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GOE 744 AIRFOIL (goe744-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 744 AIRFOIL (goe744-il)
Reynolds number: 500,000
Max Cl/Cd: 98.9 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe744-il-500000.txt
Download as CSV file: xf-goe744-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 744 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.1977   0.09717   0.09325   0.0045   0.5182   0.0316
  -8.000  -0.2165   0.09327   0.08939  -0.0012   0.5176   0.0321
  -7.750  -0.2224   0.08986   0.08602  -0.0041   0.5163   0.0321
  -7.500  -0.2108   0.08679   0.08297  -0.0037   0.5143   0.0323
  -7.250  -0.1992   0.08434   0.08053  -0.0035   0.5121   0.0324
  -7.000  -0.1937   0.08194   0.07813  -0.0038   0.5100   0.0326
  -6.750  -0.1870   0.07974   0.07593  -0.0040   0.5079   0.0328
  -6.500  -0.1786   0.07727   0.07345  -0.0051   0.5060   0.0330
  -6.250  -0.1696   0.07474   0.07088  -0.0064   0.5040   0.0333
  -6.000  -0.1595   0.07217   0.06827  -0.0079   0.5018   0.0337
  -5.750  -0.1482   0.06945   0.06553  -0.0096   0.4998   0.0342
  -5.500  -0.1354   0.06650   0.06256  -0.0116   0.4983   0.0350
  -5.250  -0.1229   0.05940   0.05527  -0.0186   0.4973   0.0366
  -5.000  -0.1069   0.05726   0.05313  -0.0185   0.4950   0.0368
  -4.750  -0.0892   0.05524   0.05110  -0.0186   0.4926   0.0370
  -4.500  -0.0706   0.05326   0.04908  -0.0189   0.4904   0.0374
  -4.250  -0.0509   0.05110   0.04686  -0.0194   0.4883   0.0378
  -4.000  -0.0249   0.04306   0.03833  -0.0231   0.4870   0.0413
  -3.750  -0.0063   0.04154   0.03680  -0.0227   0.4846   0.0416
  -3.500   0.0139   0.04034   0.03555  -0.0224   0.4817   0.0418
  -3.250   0.0359   0.03890   0.03410  -0.0222   0.4798   0.0422
  -3.000   0.0587   0.03739   0.03255  -0.0221   0.4777   0.0428
  -2.750   0.0805   0.03098   0.02550  -0.0214   0.4761   0.0469
  -2.500   0.1041   0.02985   0.02443  -0.0212   0.4736   0.0473
  -2.250   0.1285   0.02901   0.02357  -0.0209   0.4710   0.0479
  -2.000   0.1531   0.02803   0.02251  -0.0205   0.4685   0.0488
  -1.750   0.1755   0.02473   0.01863  -0.0190   0.4665   0.0534
  -1.500   0.2006   0.02389   0.01774  -0.0187   0.4636   0.0541
  -1.250   0.2267   0.02298   0.01682  -0.0184   0.4616   0.0553
  -1.000   0.2521   0.02145   0.01492  -0.0174   0.4592   0.0605
  -0.750   0.2787   0.01701   0.00949  -0.0149   0.4570   0.0416
  -0.500   0.3068   0.01624   0.00868  -0.0148   0.4543   0.0423
  -0.250   0.3352   0.01577   0.00819  -0.0147   0.4517   0.0431
   0.000   0.3638   0.01524   0.00755  -0.0144   0.4490   0.0434
   0.250   0.3923   0.01487   0.00705  -0.0143   0.4458   0.0437
   0.500   0.4213   0.01445   0.00663  -0.0142   0.4435   0.0443
   0.750   0.4501   0.01409   0.00626  -0.0141   0.4406   0.0451
   1.000   0.4788   0.01381   0.00594  -0.0140   0.4375   0.0459
   1.250   0.5073   0.01356   0.00566  -0.0138   0.4345   0.0467
   1.500   0.5347   0.01319   0.00531  -0.0136   0.4317   0.0485
   1.750   0.5622   0.01311   0.00520  -0.0134   0.4284   0.0505
   2.000   0.5903   0.01294   0.00508  -0.0133   0.4256   0.0522
   2.250   0.6173   0.01268   0.00488  -0.0129   0.4224   0.0544
   2.500   0.6448   0.01254   0.00476  -0.0127   0.4191   0.0572
   2.750   0.6720   0.01242   0.00463  -0.0125   0.4160   0.0612
   3.000   0.6990   0.01240   0.00458  -0.0122   0.4126   0.0681
   3.250   0.7256   0.01227   0.00460  -0.0119   0.4098   0.0957
   3.500   0.7510   0.01205   0.00475  -0.0114   0.4065   0.2255
   3.750   0.7772   0.01194   0.00481  -0.0112   0.4031   0.2837
   4.000   0.8692   0.01082   0.00523  -0.0243   0.3977   0.9793
   4.250   0.9818   0.01095   0.00528  -0.0417   0.3919   1.0000
   4.500   1.0084   0.01104   0.00535  -0.0415   0.3883   1.0000
   4.750   1.0349   0.01116   0.00542  -0.0414   0.3847   1.0000
