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GOE 676 (= M 12) AIRFOIL (goe676-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 676 (= M 12) AIRFOIL (goe676-il)
Reynolds number: 500,000
Max Cl/Cd: 86.12 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe676-il-500000.txt
Download as CSV file: xf-goe676-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 676 (= M 12) 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
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.9026   0.04922   0.04621  -0.0523   1.0000   0.0235
 -12.250  -0.9325   0.04417   0.04089  -0.0517   1.0000   0.0236
 -12.000  -0.9451   0.04134   0.03792  -0.0494   1.0000   0.0238
 -11.750  -0.9394   0.04028   0.03683  -0.0475   1.0000   0.0242
 -11.500  -0.9248   0.03979   0.03633  -0.0465   1.0000   0.0245
 -11.250  -0.9104   0.03916   0.03568  -0.0454   1.0000   0.0250
 -11.000  -0.8996   0.03794   0.03436  -0.0441   1.0000   0.0255
 -10.750  -0.8950   0.03568   0.03187  -0.0422   1.0000   0.0262
 -10.500  -0.8919   0.03297   0.02882  -0.0400   1.0000   0.0271
 -10.250  -0.8834   0.03105   0.02654  -0.0379   1.0000   0.0279
 -10.000  -0.8795   0.02806   0.02321  -0.0353   1.0000   0.0287
  -9.750  -0.8630   0.02718   0.02232  -0.0339   1.0000   0.0294
  -9.500  -0.8466   0.02662   0.02172  -0.0323   1.0000   0.0300
  -9.250  -0.8314   0.02600   0.02104  -0.0304   1.0000   0.0307
  -9.000  -0.8180   0.02531   0.02026  -0.0281   1.0000   0.0315
  -8.750  -0.8069   0.02448   0.01929  -0.0253   1.0000   0.0324
  -8.500  -0.7879   0.02362   0.01823  -0.0241   0.9990   0.0333
  -8.250  -0.7576   0.02173   0.01604  -0.0255   0.9961   0.0343
  -8.000  -0.7249   0.02043   0.01469  -0.0272   0.9939   0.0355
  -7.750  -0.6916   0.01994   0.01416  -0.0288   0.9905   0.0366
  -7.500  -0.6573   0.01924   0.01338  -0.0305   0.9873   0.0379
  -7.250  -0.6221   0.01835   0.01236  -0.0323   0.9849   0.0390
  -7.000  -0.5857   0.01772   0.01160  -0.0343   0.9828   0.0402
  -6.750  -0.5556   0.01655   0.01030  -0.0350   0.9772   0.0413
  -6.500  -0.5233   0.01553   0.00926  -0.0363   0.9726   0.0426
  -6.250  -0.4922   0.01500   0.00871  -0.0371   0.9666   0.0438
  -6.000  -0.4632   0.01457   0.00826  -0.0373   0.9589   0.0452
  -5.750  -0.4360   0.01414   0.00777  -0.0371   0.9505   0.0466
  -5.500  -0.4102   0.01371   0.00727  -0.0366   0.9417   0.0477
  -5.250  -0.3854   0.01339   0.00689  -0.0358   0.9313   0.0486
  -5.000  -0.3631   0.01253   0.00600  -0.0347   0.9218   0.0506
  -4.750  -0.3388   0.01217   0.00562  -0.0338   0.9116   0.0525
  -4.500  -0.3136   0.01191   0.00533  -0.0332   0.9011   0.0547
  -4.250  -0.2884   0.01164   0.00500  -0.0324   0.8912   0.0569
  -4.000  -0.2633   0.01133   0.00462  -0.0317   0.8801   0.0591
  -3.750  -0.2389   0.01088   0.00416  -0.0310   0.8687   0.0632
  -3.500  -0.2130   0.01066   0.00390  -0.0304   0.8576   0.0673
