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GOE 613 AIRFOIL (goe613-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 613 AIRFOIL (goe613-il)
Reynolds number: 500,000
Max Cl/Cd: 93.82 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe613-il-500000.txt
Download as CSV file: xf-goe613-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 613 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3396   0.10336   0.10118  -0.0323   1.0000   0.0240
  -9.250  -0.3524   0.10103   0.09890  -0.0318   1.0000   0.0242
  -9.000  -0.3609   0.09835   0.09625  -0.0319   0.9997   0.0243
  -8.750  -0.3491   0.09287   0.09078  -0.0388   0.9971   0.0244
  -8.500  -0.3347   0.08769   0.08559  -0.0454   0.9942   0.0244
  -8.250  -0.3271   0.08288   0.08079  -0.0467   0.9915   0.0249
  -8.000  -0.3088   0.08002   0.07793  -0.0491   0.9885   0.0254
  -7.750  -0.2902   0.07665   0.07455  -0.0537   0.9853   0.0262
  -7.500  -0.2747   0.07235   0.07024  -0.0601   0.9793   0.0274
  -7.250  -0.2416   0.06248   0.06020  -0.0798   0.9726   0.0302
  -7.000  -0.2223   0.05637   0.05392  -0.0861   0.9655   0.0304
  -6.750  -0.2103   0.04834   0.04574  -0.0914   0.9611   0.0311
  -6.500  -0.1841   0.04606   0.04344  -0.0940   0.9594   0.0318
  -6.250  -0.1543   0.04370   0.04102  -0.0973   0.9580   0.0329
  -6.000  -0.1350   0.04101   0.03821  -0.0982   0.9506   0.0346
  -5.750  -0.0982   0.03751   0.03413  -0.1012   0.9465   0.0382
  -5.500  -0.0862   0.03067   0.02700  -0.1024   0.9399   0.0394
  -5.250  -0.0604   0.02904   0.02535  -0.1033   0.9344   0.0404
  -5.000  -0.0308   0.02745   0.02366  -0.1047   0.9305   0.0418
  -4.750  -0.0086   0.02586   0.02191  -0.1042   0.9222   0.0439
  -4.500   0.0256   0.02638   0.02204  -0.1041   0.9164   0.0481
  -4.250   0.0379   0.02158   0.01683  -0.1026   0.9068   0.0499
  -4.000   0.0658   0.02022   0.01546  -0.1032   0.8995   0.0515
  -3.750   0.0879   0.01926   0.01439  -0.1021   0.8884   0.0534
  -3.500   0.1123   0.01836   0.01331  -0.1013   0.8785   0.0564
  -3.250   0.1432   0.01977   0.01448  -0.1008   0.8703   0.0603
  -3.000   0.1620   0.01462   0.00888  -0.0987   0.8608   0.0456
  -2.750   0.1884   0.01361   0.00769  -0.0981   0.8525   0.0454
  -2.500   0.2137   0.01263   0.00656  -0.0973   0.8427   0.0447
  -2.250   0.2391   0.01194   0.00577  -0.0966   0.8325   0.0447
  -2.000   0.2652   0.01137   0.00510  -0.0959   0.8222   0.0449
  -1.750   0.2908   0.01088   0.00454  -0.0953   0.8114   0.0452
  -1.500   0.3158   0.01049   0.00409  -0.0945   0.7995   0.0458
  -1.250   0.3411   0.01025   0.00379  -0.0937   0.7875   0.0470
  -1.000   0.3663   0.01001   0.00349  -0.0930   0.7751   0.0478
  -0.750   0.3912   0.00977   0.00319  -0.0922   0.7626   0.0484
  -0.500   0.4143   0.00933   0.00267  -0.0911   0.7498   0.0501
  -0.250   0.4383   0.00912   0.00240  -0.0902   0.7357   0.0522
   0.000   0.4627   0.00902   0.00224  -0.0893   0.7211   0.0546
   0.250   0.4870   0.00895   0.00211  -0.0884   0.7057   0.0579
   0.500   0.5113   0.00888   0.00199  -0.0875   0.6892   0.0628
   0.750   0.5350   0.00880   0.00189  -0.0865   0.6703   0.0770
   1.000   0.5339   0.00679   0.00204  -0.0809   0.6523   0.8224
   1.250   0.6560   0.00700   0.00218  -0.1013   0.6010   1.0000
   1.500   0.6736   0.00723   0.00220  -0.0991   0.5688   1.0000
   1.750   0.6920   0.00746   0.00227  -0.0971   0.5438   1.0000
   2.000   0.7115   0.00768   0.00235  -0.0954   0.5235   1.0000
   2.250   0.7317   0.00788   0.00244  -0.0938   0.5053   1.0000
   2.500   0.7523   0.00808   0.00254  -0.0923   0.4882   1.0000
   2.750   0.7729   0.00828   0.00265  -0.0908   0.4707   1.0000
   3.000   0.7935   0.00848   0.00276  -0.0893   0.4530   1.0000
