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GOE 573 AIRFOIL (goe573-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 573 AIRFOIL (goe573-il)
Reynolds number: 200,000
Max Cl/Cd: 64.7 at α=10°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe573-il-200000.txt
Download as CSV file: xf-goe573-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 573 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.2069   0.12490   0.12172  -0.0397   1.0000   0.0339
 -10.750  -0.2059   0.12245   0.11933  -0.0395   1.0000   0.0349
 -10.500  -0.2069   0.12029   0.11725  -0.0390   1.0000   0.0354
 -10.250  -0.1893   0.11598   0.11294  -0.0471   0.9953   0.0378
 -10.000  -0.1779   0.11206   0.10903  -0.0575   0.9865   0.0382
  -9.750  -0.1594   0.10596   0.10294  -0.0605   0.9755   0.0388
  -9.500  -0.1419   0.10193   0.09892  -0.0608   0.9465   0.0394
  -9.250  -0.1163   0.09745   0.09439  -0.0649   0.9274   0.0405
  -9.000  -0.0851   0.09246   0.08933  -0.0726   0.9131   0.0422
  -8.750  -0.0476   0.08670   0.08345  -0.0850   0.8980   0.0451
  -8.500  -0.0113   0.07954   0.07607  -0.1136   0.8709   0.0467
  -8.250   0.0443   0.07360   0.07000  -0.1134   0.8538   0.0491
  -8.000   0.0744   0.06976   0.06594  -0.1203   0.8223   0.0510
  -7.750   0.0820   0.06684   0.06285  -0.1235   0.7942   0.0531
  -7.500   0.0773   0.06454   0.06042  -0.1240   0.7710   0.0544
  -7.250   0.0675   0.06234   0.05804  -0.1264   0.7530   0.0564
  -7.000   0.0589   0.06060   0.05596  -0.1270   0.7379   0.0571
  -6.750   0.0637   0.05581   0.05116  -0.1260   0.7249   0.0580
  -6.500   0.0755   0.05352   0.04885  -0.1243   0.7119   0.0591
  -6.000   0.0947   0.04987   0.04500  -0.1217   0.6882   0.0633
  -5.750   0.0985   0.04948   0.04397  -0.1204   0.6790   0.0695
  -5.500   0.1050   0.04460   0.03908  -0.1194   0.6701   0.0708
  -5.250   0.1182   0.04246   0.03695  -0.1181   0.6600   0.0722
  -5.000   0.1327   0.04082   0.03519  -0.1169   0.6514   0.0745
  -4.750   0.1458   0.03924   0.03346  -0.1151   0.6419   0.0790
  -4.500   0.1558   0.03710   0.03089  -0.1129   0.6349   0.0855
  -4.250   0.1713   0.03550   0.02931  -0.1115   0.6256   0.0884
  -3.750   0.2008   0.03254   0.02584  -0.1075   0.6106   0.1012
  -3.500   0.2199   0.03116   0.02434  -0.1065   0.6040   0.1054
  -3.250   0.2343   0.03010   0.02298  -0.1039   0.5967   0.1164
  -3.000   0.2540   0.02871   0.02154  -0.1029   0.5904   0.1218
  -2.750   0.2712   0.02761   0.02025  -0.1012   0.5842   0.1344
  -2.500   0.2891   0.02665   0.01912  -0.0994   0.5780   0.1486
  -2.250   0.3093   0.02570   0.01796  -0.0982   0.5731   0.1639
  -2.000   0.3434   0.02196   0.01321  -0.0952   0.5682   0.0779
  -1.750   0.3676   0.02087   0.01186  -0.0941   0.5625   0.0759
  -1.500   0.3954   0.01982   0.01042  -0.0935   0.5578   0.0728
  -1.250   0.4213   0.01915   0.00961  -0.0928   0.5526   0.0718
  -1.000   0.4476   0.01855   0.00891  -0.0923   0.5476   0.0719
  -0.750   0.4752   0.01805   0.00832  -0.0922   0.5434   0.0730
  -0.500   0.5020   0.01779   0.00802  -0.0920   0.5396   0.0760
  -0.250   0.5257   0.01753   0.00778  -0.0911   0.5351   0.0790
   0.000   0.5505   0.01727   0.00749  -0.0904   0.5311   0.0813
   0.250   0.5757   0.01703   0.00719  -0.0899   0.5277   0.0842
   0.500   0.5997   0.01684   0.00701  -0.0891   0.5244   0.0904
   0.750   0.6205   0.01675   0.00698  -0.0877   0.5204   0.1008
   1.000   0.8371   0.01505   0.00715  -0.1285   0.5127   1.0000
   1.250   0.8626   0.01528   0.00723  -0.1282   0.5101   1.0000
   1.500   0.8839   0.01550   0.00744  -0.1270   0.5070   1.0000
   1.750   0.9055   0.01571   0.00764  -0.1259   0.5037   1.0000
