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GOE 601 AIRFOIL (goe601-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 601 AIRFOIL (goe601-il)
Reynolds number: 100,000
Max Cl/Cd: 44.11 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe601-il-100000-n5.txt
Download as CSV file: xf-goe601-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 601 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.750  -0.6366   0.08901   0.08290  -0.0747   1.0000   0.0492
 -14.500  -0.6874   0.07796   0.07165  -0.0811   1.0000   0.0489
 -14.250  -0.7237   0.07042   0.06390  -0.0848   1.0000   0.0488
 -14.000  -0.7544   0.06446   0.05774  -0.0872   1.0000   0.0489
 -13.750  -0.7793   0.05976   0.05283  -0.0882   1.0000   0.0490
 -13.500  -0.8008   0.05594   0.04880  -0.0881   1.0000   0.0492
 -13.250  -0.8093   0.05348   0.04629  -0.0871   1.0000   0.0497
 -13.000  -0.8163   0.05141   0.04417  -0.0856   1.0000   0.0502
 -12.750  -0.8255   0.04940   0.04210  -0.0837   1.0000   0.0506
 -12.500  -0.8357   0.04758   0.04020  -0.0812   1.0000   0.0510
 -12.250  -0.8468   0.04596   0.03850  -0.0781   1.0000   0.0514
 -12.000  -0.8592   0.04460   0.03706  -0.0743   1.0000   0.0519
 -11.750  -0.8734   0.04346   0.03585  -0.0698   1.0000   0.0524
 -11.500  -0.8902   0.04256   0.03487  -0.0643   1.0000   0.0528
 -11.250  -0.8883   0.04121   0.03337  -0.0623   0.9967   0.0539
 -11.000  -0.8694   0.03937   0.03125  -0.0632   0.9908   0.0554
 -10.750  -0.8478   0.03767   0.02933  -0.0641   0.9852   0.0569
 -10.500  -0.8238   0.03640   0.02805  -0.0651   0.9801   0.0582
 -10.250  -0.8011   0.03521   0.02678  -0.0657   0.9740   0.0597
 -10.000  -0.7756   0.03402   0.02546  -0.0668   0.9694   0.0620
  -9.750  -0.7557   0.03289   0.02414  -0.0664   0.9624   0.0641
  -9.500  -0.7294   0.03183   0.02307  -0.0674   0.9579   0.0662
  -9.250  -0.7108   0.03097   0.02218  -0.0668   0.9507   0.0683
  -9.000  -0.6863   0.03004   0.02115  -0.0671   0.9454   0.0711
  -8.750  -0.6581   0.02911   0.02015  -0.0682   0.9419   0.0749
  -8.500  -0.6449   0.02851   0.01953  -0.0662   0.9331   0.0780
  -8.250  -0.6180   0.02774   0.01864  -0.0667   0.9288   0.0838
  -8.000  -0.6005   0.02711   0.01800  -0.0655   0.9221   0.0890
  -7.750  -0.5797   0.02644   0.01723  -0.0648   0.9162   0.0961
  -7.500  -0.5522   0.02571   0.01643  -0.0654   0.9126   0.1053
  -7.250  -0.5389   0.02514   0.01583  -0.0632   0.9050   0.1126
  -7.000  -0.5150   0.02458   0.01516  -0.0629   0.9001   0.1224
  -6.750  -0.4883   0.02380   0.01440  -0.0634   0.8969   0.1324
  -6.500  -0.4747   0.02338   0.01396  -0.0611   0.8894   0.1400
  -6.250  -0.4511   0.02283   0.01339  -0.0607   0.8848   0.1501
  -6.000  -0.4228   0.02221   0.01282  -0.0613   0.8818   0.1643
  -5.500  -0.3865   0.02127   0.01216  -0.0585   0.8701   0.2136
  -5.250  -0.3591   0.02072   0.01178  -0.0588   0.8669   0.2557
