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GOE 702 AIRFOIL (goe702-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 702 AIRFOIL (goe702-il)
Reynolds number: 100,000
Max Cl/Cd: 43.13 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe702-il-100000-n5.txt
Download as CSV file: xf-goe702-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 702 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.2005   0.09741   0.09157  -0.0566   0.8095   0.0682
 -10.500  -0.2060   0.09243   0.08658  -0.0591   0.8021   0.0687
 -10.250  -0.2212   0.08598   0.08011  -0.0627   0.7963   0.0697
 -10.000  -0.2093   0.08453   0.07865  -0.0628   0.7878   0.0706
  -9.750  -0.2070   0.08149   0.07559  -0.0639   0.7794   0.0714
  -9.500  -0.2118   0.07738   0.07144  -0.0656   0.7729   0.0723
  -9.000  -0.4289   0.04080   0.03395  -0.0874   0.7650   0.0744
  -8.750  -0.4344   0.03694   0.02948  -0.0865   0.7578   0.0762
  -8.500  -0.4209   0.03543   0.02773  -0.0853   0.7511   0.0776
  -8.250  -0.4006   0.03476   0.02705  -0.0846   0.7421   0.0790
  -8.000  -0.3830   0.03364   0.02574  -0.0835   0.7354   0.0807
  -7.750  -0.3668   0.03209   0.02386  -0.0825   0.7300   0.0827
  -7.500  -0.3499   0.03043   0.02182  -0.0817   0.7234   0.0850
  -7.250  -0.3268   0.02994   0.02134  -0.0810   0.7173   0.0867
  -7.000  -0.3044   0.02928   0.02056  -0.0801   0.7123   0.0890
  -6.750  -0.2828   0.02833   0.01937  -0.0794   0.7063   0.0919
  -6.500  -0.2604   0.02741   0.01825  -0.0787   0.6998   0.0946
  -6.250  -0.2363   0.02693   0.01775  -0.0779   0.6941   0.0970
  -6.000  -0.2125   0.02631   0.01696  -0.0772   0.6890   0.1005
  -5.750  -0.1888   0.02557   0.01601  -0.0766   0.6818   0.1043
  -5.500  -0.1641   0.02510   0.01557  -0.0759   0.6755   0.1072
  -5.250  -0.1392   0.02458   0.01490  -0.0752   0.6705   0.1114
  -5.000  -0.1145   0.02404   0.01422  -0.0746   0.6631   0.1159
  -4.750  -0.0894   0.02361   0.01383  -0.0740   0.6561   0.1197
  -4.500  -0.0637   0.02315   0.01321  -0.0733   0.6506   0.1250
  -4.250  -0.0386   0.02273   0.01275  -0.0728   0.6428   0.1298
  -4.000  -0.0131   0.02237   0.01239  -0.0722   0.6356   0.1350
  -3.750   0.0133   0.02197   0.01178  -0.0715   0.6299   0.1412
  -3.500   0.0382   0.02165   0.01156  -0.0710   0.6210   0.1464
  -3.250   0.0643   0.02132   0.01116  -0.0704   0.6136   0.1530
  -3.000   0.0902   0.02099   0.01080  -0.0698   0.6064   0.1593
  -2.750   0.1158   0.02076   0.01057  -0.0693   0.5975   0.1665
  -2.500   0.1423   0.02043   0.01017  -0.0687   0.5909   0.1743
  -2.250   0.1676   0.02026   0.01005  -0.0682   0.5810   0.1827
  -2.000   0.1939   0.01999   0.00975  -0.0676   0.5732   0.1918
  -1.750   0.2196   0.01983   0.00960  -0.0670   0.5637   0.2024
  -1.500   0.2456   0.01962   0.00941  -0.0664   0.5554   0.2137
  -1.250   0.2716   0.01949   0.00930  -0.0659   0.5466   0.2275
  -1.000   0.2976   0.01937   0.00917  -0.0653   0.5378   0.2438
  -0.750   0.3237   0.01929   0.00908  -0.0648   0.5294   0.2622
  -0.500   0.3495   0.01924   0.00903  -0.0642   0.5205   0.2820
  -0.250   0.3756   0.01921   0.00895  -0.0637   0.5128   0.3017
   0.000   0.4012   0.01922   0.00896  -0.0631   0.5044   0.3204
   0.250   0.4276   0.01917   0.00886  -0.0626   0.4982   0.3389
