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GOE 518 AIRFOIL (goe518-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 518 AIRFOIL (goe518-il)
Reynolds number: 200,000
Max Cl/Cd: 54.07 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe518-il-200000.txt
Download as CSV file: xf-goe518-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 518 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000   0.0291   0.10397   0.10042  -0.0975   0.9312   0.0576
  -9.750   0.0455   0.09989   0.09632  -0.1024   0.9282   0.0600
  -9.500   0.0455   0.09432   0.09075  -0.1112   0.9253   0.0620
  -9.250   0.0565   0.09237   0.08883  -0.1083   0.9168   0.0627
  -9.000   0.0795   0.08913   0.08558  -0.1108   0.9134   0.0642
  -8.750   0.0971   0.08520   0.08164  -0.1156   0.9109   0.0668
  -8.500   0.0524   0.08050   0.07697  -0.1233   0.8967   0.0690
  -8.250   0.0774   0.07608   0.07255  -0.1255   0.8949   0.0698
  -8.000   0.1157   0.07344   0.06990  -0.1262   0.8941   0.0712
  -7.750   0.1104   0.07123   0.06771  -0.1250   0.8838   0.0724
  -7.500   0.1166   0.06740   0.06384  -0.1284   0.8786   0.0746
  -6.750   0.1229   0.05699   0.05321  -0.1311   0.8553   0.0809
  -6.500   0.1299   0.05454   0.05068  -0.1303   0.8461   0.0839
  -6.250   0.1430   0.04962   0.04542  -0.1337   0.8417   0.0890
  -6.000   0.1424   0.04826   0.04408  -0.1291   0.8289   0.0899
  -5.750   0.1783   0.04545   0.04115  -0.1325   0.8248   0.0939
  -5.500   0.1583   0.04362   0.03886  -0.1257   0.8104   0.0995
  -5.250   0.1818   0.04115   0.03646  -0.1258   0.8017   0.1010
  -5.000   0.2045   0.03927   0.03452  -0.1256   0.7919   0.1039
  -4.750   0.1992   0.03840   0.03312  -0.1199   0.7783   0.1121
  -4.500   0.2299   0.03546   0.03025  -0.1215   0.7689   0.1143
  -4.250   0.2462   0.03404   0.02876  -0.1196   0.7555   0.1175
  -4.000   0.2479   0.03312   0.02745  -0.1146   0.7406   0.1272
  -3.750   0.2652   0.03130   0.02564  -0.1131   0.7266   0.1299
  -3.500   0.2835   0.03012   0.02432  -0.1113   0.7123   0.1349
  -3.250   0.2974   0.02878   0.02265  -0.1087   0.6981   0.1447
  -3.000   0.3091   0.02212   0.01421  -0.1008   0.6878   0.0690
  -2.750   0.3316   0.02101   0.01290  -0.0994   0.6727   0.0685
  -2.500   0.3548   0.02027   0.01189  -0.0981   0.6573   0.0687
  -2.250   0.3779   0.01964   0.01101  -0.0968   0.6417   0.0689
  -2.000   0.4012   0.01907   0.01021  -0.0955   0.6261   0.0690
  -1.750   0.4239   0.01862   0.00955  -0.0942   0.6106   0.0691
  -1.500   0.4393   0.01817   0.00902  -0.0915   0.5949   0.0696
  -1.250   0.4549   0.01782   0.00861  -0.0888   0.5797   0.0703
  -1.000   0.4708   0.01760   0.00832  -0.0863   0.5653   0.0713
  -0.750   0.4873   0.01745   0.00809  -0.0839   0.5516   0.0728
  -0.500   0.5013   0.01739   0.00794  -0.0810   0.5377   0.0751
  -0.250   0.5147   0.01735   0.00782  -0.0780   0.5246   0.0772
   0.000   0.5296   0.01726   0.00770  -0.0754   0.5128   0.0801
   0.250   0.5450   0.01728   0.00763  -0.0728   0.5014   0.0828
   0.500   0.5596   0.01731   0.00761  -0.0701   0.4904   0.0869
   1.000   0.5924   0.01735   0.00760  -0.0656   0.4717   0.1079
   1.250   0.6013   0.01651   0.00759  -0.0622   0.4648   0.3655
   1.500   0.8829   0.01727   0.00928  -0.1148   0.4420   1.0000
   1.750   0.8957   0.01747   0.00942  -0.1120   0.4363   1.0000
   2.000   0.9129   0.01772   0.00955  -0.1101   0.4310   1.0000
   2.250   0.9382   0.01807   0.00972  -0.1098   0.4260   1.0000
   2.500   0.9496   0.01827   0.00992  -0.1067   0.4216   1.0000
