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GOE 746 AIRFOIL (goe746-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 746 AIRFOIL (goe746-il)
Reynolds number: 100,000
Max Cl/Cd: 49.14 at α=8.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe746-il-100000-n5.txt
Download as CSV file: xf-goe746-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 746 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3801   0.10460   0.09973   0.0119   0.6640   0.0406
  -8.000  -0.3838   0.10261   0.09780   0.0074   0.6582   0.0413
  -7.750  -0.3857   0.10028   0.09547   0.0038   0.6532   0.0415
  -7.500  -0.3805   0.09731   0.09243   0.0002   0.6490   0.0417
  -7.250  -0.3724   0.09250   0.08764  -0.0010   0.6433   0.0421
  -7.000  -0.3607   0.08779   0.08291   0.0020   0.6378   0.0434
  -6.750  -0.3512   0.08451   0.07957   0.0016   0.6335   0.0447
  -6.500  -0.3410   0.08131   0.07636  -0.0002   0.6281   0.0463
  -6.250  -0.3300   0.07817   0.07315  -0.0027   0.6235   0.0494
  -6.000  -0.3096   0.07588   0.07053  -0.0119   0.6202   0.0529
  -5.750  -0.3018   0.07086   0.06560  -0.0102   0.6159   0.0543
  -5.500  -0.2884   0.06770   0.06241  -0.0099   0.6109   0.0563
  -5.250  -0.2719   0.06465   0.05925  -0.0111   0.6067   0.0591
  -5.000  -0.2406   0.06261   0.05657  -0.0170   0.6036   0.0650
  -4.750  -0.2293   0.05763   0.05178  -0.0164   0.5989   0.0665
  -4.500  -0.2136   0.05503   0.04918  -0.0158   0.5945   0.0705
  -4.250  -0.1855   0.05234   0.04596  -0.0185   0.5911   0.0788
  -4.000  -0.1691   0.04900   0.04261  -0.0180   0.5880   0.0806
  -3.750  -0.1477   0.04642   0.03993  -0.0182   0.5832   0.0834
  -3.250  -0.0932   0.03938   0.03199  -0.0185   0.5760   0.0629
  -3.000  -0.0662   0.03559   0.02753  -0.0176   0.5734   0.0521
  -2.750  -0.0418   0.03333   0.02505  -0.0174   0.5695   0.0510
  -2.500  -0.0153   0.03150   0.02275  -0.0168   0.5654   0.0520
  -2.250   0.0108   0.02987   0.02071  -0.0162   0.5617   0.0523
  -2.000   0.0366   0.02822   0.01875  -0.0157   0.5586   0.0517
  -1.750   0.0636   0.02685   0.01709  -0.0154   0.5549   0.0513
  -1.500   0.0912   0.02569   0.01566  -0.0151   0.5509   0.0512
  -1.250   0.1189   0.02467   0.01436  -0.0148   0.5473   0.0512
  -1.000   0.1467   0.02399   0.01336  -0.0143   0.5441   0.0525
  -0.750   0.1743   0.02311   0.01231  -0.0141   0.5409   0.0540
  -0.500   0.2027   0.02244   0.01156  -0.0142   0.5365   0.0542
  -0.250   0.2307   0.02184   0.01088  -0.0141   0.5329   0.0544
   0.000   0.2582   0.02130   0.01026  -0.0138   0.5297   0.0549
   0.250   0.2854   0.02082   0.00970  -0.0135   0.5270   0.0556
   0.500   0.3128   0.02054   0.00948  -0.0135   0.5225   0.0566
   0.750   0.3400   0.02030   0.00924  -0.0134   0.5186   0.0579
   1.000   0.3681   0.02011   0.00898  -0.0133   0.5153   0.0599
   1.250   0.3964   0.02000   0.00874  -0.0131   0.5124   0.0644
   1.500   0.4249   0.01996   0.00871  -0.0134   0.5083   0.0693
   1.750   0.4528   0.02000   0.00873  -0.0135   0.5040   0.0743
