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GOE 758 AIRFOIL (goe758-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 758 AIRFOIL (goe758-il)
Reynolds number: 200,000
Max Cl/Cd: 73.69 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe758-il-200000.txt
Download as CSV file: xf-goe758-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 758 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.2610   0.11254   0.10900  -0.0446   1.0000   0.0565
 -10.500  -0.2745   0.10948   0.10602  -0.0481   1.0000   0.0592
 -10.250  -0.2981   0.10637   0.10302  -0.0524   1.0000   0.0598
 -10.000  -0.2852   0.10256   0.09924  -0.0491   1.0000   0.0607
  -9.750  -0.2777   0.10080   0.09753  -0.0464   1.0000   0.0615
  -9.500  -0.2834   0.09981   0.09662  -0.0431   1.0000   0.0624
  -9.250  -0.2714   0.09696   0.09379  -0.0450   0.9969   0.0645
  -8.750  -0.2535   0.08465   0.08150  -0.0639   0.9774   0.0716
  -8.500  -0.2227   0.08229   0.07912  -0.0642   0.9722   0.0737
  -8.250  -0.2013   0.07854   0.07537  -0.0689   0.9623   0.0770
  -8.000  -0.2095   0.06465   0.06134  -0.0982   0.9409   0.0833
  -7.750  -0.1751   0.06442   0.06118  -0.0934   0.9327   0.0849
  -7.500  -0.1458   0.06187   0.05858  -0.0958   0.9210   0.0879
  -7.250  -0.1698   0.05257   0.04862  -0.1106   0.8919   0.0966
  -7.000  -0.1438   0.04986   0.04605  -0.1098   0.8779   0.0983
  -6.750  -0.1252   0.04832   0.04449  -0.1088   0.8614   0.1006
  -6.250  -0.1135   0.04227   0.03788  -0.1093   0.8269   0.1134
  -6.000  -0.0954   0.04055   0.03612  -0.1085   0.8128   0.1164
  -5.750  -0.0879   0.03805   0.03311  -0.1083   0.7986   0.1278
  -5.500  -0.0788   0.02760   0.02128  -0.1064   0.7885   0.0730
  -5.250  -0.0568   0.02470   0.01788  -0.1052   0.7793   0.0649
  -5.000  -0.0355   0.02250   0.01513  -0.1038   0.7682   0.0622
  -4.750  -0.0103   0.02131   0.01355  -0.1029   0.7595   0.0608
  -4.500   0.0156   0.02064   0.01264  -0.1022   0.7504   0.0600
  -4.250   0.0413   0.01959   0.01141  -0.1016   0.7423   0.0597
  -4.000   0.0672   0.01861   0.01028  -0.1011   0.7343   0.0596
  -3.750   0.0934   0.01784   0.00938  -0.1006   0.7271   0.0598
  -3.500   0.1191   0.01702   0.00850  -0.1001   0.7196   0.0601
  -3.250   0.1444   0.01622   0.00768  -0.0996   0.7133   0.0618
  -3.000   0.1695   0.01575   0.00723  -0.0990   0.7060   0.0636
  -2.750   0.1956   0.01535   0.00675  -0.0985   0.7001   0.0650
  -2.500   0.2205   0.01502   0.00640  -0.0979   0.6931   0.0665
  -2.250   0.2464   0.01474   0.00604  -0.0974   0.6868   0.0686
  -2.000   0.2723   0.01451   0.00573  -0.0969   0.6809   0.0716
  -1.750   0.2979   0.01429   0.00551  -0.0964   0.6742   0.0778
  -1.500   0.3247   0.01407   0.00528  -0.0960   0.6686   0.0965
  -1.250   0.3444   0.01306   0.00520  -0.0951   0.6624   0.3286
  -1.000   0.3654   0.01256   0.00530  -0.0938   0.6563   0.5062
  -0.750   0.3891   0.01242   0.00538  -0.0926   0.6512   0.6124
  -0.500   0.4107   0.01225   0.00549  -0.0911   0.6448   0.6893
  -0.250   0.4344   0.01204   0.00553  -0.0897   0.6392   0.7769
   0.000   0.5146   0.01185   0.00554  -0.0997   0.6326   0.9666
   0.250   0.5649   0.01196   0.00552  -0.1046   0.6256   1.0000
   0.500   0.5895   0.01213   0.00552  -0.1040   0.6203   1.0000
   0.750   0.6125   0.01232   0.00564  -0.1032   0.6145   1.0000
   1.000   0.6360   0.01248   0.00572  -0.1024   0.6083   1.0000
   1.250   0.6619   0.01267   0.00576  -0.1020   0.6032   1.0000
   1.500   0.6847   0.01286   0.00593  -0.1011   0.5970   1.0000
   1.750   0.7090   0.01302   0.00602  -0.1003   0.5909   1.0000
   2.000   0.7356   0.01323   0.00608  -0.1001   0.5858   1.0000