   2.750   0.9645   0.01851   0.01009  -0.1044   0.4169   1.0000
   3.000   0.9839   0.01878   0.01026  -0.1030   0.4128   1.0000
   3.250   1.0160   0.01921   0.01051  -0.1041   0.4086   1.0000
   3.500   1.0270   0.01944   0.01077  -0.1010   0.4053   1.0000
   3.750   1.0425   0.01970   0.01102  -0.0989   0.4019   1.0000
   4.000   1.0614   0.01999   0.01126  -0.0974   0.3987   1.0000
   4.250   1.0828   0.02030   0.01150  -0.0964   0.3956   1.0000
   4.500   1.1128   0.02071   0.01179  -0.0972   0.3926   1.0000
   4.750   1.1387   0.02115   0.01218  -0.0972   0.3898   1.0000
   5.000   1.1507   0.02144   0.01253  -0.0944   0.3873   1.0000
   5.250   1.1658   0.02177   0.01287  -0.0922   0.3846   1.0000
   5.500   1.1837   0.02210   0.01320  -0.0907   0.3820   1.0000
   5.750   1.2039   0.02244   0.01350  -0.0895   0.3793   1.0000
   6.000   1.2283   0.02282   0.01382  -0.0893   0.3768   1.0000
   6.250   1.2626   0.02335   0.01426  -0.0910   0.3744   1.0000
   6.500   1.2867   0.02389   0.01481  -0.0908   0.3723   1.0000
   6.750   1.2961   0.02427   0.01527  -0.0877   0.3705   1.0000
   7.000   1.3087   0.02470   0.01577  -0.0852   0.3685   1.0000
   7.250   1.3237   0.02515   0.01626  -0.0833   0.3665   1.0000
   7.500   1.3409   0.02561   0.01675  -0.0818   0.3645   1.0000
   7.750   1.3600   0.02607   0.01723  -0.0807   0.3625   1.0000
   8.000   1.3819   0.02651   0.01766  -0.0801   0.3606   1.0000
   8.250   1.4098   0.02698   0.01808  -0.0806   0.3585   1.0000
   8.500   1.4473   0.02771   0.01876  -0.0831   0.3564   1.0000
   8.750   1.4614   0.02837   0.01950  -0.0813   0.3549   1.0000
   9.000   1.4666   0.02895   0.02020  -0.0777   0.3535   1.0000
   9.250   1.4736   0.02960   0.02095  -0.0746   0.3519   1.0000
   9.500   1.4815   0.03029   0.02175  -0.0718   0.3503   1.0000
   9.750   1.4902   0.03098   0.02254  -0.0692   0.3485   1.0000
  10.000   1.4996   0.03159   0.02321  -0.0667   0.3463   1.0000
  10.250   1.5140   0.03215   0.02380  -0.0651   0.3443   1.0000
  10.500   1.5374   0.03253   0.02417  -0.0650   0.3420   1.0000
  10.750   1.5720   0.03302   0.02460  -0.0668   0.3398   1.0000
  11.000   1.5872   0.03397   0.02560  -0.0656   0.3378   1.0000
  11.250   1.5751   0.03493   0.02675  -0.0599   0.3359   1.0000
  11.500   1.5682   0.03598   0.02796  -0.0554   0.3338   1.0000
  11.750   1.5655   0.03699   0.02908  -0.0518   0.3313   1.0000
  12.000   1.5684   0.03796   0.03015  -0.0490   0.3292   1.0000
  12.250   1.5788   0.03866   0.03089  -0.0473   0.3269   1.0000
  12.500   1.6035   0.03891   0.03112  -0.0475   0.3246   1.0000
  12.750   1.6465   0.03901   0.03113  -0.0502   0.3223   1.0000
  13.000   1.6366   0.04059   0.03287  -0.0460   0.3204   1.0000
  13.250   1.6054   0.04293   0.03546  -0.0397   0.3184   1.0000
  13.500   1.5780   0.04558   0.03831  -0.0346   0.3161   1.0000
  13.750   1.5575   0.04813   0.04102  -0.0307   0.3135   1.0000
  14.000   1.5521   0.05000   0.04300  -0.0284   0.3111   1.0000
  14.250   1.5697   0.05049   0.04351  -0.0280   0.3089   1.0000
  14.500   1.6068   0.04994   0.04291  -0.0291   0.3070   1.0000
  14.750   1.6638   0.04891   0.04179  -0.0323   0.3049   1.0000
  15.000   0.9865   0.12904   0.12303  -0.0245   0.2577   1.0000
  16.000   1.4615   0.07394   0.06770  -0.0160   0.2888   1.0000
  16.250   0.9536   0.14993   0.14413  -0.0303   0.2213   1.0000
  16.500   0.9722   0.14995   0.14417  -0.0302   0.2193   1.0000
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