   5.000   1.0610   0.01132   0.00551  -0.0412   0.3810   1.0000
   5.250   1.0872   0.01148   0.00566  -0.0410   0.3775   1.0000
   5.500   1.1135   0.01161   0.00580  -0.0408   0.3736   1.0000
   5.750   1.1394   0.01175   0.00593  -0.0406   0.3695   1.0000
   6.000   1.1649   0.01196   0.00607  -0.0404   0.3656   1.0000
   6.250   1.1904   0.01218   0.00628  -0.0402   0.3619   1.0000
   6.500   1.2160   0.01235   0.00648  -0.0400   0.3581   1.0000
   6.750   1.2412   0.01255   0.00668  -0.0398   0.3542   1.0000
   7.000   1.2659   0.01281   0.00688  -0.0396   0.3503   1.0000
   7.250   1.2901   0.01309   0.00716  -0.0393   0.3465   1.0000
   7.500   1.3148   0.01331   0.00742  -0.0390   0.3427   1.0000
   7.750   1.3389   0.01357   0.00768  -0.0388   0.3386   1.0000
   8.000   1.3620   0.01390   0.00797  -0.0384   0.3345   1.0000
   8.250   1.3848   0.01425   0.00832  -0.0380   0.3306   1.0000
   8.500   1.4079   0.01454   0.00866  -0.0376   0.3269   1.0000
   8.750   1.4300   0.01488   0.00901  -0.0372   0.3230   1.0000
   9.000   1.4508   0.01529   0.00940  -0.0366   0.3193   1.0000
   9.250   1.4706   0.01576   0.00986  -0.0358   0.3156   1.0000
   9.500   1.4909   0.01615   0.01031  -0.0352   0.3124   1.0000
   9.750   1.5097   0.01659   0.01079  -0.0345   0.3088   1.0000
  10.000   1.5262   0.01714   0.01134  -0.0335   0.3053   1.0000
  10.250   1.5397   0.01782   0.01198  -0.0321   0.3016   1.0000
  10.500   1.5527   0.01851   0.01274  -0.0310   0.2985   1.0000
  10.750   1.5577   0.01948   0.01378  -0.0292   0.2955   1.0000
  11.000   1.5554   0.02056   0.01490  -0.0263   0.2926   1.0000
  11.250   1.5580   0.02169   0.01603  -0.0244   0.2897   1.0000
  11.500   1.5633   0.02278   0.01708  -0.0227   0.2865   1.0000
  11.750   1.5697   0.02394   0.01831  -0.0214   0.2839   1.0000
  12.000   1.5753   0.02524   0.01968  -0.0204   0.2812   1.0000
  12.250   1.5813   0.02656   0.02105  -0.0194   0.2784   1.0000
  12.500   1.5871   0.02792   0.02242  -0.0185   0.2754   1.0000
  12.750   1.5943   0.02915   0.02363  -0.0175   0.2725   1.0000
  13.000   1.6034   0.03027   0.02476  -0.0166   0.2698   1.0000
  13.250   1.6066   0.03202   0.02660  -0.0161   0.2674   1.0000
  13.500   1.6106   0.03370   0.02836  -0.0155   0.2647   1.0000
  13.750   1.6131   0.03553   0.03022  -0.0150   0.2613   1.0000
  14.000   1.6180   0.03709   0.03175  -0.0144   0.2578   1.0000
  14.250   1.6252   0.03848   0.03315  -0.0138   0.2547   1.0000
  14.500   1.6245   0.04085   0.03563  -0.0137   0.2520   1.0000
  14.750   1.6247   0.04318   0.03803  -0.0136   0.2487   1.0000
  15.000   1.6298   0.04498   0.03987  -0.0134   0.2461   1.0000
  15.250   1.6360   0.04662   0.04147  -0.0131   0.2428   1.0000
  15.500   1.6406   0.04850   0.04339  -0.0130   0.2399   1.0000
  15.750   1.6407   0.05099   0.04599  -0.0131   0.2375   1.0000
  16.000   1.6394   0.05368   0.04876  -0.0132   0.2343   1.0000
  16.250   1.6424   0.05586   0.05097  -0.0133   0.2316   1.0000
  16.500   1.6486   0.05759   0.05271  -0.0132   0.2289   1.0000
  16.750   1.6579   0.05895   0.05406  -0.0131   0.2262   1.0000
  17.000   1.6538   0.06209   0.05734  -0.0135   0.2239   1.0000
  17.250   1.6497   0.06526   0.06060  -0.0139   0.2209   1.0000
  17.500   1.6491   0.06797   0.06336  -0.0143   0.2178   1.0000
  17.750   1.6531   0.07006   0.06545  -0.0144   0.2150   1.0000
  18.000   1.6574   0.07214   0.06754  -0.0146   0.2118   1.0000
  18.250   1.6491   0.07595   0.07149  -0.0153   0.2091   1.0000
  18.500   1.6445   0.07928   0.07491  -0.0159   0.2061   1.0000
  18.750   1.6429   0.08223   0.07789  -0.0165   0.2029   1.0000
  19.000   1.6492   0.08405   0.07965  -0.0167   0.1989   1.0000
  19.250   1.6388   0.08827   0.08403  -0.0176   0.1964   1.0000
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