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GOE 622 AIRFOIL (goe622-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 622 AIRFOIL (goe622-il)
Reynolds number: 1,000,000
Max Cl/Cd: 98.63 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe622-il-1000000.txt
Download as CSV file: xf-goe622-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 622 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.4073   0.10737   0.10581  -0.0134   1.0000   0.0110
 -10.500  -0.4078   0.10300   0.10145  -0.0145   1.0000   0.0110
 -10.250  -0.4214   0.09604   0.09451  -0.0160   1.0000   0.0115
 -10.000  -0.4215   0.09207   0.09055  -0.0170   1.0000   0.0116
  -9.750  -0.4215   0.08813   0.08662  -0.0180   1.0000   0.0118
  -9.500  -0.4228   0.08387   0.08237  -0.0192   1.0000   0.0119
  -9.250  -0.4249   0.07947   0.07798  -0.0205   1.0000   0.0120
  -9.000  -0.4304   0.07433   0.07285  -0.0221   1.0000   0.0121
  -8.750  -0.6803   0.03277   0.03054  -0.0500   1.0000   0.0071
  -8.500  -0.6808   0.02626   0.02342  -0.0494   1.0000   0.0072
  -8.250  -0.6667   0.02366   0.02048  -0.0483   1.0000   0.0074
  -8.000  -0.6479   0.02233   0.01895  -0.0472   1.0000   0.0076
  -7.750  -0.6377   0.01841   0.01447  -0.0455   1.0000   0.0078
  -7.500  -0.6215   0.01624   0.01199  -0.0440   1.0000   0.0082
  -7.250  -0.6000   0.01518   0.01080  -0.0432   0.9998   0.0085
  -7.000  -0.5665   0.01428   0.00978  -0.0447   0.9982   0.0088
  -6.750  -0.5326   0.01346   0.00883  -0.0463   0.9964   0.0093
  -6.500  -0.4985   0.01266   0.00790  -0.0479   0.9948   0.0099
  -6.250  -0.4657   0.01214   0.00730  -0.0491   0.9925   0.0106
  -6.000  -0.4326   0.01188   0.00699  -0.0503   0.9897   0.0110
  -5.750  -0.4012   0.01039   0.00530  -0.0514   0.9870   0.0124
  -5.500  -0.3672   0.00994   0.00480  -0.0528   0.9849   0.0135
  -5.250  -0.3344   0.00953   0.00435  -0.0539   0.9817   0.0146
  -5.000  -0.3034   0.00924   0.00401  -0.0546   0.9756   0.0156
  -4.750  -0.2710   0.00862   0.00335  -0.0556   0.9709   0.0188
  -4.500  -0.2408   0.00840   0.00310  -0.0561   0.9628   0.0213
  -4.250  -0.2100   0.00799   0.00267  -0.0566   0.9552   0.0266
  -4.000  -0.1807   0.00783   0.00249  -0.0569   0.9450   0.0304
  -3.750  -0.1528   0.00753   0.00217  -0.0568   0.9342   0.0387
  -3.500  -0.1252   0.00735   0.00195  -0.0566   0.9240   0.0460
  -3.250  -0.0980   0.00716   0.00176  -0.0564   0.9144   0.0573
  -3.000  -0.0709   0.00696   0.00165  -0.0562   0.9047   0.0815
  -2.750  -0.0435   0.00686   0.00156  -0.0560   0.8958   0.0985
  -2.500  -0.0160   0.00679   0.00147  -0.0558   0.8871   0.1097
  -2.250   0.0117   0.00671   0.00138  -0.0557   0.8781   0.1186
  -2.000   0.0391   0.00662   0.00128  -0.0555   0.8676   0.1278
  -1.750   0.0664   0.00655   0.00119  -0.0553   0.8559   0.1393
  -1.500   0.0936   0.00643   0.00110  -0.0551   0.8431   0.1630
  -1.250   0.1206   0.00621   0.00102  -0.0549   0.8282   0.2182
  -1.000   0.1470   0.00591   0.00095  -0.0547   0.8074   0.3111
  -0.750   0.1723   0.00543   0.00089  -0.0544   0.7835   0.4780
  -0.500   0.1973   0.00495   0.00087  -0.0539   0.7598   0.6497
  -0.250   0.2213   0.00462   0.00087  -0.0530   0.7334   0.7848
   0.000   0.2433   0.00443   0.00090  -0.0514   0.7047   0.8884
   0.250   0.2681   0.00446   0.00092  -0.0503   0.6741   0.9549
   0.500   0.3046   0.00458   0.00093  -0.0521   0.6456   0.9846
   0.750   0.3445   0.00471   0.00094  -0.0549   0.6210   0.9986
   1.000   0.3727   0.00484   0.00097  -0.0550   0.6006   1.0000
   1.250   0.3988   0.00496   0.00099  -0.0546   0.5816   1.0000
