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GOE 425 AIRFOIL (goe425-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 425 AIRFOIL (goe425-il)
Reynolds number: 1,000,000
Max Cl/Cd: 142.09 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe425-il-1000000.txt
Download as CSV file: xf-goe425-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 425 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.2557   0.08221   0.07950  -0.0566   0.6912   0.0290
 -10.750  -0.2537   0.07881   0.07609  -0.0576   0.6865   0.0292
 -10.500  -0.2516   0.07542   0.07270  -0.0587   0.6814   0.0293
 -10.250  -0.5258   0.04317   0.03980  -0.0889   0.7036   0.0292
 -10.000  -0.5103   0.04189   0.03849  -0.0890   0.6973   0.0294
  -9.750  -0.5199   0.03630   0.03246  -0.0892   0.6921   0.0278
  -9.500  -0.5159   0.03244   0.02833  -0.0890   0.6873   0.0273
  -9.250  -0.5080   0.02893   0.02447  -0.0884   0.6817   0.0271
  -9.000  -0.4934   0.02649   0.02171  -0.0877   0.6758   0.0272
  -8.750  -0.4751   0.02457   0.01953  -0.0871   0.6703   0.0273
  -8.500  -0.4539   0.02323   0.01797  -0.0866   0.6642   0.0277
  -8.250  -0.4316   0.02208   0.01660  -0.0862   0.6580   0.0279
  -8.000  -0.4085   0.02089   0.01524  -0.0858   0.6524   0.0281
  -7.750  -0.3843   0.01993   0.01412  -0.0854   0.6461   0.0282
  -7.500  -0.3595   0.01919   0.01321  -0.0851   0.6395   0.0283
  -7.250  -0.3335   0.01874   0.01264  -0.0848   0.6335   0.0285
  -7.000  -0.3094   0.01738   0.01111  -0.0845   0.6267   0.0287
  -6.750  -0.2848   0.01605   0.00968  -0.0842   0.6200   0.0290
  -6.500  -0.2588   0.01525   0.00884  -0.0840   0.6130   0.0293
  -6.250  -0.2325   0.01478   0.00831  -0.0838   0.6058   0.0297
  -6.000  -0.2055   0.01439   0.00789  -0.0837   0.5994   0.0301
  -5.750  -0.1787   0.01398   0.00744  -0.0836   0.5927   0.0305
  -5.500  -0.1520   0.01356   0.00696  -0.0834   0.5864   0.0308
  -5.250  -0.1250   0.01314   0.00650  -0.0832   0.5807   0.0311
  -5.000  -0.0981   0.01276   0.00607  -0.0830   0.5747   0.0313
  -4.750  -0.0713   0.01242   0.00568  -0.0828   0.5692   0.0316
  -4.500  -0.0441   0.01208   0.00531  -0.0827   0.5643   0.0320
  -4.250  -0.0170   0.01178   0.00497  -0.0825   0.5594   0.0323
  -4.000   0.0100   0.01155   0.00468  -0.0823   0.5546   0.0326
  -3.750   0.0376   0.01131   0.00443  -0.0822   0.5509   0.0329
  -3.500   0.0655   0.01113   0.00422  -0.0822   0.5468   0.0332
  -3.250   0.0912   0.01063   0.00369  -0.0818   0.5428   0.0340
  -3.000   0.1182   0.01042   0.00345  -0.0817   0.5388   0.0347
  -2.750   0.1459   0.01024   0.00326  -0.0816   0.5355   0.0353
  -2.500   0.1740   0.01007   0.00308  -0.0816   0.5325   0.0360
  -2.250   0.2021   0.00993   0.00292  -0.0816   0.5292   0.0367
  -2.000   0.2300   0.00982   0.00278  -0.0816   0.5258   0.0374
  -1.750   0.2580   0.00974   0.00267  -0.0816   0.5224   0.0381
  -1.500   0.2859   0.00964   0.00253  -0.0815   0.5191   0.0390
  -1.250   0.3141   0.00948   0.00238  -0.0816   0.5166   0.0407
  -1.000   0.3426   0.00938   0.00229  -0.0817   0.5139   0.0425
  -0.750   0.3710   0.00933   0.00223  -0.0817   0.5108   0.0444
  -0.500   0.3991   0.00925   0.00214  -0.0817   0.5078   0.0494
  -0.250   0.4261   0.00907   0.00210  -0.0816   0.5043   0.1058
   0.000   0.4544   0.00898   0.00208  -0.0817   0.5019   0.1281
   0.250   0.4802   0.00843   0.00201  -0.0816   0.4997   0.2857
   0.500   0.5060   0.00798   0.00202  -0.0815   0.4972   0.4383
   0.750   0.5339   0.00790   0.00207  -0.0815   0.4947   0.4885
   1.000   0.5619   0.00788   0.00211  -0.0816   0.4921   0.5202
   1.250   0.5897   0.00789   0.00217  -0.0816   0.4891   0.5463
   1.500   0.6176   0.00793   0.00224  -0.0816   0.4860   0.5685
   1.750   0.6460   0.00788   0.00228  -0.0817   0.4841   0.5961
   2.000   0.6739   0.00783   0.00234  -0.0818   0.4819   0.6284
   2.250   0.7013   0.00774   0.00240  -0.0817   0.4795   0.6743
