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GOE 681 AIRFOIL (goe681-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 681 AIRFOIL (goe681-il)
Reynolds number: 100,000
Max Cl/Cd: 42.15 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe681-il-100000-n5.txt
Download as CSV file: xf-goe681-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 681 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.5377   0.05743   0.05136  -0.0875   0.9854   0.0507
 -10.750  -0.5643   0.05012   0.04358  -0.0956   0.9695   0.0507
 -10.500  -0.5738   0.04614   0.03920  -0.0971   0.9554   0.0510
 -10.250  -0.5709   0.04313   0.03586  -0.0976   0.9431   0.0515
 -10.000  -0.5496   0.04136   0.03402  -0.0987   0.9363   0.0521
  -9.750  -0.5330   0.03955   0.03206  -0.0990   0.9272   0.0526
  -9.500  -0.5078   0.03760   0.02990  -0.1007   0.9222   0.0532
  -9.250  -0.4946   0.03607   0.02820  -0.0996   0.9114   0.0538
  -9.000  -0.4694   0.03432   0.02623  -0.1006   0.9057   0.0544
  -8.750  -0.4522   0.03295   0.02466  -0.0997   0.8965   0.0552
  -8.250  -0.4000   0.03017   0.02143  -0.1006   0.8844   0.0568
  -8.000  -0.3817   0.02937   0.02065  -0.0994   0.8747   0.0575
  -7.750  -0.3535   0.02842   0.01963  -0.0999   0.8690   0.0587
  -7.500  -0.3307   0.02763   0.01875  -0.0993   0.8615   0.0601
  -7.250  -0.3083   0.02685   0.01785  -0.0986   0.8535   0.0619
  -7.000  -0.2796   0.02601   0.01693  -0.0990   0.8482   0.0638
  -6.750  -0.2602   0.02545   0.01633  -0.0977   0.8396   0.0656
  -6.500  -0.2362   0.02478   0.01556  -0.0971   0.8324   0.0680
  -6.250  -0.2075   0.02402   0.01473  -0.0973   0.8272   0.0707
  -6.000  -0.1903   0.02356   0.01425  -0.0955   0.8183   0.0737
  -5.750  -0.1660   0.02295   0.01357  -0.0948   0.8114   0.0780
  -5.500  -0.1372   0.02227   0.01283  -0.0950   0.8064   0.0853
  -5.250  -0.1208   0.02188   0.01245  -0.0930   0.7974   0.0935
  -5.000  -0.0966   0.02131   0.01195  -0.0924   0.7907   0.1061
  -4.750  -0.0672   0.02080   0.01148  -0.0926   0.7858   0.1245
  -4.500  -0.0498   0.02067   0.01143  -0.0907   0.7769   0.1404
  -4.250  -0.0233   0.02050   0.01128  -0.0902   0.7704   0.1591
  -4.000   0.0081   0.02036   0.01102  -0.0906   0.7654   0.1798
  -3.750   0.0264   0.02044   0.01110  -0.0888   0.7565   0.1956
  -3.500   0.0525   0.02040   0.01101  -0.0883   0.7499   0.2128
  -3.250   0.0811   0.02026   0.01084  -0.0881   0.7440   0.2285
  -3.000   0.1005   0.02020   0.01075  -0.0864   0.7336   0.2405
  -2.750   0.1312   0.01990   0.01036  -0.0864   0.7256   0.2532
  -2.500   0.1506   0.01975   0.01019  -0.0845   0.7136   0.2619
  -2.250   0.1808   0.01943   0.00979  -0.0845   0.7054   0.2720
  -2.000   0.2005   0.01936   0.00970  -0.0828   0.6950   0.2808
  -1.750   0.2280   0.01911   0.00945  -0.0824   0.6877   0.2925
  -1.500   0.2500   0.01901   0.00937  -0.0811   0.6786   0.3044
  -1.250   0.2755   0.01883   0.00918  -0.0804   0.6704   0.3176
  -1.000   0.2999   0.01865   0.00904  -0.0795   0.6620   0.3290
  -0.750   0.3237   0.01852   0.00890  -0.0784   0.6527   0.3420
  -0.500   0.3492   0.01832   0.00875  -0.0777   0.6443   0.3570
  -0.250   0.3714   0.01819   0.00869  -0.0764   0.6343   0.3756
   0.000   0.3968   0.01799   0.00855  -0.0756   0.6253   0.4042
   0.250   0.4184   0.01782   0.00854  -0.0743   0.6148   0.4465
   0.500   0.4423   0.01754   0.00847  -0.0732   0.6050   0.5129
   0.750   0.4624   0.01718   0.00850  -0.0713   0.5942   0.6127
   1.000   0.5019   0.01686   0.00874  -0.0725   0.5819   0.8029
   1.250   0.5721   0.01694   0.00882  -0.0801   0.5670   0.9124
   1.500   0.6211   0.01708   0.00880  -0.0839   0.5526   0.9535