  -5.000  -0.3304   0.02027   0.01141  -0.0592   0.8639   0.2939
  -4.750  -0.3188   0.02012   0.01131  -0.0563   0.8560   0.3185
  -4.500  -0.2911   0.01978   0.01104  -0.0563   0.8524   0.3471
  -4.250  -0.2601   0.01948   0.01080  -0.0569   0.8498   0.3745
  -4.000  -0.2430   0.01944   0.01079  -0.0550   0.8433   0.3966
  -3.750  -0.2190   0.01935   0.01071  -0.0542   0.8384   0.4207
  -3.500  -0.1888   0.01921   0.01055  -0.0546   0.8352   0.4464
  -3.250  -0.1556   0.01904   0.01034  -0.0555   0.8328   0.4718
  -3.000  -0.1424   0.01916   0.01046  -0.0528   0.8252   0.4893
  -2.750  -0.1156   0.01909   0.01035  -0.0525   0.8209   0.5067
  -2.500  -0.0835   0.01893   0.01017  -0.0532   0.8179   0.5240
  -2.250  -0.0489   0.01873   0.00997  -0.0543   0.8156   0.5422
  -2.000  -0.0387   0.01893   0.01021  -0.0510   0.8073   0.5560
  -1.750  -0.0108   0.01885   0.01015  -0.0509   0.8032   0.5724
  -1.500   0.0222   0.01870   0.01003  -0.0517   0.8003   0.5903
  -1.250   0.0575   0.01853   0.00989  -0.0529   0.7980   0.6098
  -1.000   0.0646   0.01880   0.01023  -0.0490   0.7885   0.6250
  -0.750   0.0977   0.01862   0.01007  -0.0497   0.7841   0.6448
  -0.500   0.1383   0.01829   0.00975  -0.0516   0.7806   0.6654
  -0.250   0.1486   0.01846   0.01000  -0.0482   0.7705   0.6824
   0.000   0.1856   0.01818   0.00975  -0.0495   0.7654   0.7030
   0.250   0.2116   0.01813   0.00975  -0.0489   0.7585   0.7225
   0.500   0.2378   0.01806   0.00975  -0.0483   0.7508   0.7427
   0.750   0.2792   0.01777   0.00950  -0.0503   0.7461   0.7651
   1.000   0.2970   0.01788   0.00971  -0.0482   0.7363   0.7907
   1.250   0.3388   0.01765   0.00955  -0.0502   0.7299   0.8202
   1.500   0.3687   0.01769   0.00969  -0.0502   0.7201   0.8511
   1.750   0.4158   0.01756   0.00958  -0.0534   0.7128   0.8754
   2.000   0.4515   0.01767   0.00974  -0.0549   0.7035   0.8974
   2.250   0.4964   0.01759   0.00965  -0.0580   0.6957   0.9138
   2.500   0.5328   0.01769   0.00979  -0.0597   0.6850   0.9316
   2.750   0.5779   0.01759   0.00967  -0.0629   0.6756   0.9451
   3.000   0.6155   0.01764   0.00974  -0.0649   0.6632   0.9599
   3.250   0.6537   0.01767   0.00979  -0.0671   0.6494   0.9738
   3.500   0.6938   0.01766   0.00978  -0.0696   0.6344   0.9863
   3.750   0.7358   0.01764   0.00975  -0.0726   0.6169   0.9980
   4.000   0.7521   0.01765   0.00971  -0.0705   0.5996   1.0000
   4.250   0.7626   0.01767   0.00966  -0.0672   0.5808   1.0000
   4.500   0.7747   0.01771   0.00961  -0.0641   0.5603   1.0000
   4.750   0.7839   0.01785   0.00967  -0.0605   0.5372   1.0000
   5.000   0.7948   0.01802   0.00969  -0.0572   0.5116   1.0000
   5.250   0.8037   0.01827   0.00979  -0.0536   0.4840   1.0000
   5.500   0.8111   0.01858   0.00992  -0.0497   0.4578   1.0000
   5.750   0.8174   0.01894   0.01014  -0.0457   0.4339   1.0000
