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GOE 744 AIRFOIL (goe744-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 744 AIRFOIL (goe744-il)
Reynolds number: 1,000,000
Max Cl/Cd: 128.37 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe744-il-1000000.txt
Download as CSV file: xf-goe744-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.1903   0.09904   0.09596   0.0106   0.4917   0.0244
  -8.750  -0.1925   0.09463   0.09155   0.0080   0.4906   0.0245
  -8.500  -0.1909   0.09053   0.08745   0.0060   0.4891   0.0245
  -8.250  -0.1849   0.08659   0.08350   0.0053   0.4873   0.0247
  -8.000  -0.1733   0.08390   0.08080   0.0050   0.4849   0.0248
  -7.750  -0.1655   0.08107   0.07795   0.0042   0.4824   0.0249
  -7.500  -0.1585   0.07822   0.07511   0.0033   0.4812   0.0250
  -7.250  -0.1525   0.07539   0.07229   0.0024   0.4801   0.0252
  -7.000  -0.1489   0.07236   0.06928   0.0013   0.4789   0.0253
  -6.750  -0.1463   0.06947   0.06640   0.0003   0.4774   0.0256
  -6.500  -0.1481   0.06655   0.06351  -0.0008   0.4760   0.0258
  -6.250  -0.1515   0.06365   0.06062  -0.0015   0.4746   0.0260
  -6.000  -0.1469   0.06029   0.05725  -0.0032   0.4731   0.0264
  -5.750  -0.1406   0.05669   0.05363  -0.0051   0.4716   0.0269
  -5.500  -0.1393   0.04874   0.04557  -0.0117   0.4709   0.0281
  -5.000  -0.1198   0.05065   0.04708  -0.0185   0.4702   0.0284
  -4.750  -0.1006   0.04879   0.04516  -0.0188   0.4679   0.0286
  -4.500  -0.0803   0.04704   0.04335  -0.0192   0.4649   0.0288
  -4.250  -0.0593   0.04506   0.04131  -0.0196   0.4630   0.0290
  -4.000  -0.0375   0.04303   0.03923  -0.0199   0.4616   0.0294
  -3.750  -0.0237   0.03078   0.02642  -0.0207   0.4611   0.0324
  -3.500  -0.0003   0.02983   0.02545  -0.0204   0.4592   0.0326
  -3.250   0.0233   0.02860   0.02415  -0.0201   0.4571   0.0328
  -3.000   0.0473   0.02741   0.02289  -0.0197   0.4549   0.0331
  -2.750   0.0598   0.02039   0.01508  -0.0167   0.4534   0.0315
  -2.500   0.0809   0.01767   0.01198  -0.0153   0.4513   0.0305
  -2.250   0.1048   0.01554   0.00943  -0.0141   0.4488   0.0302
  -2.000   0.1316   0.01459   0.00827  -0.0136   0.4458   0.0304
  -1.750   0.1594   0.01382   0.00737  -0.0132   0.4442   0.0306
  -1.500   0.1876   0.01318   0.00663  -0.0129   0.4420   0.0309
  -1.250   0.2161   0.01266   0.00603  -0.0127   0.4397   0.0312
  -1.000   0.2447   0.01225   0.00554  -0.0125   0.4372   0.0315
  -0.750   0.2735   0.01195   0.00516  -0.0123   0.4344   0.0318
  -0.500   0.3020   0.01166   0.00480  -0.0122   0.4312   0.0323
  -0.250   0.3301   0.01125   0.00439  -0.0120   0.4283   0.0331
   0.000   0.3588   0.01105   0.00421  -0.0120   0.4263   0.0337
   0.250   0.3875   0.01085   0.00402  -0.0118   0.4236   0.0343
   0.500   0.4161   0.01068   0.00384  -0.0117   0.4207   0.0350
   0.750   0.4446   0.01053   0.00367  -0.0116   0.4175   0.0357
   1.000   0.4730   0.01046   0.00355  -0.0115   0.4139   0.0363
   1.250   0.5007   0.01024   0.00334  -0.0113   0.4111   0.0372
   1.500   0.5291   0.01010   0.00324  -0.0112   0.4084   0.0382
   1.750   0.5575   0.01002   0.00317  -0.0111   0.4053   0.0394
   2.000   0.5860   0.00998   0.00312  -0.0111   0.4020   0.0409
   2.250   0.6137   0.00990   0.00303  -0.0109   0.3986   0.0427
   2.500   0.6418   0.00990   0.00302  -0.0108   0.3951   0.0447
   2.750   0.6702   0.00985   0.00300  -0.0108   0.3923   0.0469
   3.000   0.6980   0.00978   0.00295  -0.0106   0.3888   0.0506
   3.250   0.7259   0.00976   0.00293  -0.0106   0.3851   0.0554
   3.500   0.7533   0.00977   0.00295  -0.0104   0.3812   0.0657
   3.750   0.7788   0.00958   0.00308  -0.0100   0.3782   0.1902
   4.000   0.8066   0.00957   0.00315  -0.0100   0.3752   0.2224
   4.250   0.8342   0.00958   0.00322  -0.0099   0.3716   0.2506
   4.500   0.8594   0.00948   0.00336  -0.0096   0.3677   0.3694
