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GOE 458 AIRFOIL (goe458-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 458 AIRFOIL (goe458-il)
Reynolds number: 100,000
Max Cl/Cd: 65.09 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe458-il-100000.txt
Download as CSV file: xf-goe458-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 458 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
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.3365   0.09777   0.09352  -0.0269   1.0000   0.0700
  -7.000  -0.3541   0.09740   0.09326  -0.0242   1.0000   0.0707
  -6.750  -0.3685   0.09689   0.09286  -0.0243   1.0000   0.0714
  -6.500  -0.3775   0.09609   0.09213  -0.0271   1.0000   0.0719
  -6.250  -0.3798   0.09351   0.08962  -0.0292   1.0000   0.0725
  -6.000  -0.3786   0.08904   0.08519  -0.0205   1.0000   0.0746
  -5.750  -0.3789   0.08679   0.08298  -0.0187   1.0000   0.0768
  -5.500  -0.3791   0.08458   0.08081  -0.0187   1.0000   0.0796
  -5.000  -0.3645   0.07885   0.07509  -0.0293   1.0000   0.0860
  -4.750  -0.3584   0.07578   0.07202  -0.0257   0.9983   0.0888
  -4.500  -0.3039   0.07020   0.06625  -0.0420   0.9904   0.0991
  -4.250  -0.2799   0.06650   0.06256  -0.0424   0.9845   0.1043
  -4.000  -0.2380   0.06176   0.05769  -0.0516   0.9768   0.1150
  -3.750  -0.1968   0.05768   0.05350  -0.0584   0.9705   0.1302
  -3.500  -0.1591   0.05386   0.04955  -0.0643   0.9623   0.1438
  -3.250  -0.1118   0.04963   0.04512  -0.0718   0.9567   0.1575
  -3.000  -0.0705   0.04581   0.04102  -0.0778   0.9483   0.1692
  -2.750   0.0097   0.03137   0.02484  -0.0907   0.9481   0.0654
  -2.500   0.0582   0.02739   0.01966  -0.0940   0.9443   0.0581
  -2.250   0.0957   0.02531   0.01702  -0.0955   0.9373   0.0584
  -2.000   0.1363   0.02361   0.01511  -0.0979   0.9315   0.0664
  -1.750   0.1724   0.02247   0.01373  -0.0990   0.9238   0.0718
  -1.500   0.2130   0.02137   0.01274  -0.1011   0.9176   0.0936
  -1.250   0.2470   0.02112   0.01281  -0.1023   0.9085   0.2418
  -1.000   0.2882   0.02128   0.01300  -0.1052   0.9025   0.3209
  -0.750   0.3178   0.02105   0.01270  -0.1056   0.8924   0.3444
  -0.500   0.3638   0.02044   0.01212  -0.1089   0.8886   0.3754
  -0.250   0.3930   0.02010   0.01191  -0.1093   0.8787   0.4241
   0.000   0.4499   0.01838   0.01130  -0.1145   0.8764   1.0000
   0.250   0.4792   0.01859   0.01126  -0.1147   0.8666   1.0000
   0.500   0.5222   0.01848   0.01094  -0.1173   0.8620   1.0000
   0.750   0.5478   0.01875   0.01108  -0.1170   0.8517   1.0000
   1.000   0.5899   0.01858   0.01079  -0.1193   0.8476   1.0000
   1.250   0.6131   0.01891   0.01105  -0.1186   0.8370   1.0000
   1.500   0.6407   0.01914   0.01123  -0.1185   0.8284   1.0000
   1.750   0.6755   0.01911   0.01117  -0.1195   0.8223   1.0000
   2.000   0.7000   0.01941   0.01145  -0.1190   0.8126   1.0000
   2.250   0.7402   0.01899   0.01101  -0.1203   0.8069   1.0000
   2.500   0.7667   0.01894   0.01097  -0.1196   0.7950   1.0000
   2.750   0.7963   0.01863   0.01071  -0.1189   0.7827   1.0000
   3.000   0.8258   0.01831   0.01040  -0.1182   0.7701   1.0000
   3.250   0.8540   0.01814   0.01027  -0.1175   0.7583   1.0000
   3.500   0.8828   0.01808   0.01026  -0.1172   0.7486   1.0000
   3.750   0.9128   0.01797   0.01028  -0.1169   0.7392   1.0000
   4.000   0.9373   0.01811   0.01053  -0.1160   0.7276   1.0000
   4.250   0.9628   0.01819   0.01074  -0.1151   0.7160   1.0000
   4.500   0.9903   0.01799   0.01064  -0.1142   0.7016   1.0000
   4.750   1.0184   0.01697   0.00954  -0.1118   0.6697   1.0000
   5.000   1.0395   0.01665   0.00931  -0.1092   0.6371   1.0000
   5.250   1.0579   0.01637   0.00888  -0.1059   0.5886   1.0000
   5.500   1.0721   0.01647   0.00890  -0.1023   0.5309   1.0000
   5.750   1.0813   0.01697   0.00902  -0.0981   0.4289   1.0000
   6.000   1.0773   0.01902   0.00979  -0.0927   0.2579   1.0000
   6.250   1.0773   0.02138   0.01112  -0.0887   0.1004   1.0000
   6.500   1.0819   0.02345   0.01270  -0.0851   0.0538   1.0000
   6.750   1.0965   0.02462   0.01403  -0.0826   0.0486   1.0000
   7.000   1.1091   0.02592   0.01557  -0.0800   0.0457   1.0000
   7.250   1.1174   0.02747   0.01728  -0.0769   0.0438   1.0000
   7.500   1.1213   0.02917   0.01910  -0.0732   0.0419   1.0000
   7.750   1.1304   0.03059   0.02065  -0.0703   0.0398   1.0000
   8.000   1.1416   0.03229   0.02243  -0.0677   0.0389   1.0000
   8.250   1.1651   0.03440   0.02454  -0.0666   0.0390   1.0000
   8.500   1.2133   0.03757   0.02774  -0.0688   0.0401   1.0000
   8.750   1.2732   0.04309   0.03330  -0.0727   0.0426   1.0000
   9.000   1.2909   0.04367   0.03455  -0.0694   0.0461   1.0000
   9.250   1.3150   0.04789   0.03934  -0.0679   0.0507   1.0000
   9.500   1.3450   0.05480   0.04645  -0.0684   0.0538   1.0000
   9.750   1.3400   0.05508   0.04772  -0.0621   0.0594   1.0000
  10.000   1.3474   0.05989   0.05320  -0.0587   0.0692   1.0000
  10.250   1.3470   0.06817   0.06222  -0.0554   0.0877   1.0000
  10.500   1.3190   0.07360   0.06833  -0.0505   0.0991   1.0000
  10.750   1.2176   0.06647   0.06144  -0.0388   0.0818   1.0000
  11.000   1.1873   0.07095   0.06617  -0.0359   0.0827   1.0000
  11.250   1.1566   0.07580   0.07123  -0.0343   0.0828   1.0000
  11.500   1.1247   0.08120   0.07682  -0.0339   0.0826   1.0000
  11.750   1.0927   0.08707   0.08285  -0.0346   0.0821   1.0000
  12.000   1.0614   0.09323   0.08915  -0.0364   0.0813   1.0000
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