   6.000   0.8251   0.01934   0.01039  -0.0420   0.4139   1.0000
   6.250   0.8346   0.01977   0.01070  -0.0388   0.3969   1.0000
   6.500   0.8462   0.02023   0.01104  -0.0360   0.3828   1.0000
   6.750   0.8597   0.02069   0.01143  -0.0336   0.3709   1.0000
   7.000   0.8743   0.02119   0.01182  -0.0315   0.3601   1.0000
   7.250   0.8897   0.02167   0.01227  -0.0295   0.3498   1.0000
   7.500   0.9057   0.02219   0.01270  -0.0277   0.3403   1.0000
   7.750   0.9200   0.02271   0.01323  -0.0256   0.3297   1.0000
   8.000   0.9356   0.02326   0.01372  -0.0238   0.3204   1.0000
   8.250   0.9495   0.02381   0.01426  -0.0218   0.3105   1.0000
   8.500   0.9653   0.02436   0.01482  -0.0201   0.3022   1.0000
   8.750   0.9801   0.02491   0.01541  -0.0183   0.2941   1.0000
   9.000   0.9955   0.02549   0.01598  -0.0167   0.2866   1.0000
   9.250   1.0084   0.02607   0.01665  -0.0147   0.2782   1.0000
   9.500   1.0230   0.02669   0.01725  -0.0131   0.2713   1.0000
   9.750   1.0356   0.02730   0.01801  -0.0112   0.2635   1.0000
  10.000   1.0467   0.02799   0.01869  -0.0092   0.2557   1.0000
  10.250   1.0556   0.02871   0.01955  -0.0070   0.2456   1.0000
  10.500   1.0625   0.02955   0.02042  -0.0047   0.2349   1.0000
  10.750   1.0685   0.03048   0.02140  -0.0025   0.2231   1.0000
  11.000   1.0757   0.03144   0.02245  -0.0006   0.2102   1.0000
  11.250   1.0814   0.03255   0.02360   0.0013   0.1950   1.0000
  11.500   1.0859   0.03381   0.02488   0.0032   0.1776   1.0000
  11.750   1.0890   0.03529   0.02632   0.0051   0.1526   1.0000
  12.000   1.0858   0.03731   0.02817   0.0071   0.1193   1.0000
  12.250   1.0773   0.03994   0.03053   0.0092   0.0902   1.0000
  12.500   1.0719   0.04250   0.03298   0.0109   0.0777   1.0000
  12.750   1.0689   0.04495   0.03545   0.0122   0.0709   1.0000
  13.000   1.0639   0.04769   0.03821   0.0134   0.0663   1.0000
  13.250   1.0616   0.05028   0.04091   0.0143   0.0630   1.0000
  13.500   1.0567   0.05324   0.04396   0.0150   0.0605   1.0000
  13.750   1.0502   0.05651   0.04731   0.0154   0.0587   1.0000
  14.000   1.0438   0.05993   0.05083   0.0156   0.0572   1.0000
  14.250   1.0387   0.06335   0.05440   0.0155   0.0559   1.0000
  14.500   1.0324   0.06706   0.05825   0.0152   0.0547   1.0000
  14.750   1.0262   0.07090   0.06221   0.0147   0.0538   1.0000
  15.000   1.0194   0.07493   0.06634   0.0139   0.0529   1.0000
  15.250   1.0137   0.07891   0.07041   0.0131   0.0521   1.0000
  15.500   1.0087   0.08282   0.07440   0.0122   0.0512   1.0000
  15.750   1.0056   0.08642   0.07803   0.0115   0.0504   1.0000
  16.000   1.0068   0.08951   0.08123   0.0109   0.0495   1.0000
  16.250   1.0091   0.09240   0.08421   0.0104   0.0484   1.0000
  16.500   1.0117   0.09527   0.08718   0.0099   0.0473   1.0000
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