   1.750   0.6624   0.01727   0.00887  -0.0865   0.5369   0.9806
   2.000   0.7071   0.01746   0.00891  -0.0900   0.5201   1.0000
   2.250   0.7215   0.01763   0.00895  -0.0874   0.5063   1.0000
   2.500   0.7360   0.01781   0.00899  -0.0849   0.4924   1.0000
   2.750   0.7503   0.01801   0.00904  -0.0823   0.4781   1.0000
   3.000   0.7639   0.01825   0.00917  -0.0796   0.4636   1.0000
   3.250   0.7778   0.01851   0.00931  -0.0770   0.4498   1.0000
   3.500   0.7915   0.01880   0.00945  -0.0744   0.4365   1.0000
   3.750   0.8051   0.01910   0.00961  -0.0717   0.4239   1.0000
   4.000   0.8184   0.01943   0.00984  -0.0691   0.4114   1.0000
   4.250   0.8320   0.01978   0.01006  -0.0665   0.4005   1.0000
   4.500   0.8455   0.02015   0.01030  -0.0639   0.3902   1.0000
   4.750   0.8598   0.02053   0.01059  -0.0615   0.3812   1.0000
   5.000   0.8735   0.02092   0.01087  -0.0590   0.3732   1.0000
   5.250   0.8880   0.02131   0.01118  -0.0567   0.3661   1.0000
   5.500   0.9027   0.02172   0.01153  -0.0544   0.3591   1.0000
   5.750   0.9184   0.02215   0.01184  -0.0524   0.3530   1.0000
   6.000   0.9346   0.02260   0.01224  -0.0505   0.3469   1.0000
   6.250   0.9506   0.02305   0.01266  -0.0487   0.3409   1.0000
   6.500   0.9681   0.02352   0.01304  -0.0471   0.3357   1.0000
   6.750   0.9864   0.02401   0.01347  -0.0456   0.3309   1.0000
   7.000   1.0033   0.02451   0.01398  -0.0440   0.3259   1.0000
   7.250   1.0213   0.02502   0.01446  -0.0427   0.3215   1.0000
   7.500   1.0417   0.02553   0.01490  -0.0416   0.3177   1.0000
   7.750   1.0631   0.02606   0.01537  -0.0408   0.3141   1.0000
   8.000   1.0792   0.02664   0.01602  -0.0393   0.3102   1.0000
   8.250   1.0965   0.02722   0.01662  -0.0379   0.3062   1.0000
   8.500   1.1147   0.02780   0.01719  -0.0367   0.3025   1.0000
   8.750   1.1362   0.02835   0.01768  -0.0360   0.2993   1.0000
   9.000   1.1576   0.02897   0.01827  -0.0353   0.2963   1.0000
   9.250   1.1720   0.02968   0.01909  -0.0337   0.2933   1.0000
   9.500   1.1880   0.03040   0.01988  -0.0324   0.2903   1.0000
   9.750   1.2049   0.03111   0.02063  -0.0313   0.2875   1.0000
  10.000   1.2233   0.03179   0.02134  -0.0303   0.2848   1.0000
  10.250   1.2439   0.03243   0.02195  -0.0296   0.2822   1.0000
  10.500   1.2688   0.03305   0.02252  -0.0295   0.2796   1.0000
  10.750   1.2760   0.03405   0.02369  -0.0273   0.2772   1.0000
  11.000   1.2853   0.03507   0.02484  -0.0255   0.2746   1.0000
  11.250   1.2968   0.03608   0.02596  -0.0241   0.2722   1.0000
  11.500   1.3092   0.03706   0.02703  -0.0227   0.2699   1.0000
  11.750   1.3234   0.03799   0.02801  -0.0216   0.2677   1.0000
  12.000   1.3411   0.03879   0.02884  -0.0208   0.2654   1.0000
  12.250   1.3637   0.03946   0.02950  -0.0205   0.2634   1.0000
  12.500   1.3716   0.04074   0.03088  -0.0190   0.2613   1.0000
  12.750   1.3665   0.04257   0.03293  -0.0166   0.2591   1.0000
  13.000   1.3627   0.04450   0.03506  -0.0145   0.2568   1.0000
  13.250   1.3599   0.04643   0.03714  -0.0127   0.2543   1.0000
  13.500   1.3627   0.04808   0.03889  -0.0113   0.2517   1.0000
  13.750   1.3755   0.04908   0.03992  -0.0105   0.2490   1.0000
  14.000   1.4047   0.04904   0.03980  -0.0105   0.2462   1.0000
  14.250   1.3867   0.05219   0.04318  -0.0085   0.2439   1.0000
  14.500   1.3515   0.05700   0.04829  -0.0066   0.2414   1.0000
  14.750   1.3071   0.06339   0.05495  -0.0057   0.2385   1.0000
  15.000   1.1915   0.07952   0.07148  -0.0078   0.2340   1.0000
  15.250   1.2965   0.06923   0.06098  -0.0051   0.2323   1.0000
  15.500   1.3647   0.06441   0.05595  -0.0043   0.2293   1.0000
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