   2.000   0.4798   0.01995   0.00866  -0.0133   0.5004   0.0845
   2.500   0.6059   0.01824   0.00891  -0.0279   0.4911   1.0000
   2.750   0.6311   0.01848   0.00908  -0.0275   0.4868   1.0000
   3.000   0.6561   0.01863   0.00913  -0.0269   0.4833   1.0000
   3.250   0.6811   0.01882   0.00924  -0.0263   0.4797   1.0000
   3.500   0.7060   0.01918   0.00966  -0.0262   0.4738   1.0000
   3.750   0.7309   0.01933   0.00976  -0.0256   0.4694   1.0000
   4.000   0.7556   0.01938   0.00970  -0.0249   0.4660   1.0000
   4.250   0.7802   0.01982   0.01026  -0.0248   0.4595   1.0000
   4.500   0.8048   0.02000   0.01045  -0.0243   0.4548   1.0000
   4.750   0.8296   0.02006   0.01044  -0.0235   0.4514   1.0000
   5.000   0.8535   0.02053   0.01105  -0.0234   0.4451   1.0000
   5.250   0.8778   0.02074   0.01129  -0.0229   0.4401   1.0000
   5.500   0.9026   0.02079   0.01132  -0.0222   0.4365   1.0000
   5.750   0.9259   0.02131   0.01201  -0.0220   0.4298   1.0000
   6.000   0.9500   0.02150   0.01226  -0.0215   0.4248   1.0000
   6.250   0.9746   0.02155   0.01231  -0.0208   0.4209   1.0000
   6.500   0.9969   0.02214   0.01311  -0.0206   0.4134   1.0000
   6.750   1.0211   0.02224   0.01325  -0.0199   0.4085   1.0000
   7.000   1.0437   0.02267   0.01383  -0.0195   0.4022   1.0000
   7.250   1.0665   0.02300   0.01430  -0.0190   0.3960   1.0000
   7.500   1.0907   0.02308   0.01442  -0.0183   0.3914   1.0000
   7.750   1.1112   0.02373   0.01530  -0.0179   0.3832   1.0000
   8.000   1.1348   0.02372   0.01536  -0.0171   0.3762   1.0000
   8.250   1.1560   0.02387   0.01564  -0.0164   0.3642   1.0000
   8.500   1.1764   0.02394   0.01576  -0.0156   0.3481   1.0000
   8.750   1.1937   0.02446   0.01639  -0.0149   0.3295   1.0000
   9.000   1.2105   0.02505   0.01707  -0.0141   0.3132   1.0000
   9.250   1.2236   0.02582   0.01783  -0.0131   0.2915   1.0000
   9.500   1.2305   0.02716   0.01913  -0.0121   0.2661   1.0000
   9.750   1.2323   0.02889   0.02082  -0.0110   0.2460   1.0000
  10.000   1.2252   0.03130   0.02322  -0.0099   0.2302   1.0000
  10.250   1.2125   0.03428   0.02614  -0.0089   0.2131   1.0000
  10.500   1.2018   0.03747   0.02929  -0.0085   0.1957   1.0000
  10.750   1.1896   0.04105   0.03279  -0.0083   0.1756   1.0000
  11.250   1.1574   0.04943   0.04084  -0.0086   0.1103   1.0000
  11.500   1.1363   0.05438   0.04553  -0.0091   0.0846   1.0000
  11.750   1.1141   0.05963   0.05054  -0.0097   0.0487   1.0000
  12.000   1.0990   0.06435   0.05515  -0.0104   0.0390   1.0000
  12.250   1.0900   0.06859   0.05940  -0.0111   0.0349   1.0000
  12.500   1.0828   0.07274   0.06363  -0.0119   0.0320   1.0000
  12.750   1.0776   0.07675   0.06777  -0.0127   0.0306   1.0000
  13.000   1.0714   0.08105   0.07221  -0.0137   0.0293   1.0000
  13.250   1.0664   0.08525   0.07654  -0.0148   0.0287   1.0000
  13.500   1.0584   0.09005   0.08148  -0.0161   0.0277   1.0000
  13.750   1.0506   0.09491   0.08648  -0.0176   0.0269   1.0000
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