   2.000   0.9282   0.01591   0.00778  -0.1250   0.5005   1.0000
   2.250   0.9522   0.01612   0.00792  -0.1244   0.4977   1.0000
   2.500   0.9776   0.01637   0.00807  -0.1241   0.4953   1.0000
   2.750   1.0006   0.01669   0.00836  -0.1233   0.4929   1.0000
   3.000   1.0204   0.01697   0.00870  -0.1219   0.4900   1.0000
   3.250   1.0415   0.01723   0.00898  -0.1208   0.4870   1.0000
   3.500   1.0640   0.01748   0.00921  -0.1199   0.4842   1.0000
   3.750   1.0881   0.01774   0.00943  -0.1194   0.4818   1.0000
   4.000   1.1141   0.01804   0.00966  -0.1192   0.4795   1.0000
   4.250   1.1346   0.01840   0.01006  -0.1180   0.4769   1.0000
   4.500   1.1523   0.01873   0.01048  -0.1163   0.4738   1.0000
   4.750   1.1722   0.01900   0.01079  -0.1149   0.4703   1.0000
   5.000   1.1949   0.01919   0.01096  -0.1141   0.4671   1.0000
   5.250   1.2218   0.01942   0.01110  -0.1141   0.4640   1.0000
   5.500   1.2404   0.01980   0.01156  -0.1126   0.4611   1.0000
   5.750   1.2564   0.02018   0.01206  -0.1106   0.4579   1.0000
   6.000   1.2754   0.02052   0.01246  -0.1091   0.4550   1.0000
   6.250   1.2968   0.02080   0.01277  -0.1082   0.4522   1.0000
   6.500   1.3218   0.02108   0.01304  -0.1079   0.4498   1.0000
   6.750   1.3474   0.02149   0.01343  -0.1078   0.4472   1.0000
   7.000   1.3582   0.02196   0.01408  -0.1048   0.4441   1.0000
   7.250   1.3732   0.02238   0.01462  -0.1027   0.4409   1.0000
   7.500   1.3920   0.02274   0.01507  -0.1013   0.4381   1.0000
   7.750   1.4146   0.02303   0.01538  -0.1006   0.4354   1.0000
   8.000   1.4437   0.02323   0.01551  -0.1011   0.4317   1.0000
   8.250   1.4467   0.02360   0.01609  -0.0967   0.4269   1.0000
   8.500   1.4631   0.02358   0.01612  -0.0946   0.4215   1.0000
   8.750   1.4920   0.02340   0.01583  -0.0949   0.4159   1.0000
   9.000   1.4931   0.02376   0.01640  -0.0901   0.4111   1.0000
   9.250   1.5081   0.02369   0.01635  -0.0878   0.4055   1.0000
   9.500   1.5307   0.02367   0.01630  -0.0870   0.4003   1.0000
   9.750   1.5268   0.02392   0.01675  -0.0812   0.3946   1.0000
  10.000   1.5411   0.02382   0.01664  -0.0788   0.3888   1.0000
  10.250   1.5463   0.02398   0.01688  -0.0748   0.3834   1.0000
  10.500   1.5381   0.02412   0.01714  -0.0682   0.3775   1.0000
  10.750   1.5471   0.02396   0.01694  -0.0648   0.3707   1.0000
  11.000   1.5344   0.02443   0.01762  -0.0581   0.3641   1.0000
  11.250   1.5346   0.02455   0.01772  -0.0537   0.3554   1.0000
  11.500   1.5247   0.02529   0.01863  -0.0484   0.3457   1.0000
  11.750   1.5168   0.02618   0.01961  -0.0439   0.3330   1.0000
  12.000   1.5070   0.02750   0.02097  -0.0398   0.3170   1.0000
  12.250   1.4932   0.02946   0.02290  -0.0360   0.2956   1.0000
  12.500   1.4725   0.03234   0.02568  -0.0325   0.2709   1.0000
  12.750   1.4503   0.03590   0.02915  -0.0297   0.2479   1.0000
  13.000   1.4271   0.03994   0.03313  -0.0275   0.2296   1.0000
  13.250   1.4011   0.04460   0.03773  -0.0257   0.2094   1.0000
  13.500   1.3725   0.04984   0.04291  -0.0244   0.1884   1.0000
  13.750   1.3490   0.05483   0.04786  -0.0236   0.1659   1.0000
  14.000   1.3217   0.06046   0.05341  -0.0230   0.1413   1.0000
  14.250   1.2927   0.06653   0.05937  -0.0228   0.1186   1.0000
  14.500   1.2626   0.07292   0.06565  -0.0228   0.0939   1.0000
  14.750   1.2373   0.07893   0.07156  -0.0229   0.0691   1.0000
  15.000   1.2153   0.08470   0.07727  -0.0232   0.0550   1.0000
  15.250   1.1969   0.09018   0.08274  -0.0237   0.0467   1.0000
  15.500   1.1859   0.09477   0.08740  -0.0241   0.0426   1.0000
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