  -3.250  -0.1875   0.01040   0.00357  -0.0298   0.8462   0.0725
  -3.000  -0.1616   0.01013   0.00329  -0.0293   0.8337   0.0794
  -2.750  -0.1354   0.00989   0.00302  -0.0289   0.8216   0.0873
  -2.500  -0.1091   0.00968   0.00281  -0.0285   0.8099   0.0982
  -2.250  -0.0829   0.00944   0.00265  -0.0281   0.7983   0.1248
  -2.000  -0.0567   0.00915   0.00250  -0.0279   0.7860   0.1672
  -1.750  -0.0314   0.00873   0.00232  -0.0275   0.7739   0.2359
  -1.500  -0.0100   0.00787   0.00214  -0.0266   0.7619   0.4326
  -1.250   0.0107   0.00714   0.00200  -0.0254   0.7497   0.6003
  -1.000   0.0304   0.00654   0.00200  -0.0234   0.7366   0.7637
  -0.750   0.0541   0.00644   0.00210  -0.0220   0.7237   0.8421
  -0.500   0.0795   0.00648   0.00216  -0.0210   0.7112   0.8781
  -0.250   0.1049   0.00657   0.00222  -0.0200   0.6989   0.9026
   0.000   0.1293   0.00670   0.00228  -0.0187   0.6869   0.9238
   0.250   0.1550   0.00682   0.00237  -0.0178   0.6752   0.9388
   0.500   0.1849   0.00697   0.00246  -0.0179   0.6638   0.9487
   0.750   0.2156   0.00713   0.00253  -0.0181   0.6511   0.9581
   1.000   0.2512   0.00732   0.00263  -0.0195   0.6385   0.9657
   1.250   0.2877   0.00747   0.00271  -0.0212   0.6258   0.9711
   1.500   0.3346   0.00765   0.00282  -0.0252   0.6123   0.9748
   1.750   0.3738   0.00778   0.00289  -0.0276   0.6004   0.9797
   2.000   0.4101   0.00788   0.00294  -0.0295   0.5888   0.9836
   2.250   0.4497   0.00797   0.00296  -0.0321   0.5763   0.9860
   2.500   0.4912   0.00806   0.00301  -0.0351   0.5617   0.9903
   2.750   0.5317   0.00817   0.00306  -0.0379   0.5441   0.9946
   3.000   0.5704   0.00822   0.00306  -0.0404   0.5246   0.9971
   3.250   0.6056   0.00830   0.00308  -0.0421   0.5062   0.9992
   3.500   0.6349   0.00839   0.00312  -0.0427   0.4871   1.0000
   3.750   0.6597   0.00851   0.00316  -0.0422   0.4685   1.0000
   4.000   0.6842   0.00865   0.00323  -0.0418   0.4506   1.0000
   4.250   0.7086   0.00879   0.00332  -0.0413   0.4330   1.0000
   4.500   0.7328   0.00894   0.00342  -0.0407   0.4172   1.0000
   4.750   0.7566   0.00910   0.00353  -0.0401   0.4023   1.0000
   5.000   0.7799   0.00928   0.00366  -0.0394   0.3870   1.0000
   5.250   0.8026   0.00947   0.00380  -0.0386   0.3687   1.0000
   5.500   0.8251   0.00967   0.00395  -0.0377   0.3523   1.0000
   5.750   0.8473   0.00987   0.00412  -0.0368   0.3368   1.0000
   6.000   0.8690   0.01009   0.00430  -0.0357   0.3192   1.0000
   6.250   0.8903   0.01034   0.00450  -0.0346   0.3007   1.0000
   6.500   0.9104   0.01066   0.00472  -0.0333   0.2736   1.0000
   6.750   0.9287   0.01111   0.00499  -0.0318   0.2359   1.0000
   7.250   0.9595   0.01249   0.00587  -0.0279   0.1459   1.0000
   7.500   0.9778   0.01296   0.00628  -0.0263   0.1327   1.0000
   7.750   0.9964   0.01341   0.00669  -0.0248   0.1231   1.0000
   8.000   1.0166   0.01376   0.00706  -0.0235   0.1154   1.0000