   1.500   0.4251   0.00508   0.00103  -0.0542   0.5635   1.0000
   1.750   0.4517   0.00519   0.00107  -0.0539   0.5480   1.0000
   2.000   0.4784   0.00530   0.00113  -0.0537   0.5327   1.0000
   2.250   0.5051   0.00543   0.00118  -0.0534   0.5128   1.0000
   2.500   0.5317   0.00559   0.00125  -0.0531   0.4897   1.0000
   2.750   0.5583   0.00575   0.00132  -0.0529   0.4632   1.0000
   3.000   0.5849   0.00593   0.00141  -0.0527   0.4352   1.0000
   3.250   0.6109   0.00620   0.00152  -0.0524   0.3942   1.0000
   3.500   0.6354   0.00668   0.00170  -0.0519   0.3261   1.0000
   3.750   0.6605   0.00711   0.00191  -0.0515   0.2768   1.0000
   4.000   0.6860   0.00748   0.00211  -0.0512   0.2366   1.0000
   4.250   0.7119   0.00780   0.00230  -0.0509   0.2054   1.0000
   4.500   0.7365   0.00831   0.00255  -0.0505   0.1510   1.0000
   4.750   0.7619   0.00870   0.00281  -0.0502   0.1235   1.0000
   5.000   0.7881   0.00899   0.00304  -0.0500   0.1100   1.0000
   5.250   0.8142   0.00926   0.00327  -0.0498   0.0959   1.0000
   5.500   0.8380   0.00990   0.00364  -0.0492   0.0492   1.0000
   5.750   0.8612   0.01063   0.00417  -0.0485   0.0174   1.0000
   6.000   0.8867   0.01103   0.00462  -0.0481   0.0142   1.0000
   6.250   0.9124   0.01138   0.00503  -0.0477   0.0132   1.0000
   6.500   0.9374   0.01182   0.00552  -0.0473   0.0121   1.0000
   6.750   0.9620   0.01233   0.00608  -0.0467   0.0112   1.0000
   7.000   0.9843   0.01317   0.00704  -0.0458   0.0101   1.0000
   7.250   1.0077   0.01381   0.00776  -0.0451   0.0095   1.0000
   7.500   1.0320   0.01428   0.00828  -0.0446   0.0090   1.0000
   7.750   1.0552   0.01491   0.00897  -0.0439   0.0085   1.0000
   8.000   1.0778   0.01560   0.00972  -0.0431   0.0081   1.0000
   8.250   1.0999   0.01632   0.01050  -0.0423   0.0077   1.0000
   8.500   1.1215   0.01709   0.01134  -0.0415   0.0074   1.0000
   8.750   1.1418   0.01800   0.01231  -0.0405   0.0071   1.0000
   9.000   1.1577   0.01952   0.01393  -0.0388   0.0067   1.0000
   9.250   1.1691   0.02197   0.01654  -0.0366   0.0064   1.0000
   9.500   1.1903   0.02264   0.01732  -0.0357   0.0063   1.0000
   9.750   1.2091   0.02371   0.01851  -0.0345   0.0061   1.0000
  10.000   1.2269   0.02485   0.01977  -0.0332   0.0058   1.0000
  10.250   1.2436   0.02605   0.02112  -0.0319   0.0056   1.0000
  10.500   1.2584   0.02742   0.02263  -0.0303   0.0054   1.0000
  10.750   1.2703   0.02913   0.02450  -0.0285   0.0053   1.0000
  11.000   1.2793   0.03105   0.02661  -0.0264   0.0052   1.0000
  11.250   1.2850   0.03308   0.02883  -0.0240   0.0051   1.0000
  11.500   1.2854   0.03502   0.03095  -0.0208   0.0051   1.0000
  11.750   1.2809   0.03740   0.03353  -0.0177   0.0051   1.0000
  12.000   1.2749   0.03995   0.03628  -0.0151   0.0050   1.0000
  12.250   1.2663   0.04295   0.03947  -0.0132   0.0050   1.0000
  12.500   1.2535   0.04672   0.04345  -0.0120   0.0050   1.0000
  12.750   1.2413   0.05074   0.04766  -0.0119   0.0050   1.0000
  13.000   1.2258   0.05568   0.05280  -0.0129   0.0050   1.0000
  13.250   1.2058   0.06193   0.05926  -0.0153   0.0050   1.0000
  13.500   1.1840   0.06918   0.06671  -0.0191   0.0051   1.0000
  13.750   1.1629   0.07697   0.07468  -0.0237   0.0051   1.0000
  14.000   1.1359   0.08656   0.08445  -0.0297   0.0052   1.0000
  14.250   1.1107   0.09666   0.09470  -0.0360   0.0053   1.0000
  14.500   1.0848   0.10776   0.10594  -0.0429   0.0054   1.0000
  14.750   1.0565   0.12016   0.11847  -0.0501   0.0055   1.0000
  15.000   1.0228   0.13469   0.13310  -0.0579   0.0057   1.0000
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