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GOE 155 (SSW D.1) AIRFOIL (goe155-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 155 (SSW D.1) AIRFOIL (goe155-il)
Reynolds number: 1,000,000
Max Cl/Cd: 111.01 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe155-il-1000000-n5.txt
Download as CSV file: xf-goe155-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 155 (SSW D.1) 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.4003   0.12071   0.11904  -0.0024   0.9238   0.0041
 -10.000  -0.3967   0.11667   0.11499  -0.0038   0.9146   0.0042
  -9.750  -0.3930   0.11292   0.11121  -0.0051   0.9049   0.0044
  -9.500  -0.3863   0.11003   0.10829  -0.0063   0.8946   0.0045
  -9.250  -0.3797   0.10708   0.10530  -0.0076   0.8842   0.0046
  -9.000  -0.3739   0.10384   0.10203  -0.0090   0.8734   0.0046
  -8.750  -0.3677   0.10069   0.09882  -0.0105   0.8620   0.0047
  -8.500  -0.3612   0.09750   0.09561  -0.0121   0.8508   0.0048
  -8.250  -0.3544   0.09433   0.09241  -0.0138   0.8404   0.0050
  -8.000  -0.3481   0.09099   0.08902  -0.0158   0.8298   0.0051
  -7.750  -0.3422   0.08748   0.08548  -0.0182   0.8188   0.0053
  -7.500  -0.3331   0.08326   0.08123  -0.0223   0.8086   0.0056
  -7.250  -0.3219   0.07718   0.07510  -0.0288   0.7995   0.0061
  -7.000  -0.3054   0.07230   0.07017  -0.0348   0.7899   0.0065
  -6.750  -0.2854   0.06948   0.06730  -0.0386   0.7803   0.0067
  -6.500  -0.2641   0.06631   0.06406  -0.0428   0.7716   0.0070
  -6.250  -0.2405   0.06203   0.05973  -0.0485   0.7640   0.0075
  -6.000  -0.2091   0.05241   0.04995  -0.0606   0.7578   0.0088
  -5.750  -0.1819   0.04955   0.04703  -0.0643   0.7509   0.0091
  -5.500  -0.1545   0.04697   0.04434  -0.0676   0.7439   0.0094
  -5.250  -0.1152   0.03707   0.03415  -0.0774   0.7388   0.0118
  -5.000  -0.0871   0.03513   0.03211  -0.0793   0.7320   0.0121
  -4.750  -0.0590   0.03337   0.03024  -0.0809   0.7256   0.0125
  -4.500  -0.0210   0.02101   0.01715  -0.0867   0.7210   0.0159
  -4.250   0.0068   0.02014   0.01615  -0.0872   0.7143   0.0162
  -4.000   0.0347   0.01912   0.01501  -0.0876   0.7094   0.0166
  -3.750   0.0629   0.01787   0.01359  -0.0881   0.7049   0.0174
  -3.500   0.0922   0.01450   0.00967  -0.0887   0.7004   0.0192
  -3.250   0.1209   0.01373   0.00865  -0.0889   0.6953   0.0200
  -3.000   0.1495   0.01332   0.00809  -0.0890   0.6878   0.0202
  -2.750   0.1779   0.01209   0.00658  -0.0893   0.6802   0.0206
  -2.500   0.2062   0.01122   0.00556  -0.0896   0.6726   0.0209
  -2.250   0.2347   0.01071   0.00495  -0.0898   0.6667   0.0211
  -2.000   0.2632   0.01038   0.00456  -0.0900   0.6589   0.0215
  -1.750   0.2917   0.01004   0.00414  -0.0901   0.6498   0.0218
  -1.500   0.3202   0.00970   0.00370  -0.0902   0.6390   0.0221
  -1.250   0.3486   0.00941   0.00333  -0.0904   0.6260   0.0225
  -1.000   0.3771   0.00919   0.00302  -0.0905   0.6104   0.0230
  -0.750   0.4054   0.00903   0.00275  -0.0906   0.5906   0.0235
  -0.500   0.4336   0.00893   0.00253  -0.0907   0.5648   0.0240
  -0.250   0.4617   0.00886   0.00234  -0.0909   0.5403   0.0244
   0.000   0.4899   0.00882   0.00220  -0.0910   0.5167   0.0247
   0.250   0.5180   0.00880   0.00207  -0.0911   0.4927   0.0249
   0.500   0.5460   0.00881   0.00198  -0.0913   0.4708   0.0251
   0.750   0.5741   0.00883   0.00191  -0.0914   0.4506   0.0253
   1.000   0.6021   0.00886   0.00188  -0.0915   0.4345   0.0257
   1.250   0.6303   0.00888   0.00184  -0.0917   0.4219   0.0259
   1.500   0.6584   0.00887   0.00179  -0.0918   0.4113   0.0260
   1.750   0.6865   0.00888   0.00177  -0.0919   0.4009   0.0260
   2.000   0.7147   0.00890   0.00176  -0.0921   0.3916   0.0262
   2.250   0.7427   0.00895   0.00178  -0.0922   0.3819   0.0263
