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GOE 562 AIRFOIL (goe562-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 562 AIRFOIL (goe562-il)
Reynolds number: 1,000,000
Max Cl/Cd: 115.88 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe562-il-1000000-n5.txt
Download as CSV file: xf-goe562-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 562 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3443   0.01816   0.01311  -0.1174   0.6102   0.0168
  -9.000  -0.3291   0.01710   0.01182  -0.1153   0.6040   0.0173
  -8.750  -0.3059   0.01705   0.01174  -0.1143   0.5968   0.0176
  -8.500  -0.2805   0.01722   0.01191  -0.1137   0.5901   0.0178
  -8.250  -0.2575   0.01714   0.01177  -0.1127   0.5839   0.0180
  -8.000  -0.2332   0.01714   0.01175  -0.1119   0.5788   0.0183
  -7.750  -0.2104   0.01699   0.01154  -0.1109   0.5731   0.0186
  -7.250  -0.1639   0.01679   0.01123  -0.1090   0.5620   0.0194
  -7.000  -0.1452   0.01604   0.01030  -0.1073   0.5564   0.0201
  -6.500  -0.1035   0.01501   0.00899  -0.1045   0.5474   0.0210
  -6.250  -0.0814   0.01465   0.00851  -0.1033   0.5427   0.0212
  -6.000  -0.0621   0.01395   0.00767  -0.1017   0.5371   0.0217
  -5.750  -0.0386   0.01384   0.00754  -0.1007   0.5329   0.0221
  -5.500  -0.0154   0.01365   0.00729  -0.0997   0.5275   0.0223
  -5.250   0.0077   0.01348   0.00707  -0.0987   0.5228   0.0226
  -5.000   0.0308   0.01328   0.00680  -0.0977   0.5185   0.0229
  -4.750   0.0540   0.01299   0.00645  -0.0967   0.5144   0.0233
  -4.500   0.0773   0.01276   0.00615  -0.0957   0.5096   0.0238
  -4.250   0.0999   0.01242   0.00572  -0.0945   0.5052   0.0241
  -4.000   0.1232   0.01213   0.00535  -0.0935   0.5001   0.0245
  -3.750   0.1458   0.01186   0.00499  -0.0924   0.4919   0.0248
  -3.500   0.1685   0.01160   0.00466  -0.0912   0.4876   0.0252
  -3.250   0.1917   0.01138   0.00439  -0.0902   0.4834   0.0255
  -3.000   0.2148   0.01121   0.00417  -0.0891   0.4790   0.0258
  -2.750   0.2377   0.01112   0.00403  -0.0880   0.4739   0.0261
  -2.500   0.2604   0.01095   0.00381  -0.0869   0.4697   0.0262
  -2.250   0.2807   0.01056   0.00337  -0.0852   0.4649   0.0268
  -2.000   0.3020   0.01037   0.00313  -0.0838   0.4598   0.0270
  -1.750   0.3241   0.01025   0.00297  -0.0825   0.4550   0.0275
  -1.500   0.3469   0.01015   0.00286  -0.0814   0.4504   0.0281
  -1.250   0.3693   0.01004   0.00272  -0.0802   0.4467   0.0284
  -1.000   0.3916   0.00997   0.00262  -0.0789   0.4428   0.0287
  -0.750   0.4145   0.00990   0.00253  -0.0779   0.4395   0.0292
  -0.500   0.4374   0.00983   0.00244  -0.0768   0.4351   0.0298
  -0.250   0.4601   0.00978   0.00236  -0.0757   0.4306   0.0304
   0.000   0.4825   0.00978   0.00232  -0.0745   0.4256   0.0309
   0.250   0.5059   0.00974   0.00227  -0.0735   0.4221   0.0316
   0.500   0.5287   0.00974   0.00224  -0.0725   0.4160   0.0321
   0.750   0.5511   0.00975   0.00222  -0.0713   0.4115   0.0325
   1.000   0.5737   0.00971   0.00216  -0.0702   0.4059   0.0339
   1.250   0.5963   0.00972   0.00216  -0.0691   0.4010   0.0355
   1.500   0.6186   0.00976   0.00218  -0.0680   0.3969   0.0363
   1.750   0.6414   0.00979   0.00220  -0.0670   0.3938   0.0383
   2.000   0.6644   0.00981   0.00223  -0.0660   0.3901   0.0402
   2.250   0.6871   0.00984   0.00227  -0.0650   0.3862   0.0455
   2.500   0.7092   0.00990   0.00232  -0.0638   0.3821   0.0520
   2.750   0.7305   0.00982   0.00242  -0.0626   0.3785   0.1364