   2.250   0.7577   0.01339   0.00628  -0.0990   0.5790   1.0000
   2.500   0.7828   0.01354   0.00636  -0.0984   0.5731   1.0000
   2.750   0.8086   0.01373   0.00647  -0.0980   0.5677   1.0000
   3.000   0.8312   0.01387   0.00665  -0.0970   0.5605   1.0000
   3.250   0.8574   0.01401   0.00670  -0.0966   0.5549   1.0000
   3.500   0.8811   0.01420   0.00689  -0.0959   0.5485   1.0000
   3.750   0.9054   0.01432   0.00701  -0.0952   0.5417   1.0000
   4.000   0.9320   0.01446   0.00706  -0.0949   0.5362   1.0000
   4.250   0.9540   0.01461   0.00728  -0.0938   0.5283   1.0000
   4.500   0.9802   0.01472   0.00733  -0.0935   0.5225   1.0000
   4.750   1.0029   0.01490   0.00755  -0.0925   0.5150   1.0000
   5.000   1.0278   0.01501   0.00763  -0.0920   0.5081   1.0000
   5.250   1.0515   0.01519   0.00783  -0.0912   0.5011   1.0000
   5.500   1.0754   0.01534   0.00799  -0.0905   0.4938   1.0000
   5.750   1.0998   0.01553   0.00816  -0.0899   0.4871   1.0000
   6.000   1.1226   0.01571   0.00837  -0.0890   0.4791   1.0000
   6.250   1.1474   0.01592   0.00855  -0.0885   0.4725   1.0000
   6.500   1.1692   0.01615   0.00885  -0.0875   0.4645   1.0000
   6.750   1.1939   0.01636   0.00901  -0.0870   0.4575   1.0000
   7.000   1.2145   0.01658   0.00931  -0.0858   0.4487   1.0000
   7.250   1.2378   0.01682   0.00952  -0.0850   0.4411   1.0000
   7.500   1.2586   0.01708   0.00984  -0.0839   0.4328   1.0000
   7.750   1.2822   0.01740   0.01014  -0.0832   0.4261   1.0000
   8.000   1.3023   0.01771   0.01055  -0.0820   0.4184   1.0000
   8.250   1.3261   0.01804   0.01084  -0.0814   0.4118   1.0000
   8.500   1.3434   0.01834   0.01125  -0.0798   0.4031   1.0000
   8.750   1.3635   0.01864   0.01155  -0.0785   0.3947   1.0000
   9.000   1.3797   0.01891   0.01187  -0.0766   0.3850   1.0000
   9.250   1.3956   0.01926   0.01227  -0.0748   0.3757   1.0000
   9.500   1.4136   0.01961   0.01258  -0.0733   0.3672   1.0000
   9.750   1.4250   0.01998   0.01309  -0.0707   0.3579   1.0000
  10.000   1.4386   0.02039   0.01350  -0.0685   0.3492   1.0000
  10.250   1.4468   0.02080   0.01401  -0.0654   0.3405   1.0000
  10.500   1.4556   0.02129   0.01455  -0.0625   0.3318   1.0000
  10.750   1.4624   0.02184   0.01510  -0.0595   0.3220   1.0000
  11.000   1.4667   0.02249   0.01587  -0.0563   0.3113   1.0000
  11.250   1.4705   0.02327   0.01670  -0.0533   0.2999   1.0000
  11.500   1.4726   0.02423   0.01769  -0.0504   0.2877   1.0000
  11.750   1.4732   0.02538   0.01888  -0.0476   0.2745   1.0000
  12.000   1.4727   0.02676   0.02031  -0.0451   0.2595   1.0000
  12.250   1.4701   0.02845   0.02204  -0.0426   0.2410   1.0000
  12.500   1.4588   0.03092   0.02444  -0.0400   0.2148   1.0000
  12.750   1.4414   0.03420   0.02758  -0.0377   0.1819   1.0000
  13.000   1.4177   0.03842   0.03160  -0.0358   0.1461   1.0000
  13.250   1.3918   0.04328   0.03625  -0.0345   0.1129   1.0000
  13.500   1.3697   0.04807   0.04092  -0.0337   0.0934   1.0000
  13.750   1.3471   0.05321   0.04599  -0.0333   0.0780   1.0000
  14.000   1.3279   0.05821   0.05097  -0.0332   0.0648   1.0000
  14.250   1.3150   0.06270   0.05547  -0.0333   0.0555   1.0000
  14.500   1.3037   0.06714   0.05994  -0.0336   0.0494   1.0000
  14.750   1.2908   0.07194   0.06477  -0.0342   0.0458   1.0000
  15.000   1.2832   0.07621   0.06914  -0.0348   0.0433   1.0000
  15.250   1.2735   0.08083   0.07382  -0.0356   0.0412   1.0000
  15.500   1.2636   0.08559   0.07864  -0.0365   0.0397   1.0000
  15.750   1.2558   0.09009   0.08321  -0.0374   0.0385   1.0000
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