205  -0.0509   0.2965   0.0273
   2.750   0.6338   0.00993   0.00205  -0.0497   0.2925   0.0281
   3.000   0.6559   0.00995   0.00206  -0.0485   0.2892   0.0292
   3.250   0.6781   0.00998   0.00209  -0.0474   0.2858   0.0307
   3.500   0.6998   0.01003   0.00215  -0.0462   0.2819   0.0320
   3.750   0.7213   0.01010   0.00221  -0.0449   0.2783   0.0335
   4.000   0.7431   0.01017   0.00228  -0.0437   0.2751   0.0349
   4.250   0.9995   0.00940   0.00351  -0.0980   0.2604   1.0000
   4.500   1.0226   0.00951   0.00363  -0.0971   0.2565   1.0000
   4.750   1.0440   0.00971   0.00377  -0.0960   0.2465   1.0000
   5.000   1.0663   0.00986   0.00391  -0.0950   0.2388   1.0000
   5.250   1.0877   0.01006   0.00407  -0.0938   0.2315   1.0000
   5.500   1.1093   0.01024   0.00423  -0.0927   0.2222   1.0000
   5.750   1.1305   0.01044   0.00441  -0.0915   0.2146   1.0000
   6.000   1.1507   0.01071   0.00462  -0.0902   0.2027   1.0000
   6.250   1.1686   0.01110   0.00489  -0.0884   0.1790   1.0000
   6.500   1.1726   0.01238   0.00571  -0.0842   0.1030   1.0000
   6.750   1.1746   0.01387   0.00679  -0.0795   0.0205   1.0000
   7.000   1.1931   0.01423   0.00715  -0.0779   0.0143   1.0000
   7.250   1.2117   0.01456   0.00749  -0.0763   0.0124   1.0000
   7.500   1.2293   0.01494   0.00790  -0.0745   0.0101   1.0000
   7.750   1.2471   0.01526   0.00825  -0.0728   0.0095   1.0000
   8.000   1.2632   0.01557   0.00859  -0.0707   0.0089   1.0000
   8.250   1.2773   0.01592   0.00898  -0.0683   0.0082   1.0000
   8.500   1.2904   0.01633   0.00942  -0.0656   0.0073   1.0000
   8.750   1.3033   0.01676   0.00989  -0.0630   0.0068   1.0000
   9.000   1.3177   0.01712   0.01029  -0.0607   0.0064   1.0000
   9.250   1.3313   0.01755   0.01077  -0.0584   0.0059   1.0000
   9.500   1.3455   0.01795   0.01120  -0.0562   0.0056   1.0000
   9.750   1.3579   0.01847   0.01177  -0.0538   0.0052   1.0000
  10.000   1.3698   0.01902   0.01237  -0.0513   0.0051   1.0000
  10.250   1.3774   0.01983   0.01326  -0.0482   0.0046   1.0000
  10.500   1.3910   0.02032   0.01378  -0.0462   0.0044   1.0000
  10.750   1.4000   0.02107   0.01462  -0.0435   0.0043   1.0000
  11.000   1.4127   0.02164   0.01522  -0.0415   0.0041   1.0000
  11.250   1.4190   0.02259   0.01627  -0.0387   0.0040   1.0000
  11.500   1.4304   0.02327   0.01700  -0.0368   0.0037   1.0000
  11.750   1.4328   0.02455   0.01839  -0.0338   0.0037   1.0000
  12.000   1.4437   0.02531   0.01919  -0.0321   0.0035   1.0000
  12.250   1.4485   0.02653   0.02048  -0.0297   0.0034   1.0000
  12.500   1.4546   0.02770   0.02172  -0.0277   0.0033   1.0000
  12.750   1.4565   0.02923   0.02332  -0.0254   0.0031   1.0000
  13.000   1.4537   0.03121   0.02541  -0.0230   0.0030   1.0000
  13.250   1.4547   0.03300   0.02730  -0.0211   0.0031   1.0000
  13.500   1.4498   0.03542   0.02984  -0.0193   0.0030   1.0000
  13.750   1.4445   0.03809   0.03263  -0.0177   0.0029   1.0000
  14.000   1.4447   0.04036   0.03499  -0.0168   0.0029   1.0000
  14.250   1.4488   0.04238   0.03709  -0.0163   0.0027   1.0000
  14.500   1.4327   0.04685   0.04172  -0.0158   0.0028   1.0000
  14.750   1.4260   0.05054   0.04552  -0.0159   0.0027   1.0000
  15.000   1.4136   0.05526   0.05038  -0.0165   0.0027   1.0000
  15.250   1.4087   0.05918   0.05440  -0.0173   0.0026   1.0000
  15.500   1.3900   0.06528   0.06065  -0.0188   0.0027   1.0000
  15.750   1.3841   0.06952   0.06498  -0.0199   0.0027   1.0000
  16.000   1.3615   0.07632   0.07193  -0.0217   0.0027   1.0000
  16.250   1.3474   0.08183   0.07754  -0.0232   0.0025   1.0000
  16.500   1.3309   0.08768   0.08350  -0.0247   0.0026   1.0000
  16.750   1.3275   0.09161   0.08750  -0.0259   0.0025   1.0000
  17.000   1.3140   0.09711   0.09310  -0.0274   0.0024   1.0000
  17.250   1.3006   0.10259   0.09868  -0.0290   0.0025   1.0000
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