   8.250   1.0359   0.01422   0.00750  -0.0222   0.1065   1.0000
   8.500   1.0567   0.01460   0.00787  -0.0212   0.0958   1.0000
   8.750   1.0766   0.01509   0.00826  -0.0200   0.0727   1.0000
   9.000   1.0912   0.01600   0.00896  -0.0182   0.0480   1.0000
   9.250   1.1076   0.01678   0.00971  -0.0166   0.0405   1.0000
   9.500   1.1243   0.01752   0.01045  -0.0150   0.0364   1.0000
   9.750   1.1398   0.01831   0.01129  -0.0133   0.0333   1.0000
  10.000   1.1563   0.01899   0.01203  -0.0118   0.0310   1.0000
  10.250   1.1666   0.02002   0.01308  -0.0095   0.0287   1.0000
  10.500   1.1781   0.02079   0.01393  -0.0072   0.0274   1.0000
  10.750   1.1900   0.02157   0.01478  -0.0052   0.0261   1.0000
  11.000   1.2007   0.02249   0.01575  -0.0032   0.0250   1.0000
  11.250   1.2080   0.02368   0.01699  -0.0011   0.0240   1.0000
  11.500   1.2080   0.02549   0.01886   0.0015   0.0231   1.0000
  11.750   1.2205   0.02650   0.01996   0.0027   0.0224   1.0000
  12.000   1.2307   0.02772   0.02127   0.0039   0.0216   1.0000
  12.250   1.2399   0.02907   0.02269   0.0050   0.0208   1.0000
  12.500   1.2477   0.03060   0.02427   0.0060   0.0201   1.0000
  12.750   1.2528   0.03243   0.02617   0.0069   0.0196   1.0000
  13.000   1.2523   0.03484   0.02864   0.0081   0.0191   1.0000
  13.250   1.2537   0.03717   0.03106   0.0090   0.0186   1.0000
  13.500   1.2603   0.03908   0.03308   0.0095   0.0183   1.0000
  13.750   1.2653   0.04119   0.03530   0.0099   0.0179   1.0000
  14.000   1.2693   0.04345   0.03767   0.0102   0.0175   1.0000
  14.250   1.2726   0.04584   0.04015   0.0103   0.0171   1.0000
  14.500   1.2755   0.04833   0.04273   0.0103   0.0168   1.0000
  14.750   1.2777   0.05093   0.04542   0.0102   0.0164   1.0000
  15.000   1.2789   0.05367   0.04822   0.0099   0.0161   1.0000
  15.250   1.2791   0.05657   0.05118   0.0097   0.0158   1.0000
  15.500   1.2769   0.05969   0.05437   0.0096   0.0154   1.0000
  15.750   1.2722   0.06312   0.05790   0.0098   0.0151   1.0000
  16.000   1.2706   0.06660   0.06153   0.0089   0.0150   1.0000
  16.250   1.2679   0.07027   0.06534   0.0078   0.0148   1.0000
  16.500   1.2642   0.07415   0.06936   0.0067   0.0146   1.0000
  16.750   1.2594   0.07826   0.07361   0.0054   0.0144   1.0000
  17.000   1.2538   0.08261   0.07810   0.0039   0.0143   1.0000
  17.250   1.2472   0.08722   0.08284   0.0022   0.0141   1.0000
  17.500   1.2395   0.09207   0.08783   0.0003   0.0140   1.0000
  17.750   1.2310   0.09719   0.09310  -0.0019   0.0138   1.0000
  18.000   1.2217   0.10258   0.09862  -0.0043   0.0137   1.0000
  18.250   1.2113   0.10825   0.10443  -0.0070   0.0136   1.0000
  18.500   1.1999   0.11424   0.11056  -0.0100   0.0135   1.0000
  18.750   1.1872   0.12064   0.11711  -0.0133   0.0134   1.0000
  19.000   1.1731   0.12753   0.12414  -0.0171   0.0134   1.0000
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