   0.500   0.4532   0.01924   0.00897  -0.0621   0.4901   0.3570
   0.750   0.4795   0.01924   0.00894  -0.0616   0.4834   0.3752
   1.000   0.5060   0.01929   0.00895  -0.0612   0.4770   0.3941
   1.250   0.5324   0.01936   0.00906  -0.0609   0.4702   0.4143
   1.500   0.5590   0.01939   0.00906  -0.0606   0.4648   0.4383
   1.750   0.5847   0.01941   0.00914  -0.0601   0.4597   0.4699
   2.000   0.6087   0.01938   0.00932  -0.0594   0.4539   0.5172
   2.250   0.7013   0.01854   0.00948  -0.0714   0.4462   1.0000
   2.500   0.7251   0.01884   0.00961  -0.0706   0.4416   1.0000
   2.750   0.7478   0.01918   0.00988  -0.0698   0.4365   1.0000
   3.000   0.7710   0.01949   0.01009  -0.0689   0.4321   1.0000
   3.250   0.7949   0.01980   0.01025  -0.0681   0.4282   1.0000
   3.500   0.8193   0.02012   0.01041  -0.0675   0.4248   1.0000
   3.750   0.8406   0.02053   0.01083  -0.0664   0.4202   1.0000
   4.000   0.8627   0.02092   0.01117  -0.0655   0.4158   1.0000
   4.250   0.8856   0.02127   0.01145  -0.0647   0.4119   1.0000
   4.500   0.9097   0.02162   0.01168  -0.0640   0.4086   1.0000
   4.750   0.9336   0.02202   0.01199  -0.0633   0.4055   1.0000
   5.000   0.9536   0.02253   0.01255  -0.0622   0.4018   1.0000
   5.250   0.9744   0.02301   0.01304  -0.0612   0.3981   1.0000
   5.500   0.9963   0.02344   0.01345  -0.0603   0.3945   1.0000
   5.750   1.0196   0.02384   0.01377  -0.0596   0.3913   1.0000
   6.000   1.0446   0.02422   0.01407  -0.0591   0.3884   1.0000
   6.250   1.0638   0.02480   0.01469  -0.0580   0.3853   1.0000
   6.500   1.0811   0.02544   0.01541  -0.0567   0.3819   1.0000
   6.750   1.0999   0.02604   0.01606  -0.0556   0.3787   1.0000
   7.000   1.1201   0.02657   0.01660  -0.0546   0.3756   1.0000
   7.250   1.1424   0.02703   0.01702  -0.0539   0.3727   1.0000
   7.500   1.1674   0.02745   0.01737  -0.0535   0.3701   1.0000
   7.750   1.1845   0.02814   0.01812  -0.0522   0.3673   1.0000
   8.000   1.1947   0.02904   0.01916  -0.0502   0.3641   1.0000
   8.250   1.2067   0.02988   0.02010  -0.0485   0.3610   1.0000
   8.500   1.2215   0.03061   0.02088  -0.0470   0.3580   1.0000
   8.750   1.2403   0.03119   0.02146  -0.0460   0.3553   1.0000
   9.000   1.2639   0.03163   0.02187  -0.0455   0.3528   1.0000
   9.250   1.2902   0.03208   0.02228  -0.0454   0.3507   1.0000
   9.500   1.2788   0.03363   0.02405  -0.0412   0.3475   1.0000
   9.750   1.2673   0.03530   0.02588  -0.0373   0.3443   1.0000
  10.000   1.2633   0.03690   0.02759  -0.0348   0.3410   1.0000
  10.250   1.2718   0.03801   0.02875  -0.0333   0.3382   1.0000
  10.500   1.2924   0.03854   0.02927  -0.0327   0.3358   1.0000
  10.750   1.3215   0.03871   0.02943  -0.0326   0.3339   1.0000
  11.000   1.2755   0.04320   0.03418  -0.0288   0.3297   1.0000
  11.250   1.1706   0.05416   0.04546  -0.0263   0.3206   1.0000
  11.500   1.1936   0.05434   0.04564  -0.0258   0.3187   1.0000
  11.750   1.2249   0.05378   0.04509  -0.0252   0.3174   1.0000
  12.000   1.2621   0.05279   0.04407  -0.0247   0.3164   1.0000
  14.000   0.9325   0.12325   0.11537  -0.0402   0.2442   1.0000
  14.250   0.9446   0.12482   0.11698  -0.0403   0.2411   1.0000
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