   2.500   0.7277   0.00763   0.00246  -0.0814   0.4770   0.7305
   2.750   0.7501   0.00735   0.00255  -0.0802   0.4743   0.8540
   3.000   0.8051   0.00736   0.00273  -0.0859   0.4698   0.9841
   3.250   0.8495   0.00740   0.00278  -0.0896   0.4670   0.9975
   3.500   0.8832   0.00746   0.00283  -0.0910   0.4640   1.0000
   3.750   0.9095   0.00753   0.00288  -0.0907   0.4608   1.0000
   4.000   0.9353   0.00762   0.00295  -0.0903   0.4576   1.0000
   4.250   0.9607   0.00776   0.00305  -0.0899   0.4542   1.0000
   4.500   0.9871   0.00783   0.00313  -0.0896   0.4517   1.0000
   4.750   1.0136   0.00789   0.00320  -0.0894   0.4485   1.0000
   5.000   1.0397   0.00796   0.00328  -0.0891   0.4447   1.0000
   5.250   1.0652   0.00808   0.00337  -0.0887   0.4404   1.0000
   5.500   1.0908   0.00820   0.00348  -0.0884   0.4362   1.0000
   5.750   1.1175   0.00826   0.00356  -0.0882   0.4323   1.0000
   6.000   1.1435   0.00836   0.00366  -0.0880   0.4274   1.0000
   6.250   1.1687   0.00851   0.00379  -0.0876   0.4228   1.0000
   6.500   1.1951   0.00861   0.00390  -0.0874   0.4186   1.0000
   6.750   1.2213   0.00871   0.00402  -0.0872   0.4138   1.0000
   7.000   1.2466   0.00887   0.00416  -0.0869   0.4083   1.0000
   7.250   1.2724   0.00900   0.00430  -0.0867   0.4024   1.0000
   7.500   1.2980   0.00915   0.00445  -0.0864   0.3959   1.0000
   7.750   1.3226   0.00935   0.00463  -0.0860   0.3899   1.0000
   8.000   1.3484   0.00949   0.00479  -0.0858   0.3829   1.0000
   8.250   1.3721   0.00973   0.00500  -0.0853   0.3752   1.0000
   8.500   1.3972   0.00991   0.00519  -0.0850   0.3673   1.0000
   8.750   1.4201   0.01020   0.00545  -0.0844   0.3562   1.0000
   9.000   1.4419   0.01054   0.00574  -0.0836   0.3436   1.0000
   9.250   1.4639   0.01087   0.00603  -0.0829   0.3313   1.0000
   9.500   1.4852   0.01123   0.00637  -0.0820   0.3185   1.0000
   9.750   1.5050   0.01166   0.00674  -0.0810   0.3045   1.0000
  10.000   1.5228   0.01217   0.00719  -0.0796   0.2880   1.0000
  10.250   1.5367   0.01285   0.00776  -0.0777   0.2666   1.0000
  10.500   1.5415   0.01379   0.00854  -0.0743   0.2356   1.0000
  10.750   1.5346   0.01535   0.00985  -0.0696   0.1938   1.0000
  11.000   1.5319   0.01688   0.01124  -0.0660   0.1693   1.0000
  11.250   1.5370   0.01815   0.01247  -0.0638   0.1571   1.0000
  11.500   1.5449   0.01938   0.01370  -0.0622   0.1483   1.0000
  11.750   1.5501   0.02090   0.01521  -0.0606   0.1394   1.0000
  12.000   1.5588   0.02230   0.01662  -0.0595   0.1314   1.0000
  12.250   1.5635   0.02411   0.01842  -0.0584   0.1225   1.0000
  12.500   1.5656   0.02623   0.02052  -0.0573   0.1121   1.0000
  12.750   1.5667   0.02850   0.02277  -0.0563   0.1019   1.0000
  13.000   1.5668   0.03090   0.02516  -0.0554   0.0937   1.0000
  13.250   1.5659   0.03340   0.02768  -0.0544   0.0877   1.0000
  13.500   1.5668   0.03576   0.03007  -0.0536   0.0837   1.0000
  13.750   1.5648   0.03841   0.03274  -0.0527   0.0798   1.0000
  14.000   1.5657   0.04079   0.03517  -0.0520   0.0769   1.0000
  14.250   1.5662   0.04328   0.03770  -0.0513   0.0741   1.0000
  14.500   1.5640   0.04610   0.04056  -0.0507   0.0712   1.0000
  14.750   1.5622   0.04892   0.04343  -0.0502   0.0681   1.0000
  15.000   1.5640   0.05144   0.04600  -0.0498   0.0655   1.0000
  15.250   1.5614   0.05448   0.04907  -0.0494   0.0621   1.0000
  15.500   1.5593   0.05747   0.05209  -0.0491   0.0586   1.0000
  15.750   1.5576   0.06044   0.05509  -0.0488   0.0542   1.0000
  16.000   1.5529   0.06382   0.05848  -0.0486   0.0492   1.0000
  16.250   1.5449   0.06761   0.06226  -0.0484   0.0425   1.0000
  16.500   1.5335   0.07178   0.06641  -0.0483   0.0345   1.0000
  16.750   1.5219   0.07607   0.07068  -0.0483   0.0276   1.0000
  17.000   1.5124   0.08022   0.07483  -0.0484   0.0234   1.0000
  17.250   1.5054   0.08405   0.07869  -0.0485   0.0208   1.0000
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