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GOE 403 AIRFOIL (goe403-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 403 AIRFOIL (goe403-il)
Reynolds number: 100,000
Max Cl/Cd: 59.26 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe403-il-100000.txt
Download as CSV file: xf-goe403-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 403 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3444   0.10009   0.09535  -0.0271   1.0000   0.0638
  -7.750  -0.3524   0.09923   0.09462  -0.0284   1.0000   0.0644
  -7.500  -0.3561   0.09798   0.09347  -0.0321   1.0000   0.0647
  -7.250  -0.3534   0.09603   0.09158  -0.0371   1.0000   0.0650
  -7.000  -0.3386   0.08838   0.08393  -0.0253   1.0000   0.0703
  -6.750  -0.3370   0.08596   0.08158  -0.0259   1.0000   0.0733
  -6.500  -0.3368   0.08399   0.07970  -0.0287   1.0000   0.0763
  -6.250  -0.3328   0.08307   0.07880  -0.0375   1.0000   0.0779
  -6.000  -0.3326   0.07884   0.07466  -0.0358   1.0000   0.0789
  -5.750  -0.3331   0.07551   0.07140  -0.0302   1.0000   0.0808
  -5.500  -0.3324   0.07315   0.06908  -0.0283   1.0000   0.0835
  -5.250  -0.3297   0.07083   0.06679  -0.0286   1.0000   0.0868
  -5.000  -0.3067   0.06831   0.06403  -0.0402   1.0000   0.0920
  -4.750  -0.3098   0.06460   0.06047  -0.0351   1.0000   0.0934
  -4.500  -0.3058   0.06204   0.05791  -0.0327   1.0000   0.0964
  -4.250  -0.2734   0.05879   0.05432  -0.0418   1.0000   0.1060
  -4.000  -0.2720   0.05555   0.05123  -0.0381   1.0000   0.1083
  -3.750  -0.2473   0.05261   0.04807  -0.0422   1.0000   0.1205
  -3.500  -0.2403   0.05015   0.04570  -0.0397   1.0000   0.1267
  -3.250  -0.1941   0.04599   0.04131  -0.0468   0.9945   0.1417
  -3.000  -0.1446   0.04196   0.03695  -0.0543   0.9872   0.1632
  -2.750  -0.1050   0.03900   0.03387  -0.0582   0.9802   0.1942
  -2.500  -0.0328   0.03121   0.02470  -0.0677   0.9752   0.1211
  -2.250   0.0170   0.02752   0.02042  -0.0720   0.9697   0.1119
  -2.000   0.0627   0.02472   0.01659  -0.0745   0.9614   0.1052
  -1.750   0.1100   0.02254   0.01406  -0.0783   0.9550   0.1080
  -1.500   0.1518   0.02157   0.01282  -0.0809   0.9445   0.1182
  -1.250   0.1936   0.02028   0.01140  -0.0834   0.9345   0.1260
  -1.000   0.2413   0.01906   0.01009  -0.0868   0.9267   0.1403
  -0.750   0.2853   0.01794   0.00903  -0.0895   0.9168   0.1744
  -0.500   0.3266   0.01697   0.00837  -0.0919   0.9059   0.2435
  -0.250   0.3861   0.01412   0.00751  -0.0974   0.9015   1.0000
   0.000   0.4264   0.01396   0.00699  -0.0991   0.8882   1.0000
   0.250   0.4643   0.01380   0.00662  -0.1004   0.8741   1.0000
   0.500   0.4972   0.01372   0.00637  -0.1007   0.8580   1.0000
   0.750   0.5271   0.01371   0.00622  -0.1003   0.8401   1.0000
   1.000   0.5564   0.01373   0.00611  -0.0999   0.8228   1.0000
   1.250   0.5849   0.01378   0.00604  -0.0993   0.8058   1.0000
   1.500   0.6103   0.01394   0.00612  -0.0983   0.7870   1.0000
   1.750   0.6357   0.01410   0.00620  -0.0974   0.7688   1.0000
   2.000   0.6615   0.01425   0.00627  -0.0965   0.7520   1.0000
   2.250   0.6875   0.01441   0.00635  -0.0957   0.7362   1.0000
   2.500   0.7126   0.01460   0.00655  -0.0948   0.7200   1.0000
   2.750   0.7378   0.01481   0.00674  -0.0940   0.7042   1.0000
   3.000   0.7633   0.01503   0.00695  -0.0933   0.6895   1.0000
   3.250   0.7889   0.01526   0.00719  -0.0926   0.6753   1.0000
   3.500   0.8146   0.01552   0.00746  -0.0919   0.6618   1.0000
   3.750   0.8393   0.01560   0.00757  -0.0907   0.6431   1.0000
   4.000   0.8618   0.01544   0.00728  -0.0886   0.6139   1.0000
   4.250   0.8836   0.01544   0.00717  -0.0866   0.5833   1.0000
   4.500   0.9064   0.01563   0.00736  -0.0852   0.5586   1.0000
   4.750   0.9265   0.01577   0.00745  -0.0831   0.5218   1.0000
   5.000   0.9452   0.01595   0.00762  -0.0808   0.4768   1.0000
   5.250   0.9615   0.01626   0.00775  -0.0781   0.4068   1.0000
   5.500   0.9717   0.01757   0.00815  -0.0750   0.2395   1.0000
   5.750   0.9741   0.02082   0.01005  -0.0718   0.0603   1.0000
   6.000   0.9918   0.02211   0.01145  -0.0700   0.0497   1.0000
   6.250   1.0085   0.02341   0.01296  -0.0681   0.0466   1.0000
   6.500   1.0245   0.02465   0.01442  -0.0661   0.0450   1.0000
   6.750   1.0384   0.02603   0.01596  -0.0637   0.0440   1.0000
   7.000   1.0516   0.02754   0.01762  -0.0613   0.0435   1.0000
   7.250   1.0679   0.02925   0.01934  -0.0592   0.0434   1.0000
   7.500   1.0917   0.03126   0.02133  -0.0580   0.0437   1.0000
   7.750   1.1191   0.03338   0.02350  -0.0574   0.0426   1.0000
   8.000   1.1469   0.03573   0.02597  -0.0568   0.0413   1.0000
   8.250   1.1775   0.03885   0.02934  -0.0563   0.0438   1.0000
   8.500   1.2071   0.04349   0.03415  -0.0561   0.0468   1.0000
   8.750   1.2285   0.04467   0.03602  -0.0534   0.0526   1.0000
   9.000   1.2591   0.04923   0.04093  -0.0525   0.0617   1.0000
   9.250   1.2842   0.05740   0.04988  -0.0505   0.0844   1.0000
   9.500   1.2789   0.06496   0.05933  -0.0448   0.1356   1.0000
   9.750   1.2384   0.06916   0.06423  -0.0408   0.1400   1.0000
  10.000   1.2046   0.07760   0.07307  -0.0400   0.1588   1.0000
  10.250   1.1741   0.08208   0.07768  -0.0383   0.1589   1.0000
  10.500   1.1431   0.08773   0.08341  -0.0389   0.1594   1.0000
  10.750   1.1133   0.09460   0.09033  -0.0416   0.1599   1.0000
  11.000   1.0824   0.10299   0.09873  -0.0464   0.1602   1.0000
  11.250   1.0483   0.11363   0.10933  -0.0539   0.1604   1.0000
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