   4.750   0.9243   0.00848   0.00378  -0.0175   0.3625   0.9755
   5.000   0.9805   0.00873   0.00400  -0.0233   0.3581   0.9848
   5.250   1.0412   0.00900   0.00421  -0.0301   0.3529   0.9925
   5.500   1.1051   0.00914   0.00428  -0.0378   0.3473   0.9973
   5.750   1.1439   0.00920   0.00434  -0.0402   0.3439   0.9992
   6.000   1.1776   0.00931   0.00443  -0.0416   0.3399   1.0000
   6.250   1.2039   0.00949   0.00458  -0.0415   0.3357   1.0000
   6.500   1.2300   0.00970   0.00476  -0.0415   0.3314   1.0000
   6.750   1.2563   0.00982   0.00489  -0.0413   0.3282   1.0000
   7.000   1.2824   0.00999   0.00505  -0.0412   0.3241   1.0000
   7.250   1.3079   0.01023   0.00526  -0.0412   0.3196   1.0000
   7.500   1.3333   0.01047   0.00548  -0.0410   0.3156   1.0000
   7.750   1.3590   0.01063   0.00566  -0.0409   0.3124   1.0000
   8.000   1.3842   0.01084   0.00588  -0.0408   0.3086   1.0000
   8.250   1.4088   0.01113   0.00614  -0.0406   0.3045   1.0000
   8.500   1.4329   0.01145   0.00645  -0.0404   0.3004   1.0000
   8.750   1.4577   0.01164   0.00667  -0.0402   0.2975   1.0000
   9.000   1.4818   0.01191   0.00694  -0.0400   0.2939   1.0000
   9.250   1.5048   0.01226   0.00728  -0.0397   0.2899   1.0000
   9.500   1.5265   0.01270   0.00771  -0.0393   0.2854   1.0000
   9.750   1.5499   0.01294   0.00798  -0.0390   0.2828   1.0000
  10.000   1.5720   0.01326   0.00833  -0.0386   0.2796   1.0000
  10.250   1.5926   0.01369   0.00876  -0.0381   0.2762   1.0000
  10.500   1.6107   0.01426   0.00932  -0.0374   0.2724   1.0000
  10.750   1.6289   0.01476   0.00985  -0.0366   0.2695   1.0000
  11.000   1.6474   0.01519   0.01032  -0.0359   0.2672   1.0000
  11.250   1.6626   0.01583   0.01100  -0.0350   0.2639   1.0000
  11.500   1.6689   0.01715   0.01235  -0.0341   0.2605   1.0000
  11.750   1.6491   0.01908   0.01430  -0.0297   0.2572   1.0000
  12.000   1.6502   0.02041   0.01567  -0.0277   0.2544   1.0000
  12.250   1.6565   0.02157   0.01688  -0.0264   0.2515   1.0000
  12.500   1.6591   0.02307   0.01841  -0.0251   0.2487   1.0000
  12.750   1.6581   0.02493   0.02028  -0.0238   0.2456   1.0000
  13.000   1.6524   0.02720   0.02257  -0.0224   0.2420   1.0000
  13.250   1.6573   0.02876   0.02418  -0.0216   0.2394   1.0000
  13.500   1.6626   0.03030   0.02577  -0.0209   0.2372   1.0000
  13.750   1.6646   0.03214   0.02764  -0.0201   0.2342   1.0000
  14.000   1.6632   0.03431   0.02985  -0.0194   0.2317   1.0000
  14.250   1.6560   0.03705   0.03259  -0.0187   0.2281   1.0000
  14.500   1.6595   0.03891   0.03449  -0.0182   0.2259   1.0000
  14.750   1.6652   0.04067   0.03632  -0.0179   0.2241   1.0000
  15.000   1.6702   0.04248   0.03817  -0.0177   0.2216   1.0000
  15.250   1.6705   0.04481   0.04054  -0.0174   0.2190   1.0000
  15.500   1.6696   0.04724   0.04299  -0.0172   0.2161   1.0000
  15.750   1.6651   0.05007   0.04583  -0.0170   0.2129   1.0000
  16.000   1.6717   0.05185   0.04768  -0.0170   0.2111   1.0000
  16.250   1.6769   0.05380   0.04968  -0.0170   0.2087   1.0000
  16.500   1.6775   0.05624   0.05216  -0.0170   0.2058   1.0000
  16.750   1.6772   0.05877   0.05471  -0.0170   0.2029   1.0000
  17.000   1.6701   0.06207   0.05802  -0.0172   0.1993   1.0000
  17.250   1.6759   0.06400   0.06002  -0.0173   0.1972   1.0000
  17.500   1.6805   0.06609   0.06217  -0.0174   0.1947   1.0000
  17.750   1.6779   0.06904   0.06515  -0.0177   0.1914   1.0000
  18.000   1.6755   0.07192   0.06805  -0.0180   0.1882   1.0000
  18.250   1.6699   0.07524   0.07141  -0.0184   0.1849   1.0000
  18.500   1.6738   0.07749   0.07372  -0.0187   0.1821   1.0000
  18.750   1.6726   0.08033   0.07659  -0.0191   0.1782   1.0000
  19.000   1.6613   0.08444   0.08072  -0.0198   0.1739   1.0000
  19.250   1.6616   0.08713   0.08346  -0.0203   0.1709   1.0000
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