   3.000   0.7506   0.00953   0.00257  -0.0613   0.3744   0.3377
   3.500   1.0939   0.00953   0.00386  -0.1278   0.3477   1.0000
   3.750   1.1149   0.00966   0.00397  -0.1265   0.3412   1.0000
   4.000   1.1351   0.00982   0.00409  -0.1250   0.3349   1.0000
   4.250   1.1553   0.00997   0.00421  -0.1236   0.3270   1.0000
   4.500   1.1744   0.01016   0.00436  -0.1220   0.3185   1.0000
   4.750   1.1928   0.01037   0.00452  -0.1202   0.3084   1.0000
   5.000   1.2069   0.01074   0.00476  -0.1176   0.2876   1.0000
   5.250   1.2207   0.01104   0.00499  -0.1149   0.2741   1.0000
   5.500   1.2347   0.01128   0.00519  -0.1122   0.2648   1.0000
   5.750   1.2499   0.01148   0.00538  -0.1098   0.2587   1.0000
   6.000   1.2647   0.01171   0.00558  -0.1073   0.2517   1.0000
   6.250   1.2780   0.01200   0.00583  -0.1046   0.2426   1.0000
   6.500   1.2921   0.01227   0.00606  -0.1020   0.2359   1.0000
   6.750   1.3060   0.01254   0.00632  -0.0994   0.2298   1.0000
   7.000   1.3216   0.01276   0.00654  -0.0973   0.2257   1.0000
   7.250   1.3361   0.01305   0.00681  -0.0949   0.2207   1.0000
   7.500   1.3494   0.01337   0.00712  -0.0923   0.2145   1.0000
   7.750   1.3637   0.01367   0.00741  -0.0900   0.2089   1.0000
   8.000   1.3776   0.01400   0.00773  -0.0876   0.2043   1.0000
   8.250   1.3912   0.01434   0.00808  -0.0852   0.1991   1.0000
   8.500   1.4043   0.01471   0.00843  -0.0828   0.1921   1.0000
   8.750   1.4154   0.01516   0.00886  -0.0801   0.1844   1.0000
   9.000   1.4087   0.01631   0.00980  -0.0745   0.1486   1.0000
   9.250   1.3808   0.01846   0.01172  -0.0659   0.0976   1.0000
   9.500   1.3630   0.02048   0.01361  -0.0598   0.0598   1.0000
   9.750   1.3668   0.02161   0.01473  -0.0570   0.0499   1.0000
  10.000   1.3707   0.02282   0.01596  -0.0545   0.0413   1.0000
  10.250   1.3635   0.02487   0.01793  -0.0511   0.0203   1.0000
  10.500   1.3662   0.02643   0.01952  -0.0491   0.0157   1.0000
  10.750   1.3722   0.02784   0.02098  -0.0475   0.0139   1.0000
  11.000   1.3765   0.02945   0.02264  -0.0460   0.0124   1.0000
  11.250   1.3807   0.03117   0.02441  -0.0446   0.0114   1.0000
  11.500   1.3860   0.03286   0.02616  -0.0435   0.0111   1.0000
  11.750   1.3903   0.03469   0.02806  -0.0424   0.0105   1.0000
  12.000   1.3934   0.03668   0.03011  -0.0414   0.0099   1.0000
  12.250   1.3950   0.03889   0.03238  -0.0405   0.0093   1.0000
  12.500   1.3944   0.04134   0.03489  -0.0396   0.0086   1.0000
  12.750   1.3937   0.04387   0.03749  -0.0387   0.0085   1.0000
  13.000   1.3942   0.04629   0.03998  -0.0380   0.0082   1.0000
  13.250   1.3936   0.04887   0.04264  -0.0373   0.0081   1.0000
  13.500   1.3921   0.05160   0.04543  -0.0367   0.0077   1.0000
  13.750   1.3908   0.05434   0.04824  -0.0362   0.0073   1.0000
  14.000   1.3881   0.05728   0.05126  -0.0357   0.0073   1.0000
  14.250   1.3847   0.06037   0.05440  -0.0353   0.0069   1.0000
  14.500   1.3810   0.06354   0.05765  -0.0350   0.0066   1.0000
  14.750   1.3764   0.06687   0.06105  -0.0348   0.0065   1.0000
  15.000   1.3717   0.07025   0.06451  -0.0346   0.0065   1.0000
  15.250   1.3644   0.07403   0.06837  -0.0345   0.0061   1.0000
  15.500   1.3594   0.07758   0.07199  -0.0345   0.0061   1.0000
  15.750   1.3551   0.08104   0.07553  -0.0346   0.0059   1.0000
  16.000   1.3499   0.08466   0.07923  -0.0347   0.0059   1.0000
  16.250   1.3414   0.08881   0.08347  -0.0349   0.0058   1.0000
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