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GOE 101 AIRFOIL (goe101-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 101 AIRFOIL (goe101-il)
Reynolds number: 500,000
Max Cl/Cd: 100.46 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe101-il-500000-n5.txt
Download as CSV file: xf-goe101-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 101 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3636   0.08245   0.08036  -0.0206   1.0000   0.0062
  -7.250  -0.3633   0.07950   0.07745  -0.0215   1.0000   0.0062
  -7.000  -0.3599   0.07607   0.07405  -0.0236   1.0000   0.0062
  -6.750  -0.3426   0.07125   0.06923  -0.0298   0.9909   0.0062
  -6.500  -0.3156   0.06525   0.06319  -0.0389   0.9806   0.0062
  -6.250  -0.2833   0.05820   0.05607  -0.0495   0.9690   0.0064
  -6.000  -0.2505   0.05295   0.05073  -0.0576   0.9557   0.0066
  -5.750  -0.2174   0.04964   0.04732  -0.0633   0.9408   0.0073
  -5.500  -0.1856   0.04469   0.04219  -0.0691   0.9206   0.0081
  -5.250  -0.1577   0.03865   0.03588  -0.0737   0.8973   0.0083
  -5.000  -0.1321   0.03089   0.02766  -0.0768   0.8737   0.0090
  -4.750  -0.1083   0.02400   0.02014  -0.0778   0.8507   0.0098
  -4.500  -0.0838   0.02279   0.01869  -0.0775   0.8242   0.0106
  -4.250  -0.0611   0.01490   0.00969  -0.0768   0.8033   0.0143
  -4.000  -0.0353   0.01518   0.00985  -0.0764   0.7781   0.0149
  -3.750  -0.0095   0.01540   0.00994  -0.0760   0.7546   0.0158
  -3.500   0.0166   0.01509   0.00942  -0.0756   0.7333   0.0179
  -3.250   0.0428   0.01407   0.00802  -0.0751   0.7134   0.0206
  -3.000   0.0696   0.01410   0.00783  -0.0746   0.6941   0.0217
  -2.750   0.0950   0.01290   0.00642  -0.0744   0.6761   0.0236
  -2.500   0.1214   0.01252   0.00588  -0.0741   0.6585   0.0248
  -2.250   0.1480   0.01220   0.00542  -0.0739   0.6412   0.0264
  -2.000   0.1746   0.01187   0.00495  -0.0735   0.6241   0.0280
  -1.750   0.2012   0.01148   0.00440  -0.0732   0.6073   0.0289
  -1.500   0.2278   0.01114   0.00392  -0.0729   0.5906   0.0294
  -1.250   0.2544   0.01083   0.00349  -0.0726   0.5744   0.0297
  -1.000   0.2811   0.01065   0.00320  -0.0723   0.5594   0.0303
  -0.750   0.3078   0.01042   0.00288  -0.0720   0.5465   0.0306
  -0.500   0.3344   0.01015   0.00253  -0.0717   0.5347   0.0304
  -0.250   0.3612   0.00993   0.00224  -0.0715   0.5242   0.0303
   0.000   0.3880   0.00975   0.00201  -0.0713   0.5145   0.0303
   0.500   0.4418   0.00953   0.00167  -0.0708   0.4942   0.0304
   0.750   0.4687   0.00949   0.00156  -0.0706   0.4824   0.0305
   1.000   0.4956   0.00947   0.00147  -0.0704   0.4707   0.0309
   1.250   0.5225   0.00948   0.00142  -0.0702   0.4606   0.0314
   1.500   0.5497   0.00946   0.00137  -0.0700   0.4523   0.0331
   2.000   0.6040   0.00949   0.00138  -0.0697   0.4390   0.0422
   2.250   0.6338   0.00752   0.00160  -0.0708   0.4318   1.0000
   2.500   0.6607   0.00762   0.00167  -0.0706   0.4251   1.0000
   2.750   0.6874   0.00776   0.00175  -0.0704   0.4163   1.0000
   3.000   0.7141   0.00788   0.00183  -0.0701   0.4054   1.0000
   3.250   0.7407   0.00801   0.00193  -0.0699   0.3950   1.0000