   2.500   0.7707   0.00898   0.00178  -0.0923   0.3716   0.0271
   2.750   0.7987   0.00904   0.00180  -0.0924   0.3610   0.0289
   3.000   0.8261   0.00920   0.00188  -0.0925   0.3405   0.0304
   3.250   0.8533   0.00942   0.00199  -0.0925   0.3140   0.0317
   3.500   0.8804   0.00962   0.00212  -0.0926   0.2938   0.0330
   4.000   0.9340   0.01011   0.00248  -0.0926   0.2505   0.0679
   4.250   0.9611   0.01028   0.00264  -0.0927   0.2385   0.0872
   4.500   0.9883   0.01037   0.00284  -0.0927   0.2310   0.1511
   4.750   1.0154   0.01052   0.00303  -0.0928   0.2238   0.1809
   5.250   1.0646   0.00959   0.00359  -0.0922   0.2027   1.0000
   5.750   1.1166   0.01021   0.00406  -0.0920   0.1690   1.0000
   6.000   1.1351   0.01164   0.00495  -0.0911   0.0701   1.0000
   6.250   1.1578   0.01238   0.00551  -0.0906   0.0339   1.0000
   6.500   1.1830   0.01274   0.00585  -0.0903   0.0273   1.0000
   6.750   1.2084   0.01302   0.00616  -0.0901   0.0249   1.0000
   7.000   1.2329   0.01343   0.00655  -0.0898   0.0189   1.0000
   7.250   1.2575   0.01380   0.00692  -0.0895   0.0155   1.0000
   7.500   1.2814   0.01424   0.00734  -0.0891   0.0122   1.0000
   7.750   1.3056   0.01461   0.00774  -0.0887   0.0110   1.0000
   8.000   1.3292   0.01503   0.00818  -0.0882   0.0097   1.0000
   8.250   1.3519   0.01555   0.00870  -0.0877   0.0082   1.0000
   8.500   1.3751   0.01597   0.00917  -0.0872   0.0076   1.0000
   8.750   1.3976   0.01644   0.00968  -0.0866   0.0070   1.0000
   9.000   1.4194   0.01695   0.01022  -0.0859   0.0064   1.0000
   9.250   1.4401   0.01754   0.01085  -0.0851   0.0058   1.0000
   9.500   1.4597   0.01822   0.01158  -0.0841   0.0054   1.0000
   9.750   1.4796   0.01880   0.01223  -0.0832   0.0052   1.0000
  10.000   1.4986   0.01942   0.01291  -0.0821   0.0049   1.0000
  10.250   1.5167   0.02006   0.01361  -0.0810   0.0046   1.0000
  10.500   1.5339   0.02072   0.01431  -0.0797   0.0043   1.0000
  10.750   1.5489   0.02145   0.01510  -0.0781   0.0040   1.0000
  11.000   1.5588   0.02232   0.01603  -0.0758   0.0038   1.0000
  11.250   1.5649   0.02350   0.01732  -0.0731   0.0036   1.0000
  11.500   1.5737   0.02459   0.01849  -0.0710   0.0035   1.0000
  11.750   1.5826   0.02574   0.01972  -0.0692   0.0034   1.0000
  12.000   1.5905   0.02703   0.02111  -0.0674   0.0034   1.0000
  12.250   1.5974   0.02847   0.02264  -0.0657   0.0033   1.0000
  12.500   1.6032   0.03007   0.02434  -0.0641   0.0032   1.0000
  12.750   1.6081   0.03183   0.02620  -0.0627   0.0031   1.0000
  13.000   1.6124   0.03373   0.02821  -0.0614   0.0030   1.0000
  13.250   1.6154   0.03583   0.03041  -0.0602   0.0029   1.0000
  13.500   1.6179   0.03807   0.03275  -0.0592   0.0028   1.0000
  13.750   1.6190   0.04052   0.03530  -0.0584   0.0028   1.0000
  14.000   1.6190   0.04317   0.03805  -0.0576   0.0027   1.0000
  14.250   1.6179   0.04604   0.04103  -0.0571   0.0027   1.0000
  14.500   1.6160   0.04904   0.04414  -0.0566   0.0026   1.0000
  14.750   1.6124   0.05237   0.04757  -0.0564   0.0026   1.0000
  15.000   1.6075   0.05598   0.05130  -0.0564   0.0025   1.0000
  15.250   1.6021   0.05982   0.05524  -0.0566   0.0025   1.0000
  15.500   1.5953   0.06402   0.05956  -0.0571   0.0024   1.0000
  15.750   1.5869   0.06861   0.06428  -0.0579   0.0024   1.0000
  16.000   1.5775   0.07348   0.06927  -0.0589   0.0024   1.0000
  16.250   1.5666   0.07872   0.07463  -0.0601   0.0023   1.0000
  16.500   1.5550   0.08422   0.08025  -0.0616   0.0023   1.0000
  16.750   1.5423   0.08994   0.08609  -0.0632   0.0023   1.0000
  17.000   1.5276   0.09607   0.09236  -0.0651   0.0022   1.0000
  17.250   1.5132   0.10225   0.09867  -0.0671   0.0022   1.0000
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