   3.250   0.8142   0.00869   0.00288  -0.0879   0.4346   1.0000
   3.500   0.8350   0.00890   0.00300  -0.0864   0.4158   1.0000
   3.750   0.8556   0.00913   0.00315  -0.0850   0.3980   1.0000
   4.000   0.8763   0.00937   0.00330  -0.0836   0.3819   1.0000
   4.250   0.8970   0.00961   0.00347  -0.0822   0.3677   1.0000
   4.500   0.9178   0.00986   0.00365  -0.0808   0.3546   1.0000
   4.750   0.9384   0.01011   0.00385  -0.0794   0.3419   1.0000
   5.000   0.9589   0.01038   0.00404  -0.0780   0.3293   1.0000
   5.250   0.9793   0.01065   0.00424  -0.0766   0.3154   1.0000
   5.500   1.0005   0.01089   0.00444  -0.0753   0.3046   1.0000
   5.750   1.0223   0.01110   0.00465  -0.0742   0.2955   1.0000
   6.000   1.0429   0.01138   0.00487  -0.0729   0.2864   1.0000
   6.250   1.0650   0.01158   0.00508  -0.0718   0.2778   1.0000
   6.500   1.0861   0.01182   0.00532  -0.0706   0.2685   1.0000
   6.750   1.1064   0.01210   0.00555  -0.0693   0.2569   1.0000
   7.000   1.1272   0.01236   0.00577  -0.0681   0.2449   1.0000
   7.250   1.1474   0.01264   0.00602  -0.0668   0.2311   1.0000
   7.500   1.1664   0.01299   0.00631  -0.0652   0.2147   1.0000
   7.750   1.1838   0.01342   0.00662  -0.0635   0.1893   1.0000
   8.000   1.1912   0.01436   0.00719  -0.0601   0.1337   1.0000
   8.750   1.2045   0.01787   0.01001  -0.0487   0.0201   1.0000
   9.000   1.2191   0.01845   0.01068  -0.0466   0.0190   1.0000
   9.250   1.2320   0.01914   0.01146  -0.0443   0.0179   1.0000
   9.500   1.2422   0.02002   0.01243  -0.0417   0.0167   1.0000
   9.750   1.2521   0.02090   0.01341  -0.0392   0.0160   1.0000
  10.000   1.2629   0.02173   0.01433  -0.0369   0.0156   1.0000
  10.250   1.2723   0.02267   0.01536  -0.0345   0.0151   1.0000
  10.500   1.2798   0.02373   0.01651  -0.0321   0.0148   1.0000
  10.750   1.2853   0.02496   0.01783  -0.0295   0.0144   1.0000
  11.000   1.2896   0.02631   0.01927  -0.0271   0.0140   1.0000
  11.250   1.2911   0.02791   0.02096  -0.0246   0.0137   1.0000
  11.500   1.2929   0.02957   0.02271  -0.0224   0.0135   1.0000
  11.750   1.2931   0.03146   0.02469  -0.0203   0.0134   1.0000
  12.000   1.2905   0.03369   0.02701  -0.0183   0.0132   1.0000
  12.250   1.2860   0.03623   0.02965  -0.0166   0.0130   1.0000
  12.500   1.2791   0.03916   0.03267  -0.0151   0.0128   1.0000
  12.750   1.2693   0.04250   0.03609  -0.0137   0.0125   1.0000
  13.000   1.2634   0.04558   0.03923  -0.0124   0.0123   1.0000
  13.250   1.2684   0.04772   0.04149  -0.0121   0.0122   1.0000
  13.500   1.2714   0.05015   0.04402  -0.0119   0.0119   1.0000
  13.750   1.2732   0.05273   0.04670  -0.0116   0.0118   1.0000
  14.000   1.2743   0.05543   0.04948  -0.0113   0.0117   1.0000
  14.250   1.2755   0.05814   0.05227  -0.0109   0.0116   1.0000
  14.500   1.2773   0.06087   0.05511  -0.0108   0.0114   1.0000
  14.750   1.2794   0.06358   0.05790  -0.0106   0.0113   1.0000
  15.000   1.2820   0.06627   0.06068  -0.0105   0.0112   1.0000
  15.250   1.2841   0.06905   0.06356  -0.0104   0.0111   1.0000
  15.500   1.2867   0.07181   0.06641  -0.0103   0.0111   1.0000
  15.750   1.2878   0.07487   0.06958  -0.0105   0.0109   1.0000
  16.000   1.2898   0.07783   0.07265  -0.0104   0.0110   1.0000
  16.250   1.2903   0.08107   0.07602  -0.0106   0.0110   1.0000
  16.500   1.2905   0.08442   0.07950  -0.0108   0.0112   1.0000
  16.750   1.2862   0.08858   0.08381  -0.0119   0.0111   1.0000
  17.000   1.2815   0.09286   0.08824  -0.0133   0.0110   1.0000
  17.250   1.2769   0.09720   0.09274  -0.0143   0.0113   1.0000
  17.500   1.2688   0.10222   0.09790  -0.0165   0.0112   1.0000
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