   3.500   0.7674   0.00815   0.00204  -0.0697   0.3875   1.0000
   3.750   0.7943   0.00826   0.00216  -0.0695   0.3808   1.0000
   4.000   0.8209   0.00840   0.00230  -0.0693   0.3727   1.0000
   4.250   0.8476   0.00853   0.00245  -0.0691   0.3638   1.0000
   4.500   0.8740   0.00870   0.00260  -0.0688   0.3503   1.0000
   4.750   0.8993   0.00899   0.00278  -0.0685   0.3172   1.0000
   5.250   0.9429   0.01055   0.00365  -0.0670   0.1793   1.0000
   5.500   0.9663   0.01111   0.00406  -0.0665   0.1454   1.0000
   5.750   0.9877   0.01196   0.00459  -0.0657   0.0880   1.0000
   6.000   1.0116   0.01245   0.00503  -0.0652   0.0699   1.0000
   6.250   1.0312   0.01352   0.00583  -0.0642   0.0183   1.0000
   6.500   1.0548   0.01404   0.00641  -0.0635   0.0127   1.0000
   6.750   1.0787   0.01447   0.00691  -0.0629   0.0108   1.0000
   7.000   1.1020   0.01497   0.00750  -0.0623   0.0095   1.0000
   7.250   1.1241   0.01561   0.00822  -0.0615   0.0083   1.0000
   7.500   1.1443   0.01650   0.00926  -0.0604   0.0074   1.0000
   7.750   1.1662   0.01711   0.00995  -0.0596   0.0069   1.0000
   8.000   1.1878   0.01770   0.01060  -0.0588   0.0060   1.0000
   8.250   1.2079   0.01844   0.01141  -0.0578   0.0056   1.0000
   8.500   1.2264   0.01933   0.01238  -0.0566   0.0052   1.0000
   8.750   1.2396   0.02073   0.01389  -0.0547   0.0049   1.0000
   9.000   1.2558   0.02174   0.01502  -0.0532   0.0047   1.0000
   9.250   1.2702   0.02287   0.01631  -0.0515   0.0045   1.0000
   9.500   1.2827   0.02413   0.01769  -0.0495   0.0043   1.0000
   9.750   1.2931   0.02550   0.01919  -0.0473   0.0041   1.0000
  10.000   1.3026   0.02679   0.02060  -0.0450   0.0039   1.0000
  10.250   1.3097   0.02802   0.02194  -0.0424   0.0038   1.0000
  10.500   1.3173   0.02913   0.02315  -0.0402   0.0036   1.0000
  10.750   1.3243   0.03034   0.02444  -0.0381   0.0034   1.0000
  11.000   1.3284   0.03187   0.02607  -0.0360   0.0033   1.0000
  11.250   1.3307   0.03369   0.02799  -0.0342   0.0032   1.0000
  11.500   1.3292   0.03610   0.03054  -0.0324   0.0031   1.0000
  11.750   1.3270   0.03884   0.03345  -0.0310   0.0030   1.0000
  12.000   1.3272   0.04142   0.03622  -0.0301   0.0029   1.0000
  12.250   1.3254   0.04440   0.03940  -0.0295   0.0029   1.0000
  12.500   1.3219   0.04775   0.04294  -0.0292   0.0028   1.0000
  12.750   1.3158   0.05161   0.04702  -0.0294   0.0028   1.0000
  13.000   1.3076   0.05595   0.05158  -0.0300   0.0028   1.0000
  13.250   1.2995   0.06042   0.05627  -0.0310   0.0028   1.0000
  13.500   1.2878   0.06570   0.06178  -0.0326   0.0027   1.0000
  13.750   1.2750   0.07135   0.06763  -0.0348   0.0027   1.0000
  14.000   1.2625   0.07717   0.07363  -0.0373   0.0027   1.0000
  14.250   1.2476   0.08374   0.08038  -0.0404   0.0027   1.0000
  14.500   1.2309   0.09101   0.08785  -0.0440   0.0026   1.0000
  14.750   1.2151   0.09849   0.09549  -0.0480   0.0026   1.0000
  15.000   1.1985   0.10659   0.10375  -0.0526   0.0026   1.0000
  15.250   1.1828   0.11486   0.11217  -0.0573   0.0027   1.0000
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