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GOE 178 AIRFOIL (goe178-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 178 AIRFOIL (goe178-il)
Reynolds number: 1,000,000
Max Cl/Cd: 110.48 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe178-il-1000000-n5.txt
Download as CSV file: xf-goe178-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 178 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
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.5000   0.15472   0.15308   0.0144   1.0000   0.0038
 -12.500  -0.4871   0.14785   0.14622   0.0115   1.0000   0.0041
 -10.000  -0.6760   0.02028   0.01719  -0.0850   0.9952   0.0075
  -9.750  -0.6467   0.01820   0.01487  -0.0869   0.9888   0.0083
  -9.500  -0.6169   0.01674   0.01320  -0.0883   0.9798   0.0091
  -9.250  -0.5896   0.01563   0.01190  -0.0888   0.9697   0.0099
  -9.000  -0.5631   0.01500   0.01118  -0.0888   0.9621   0.0110
  -8.750  -0.5363   0.01478   0.01097  -0.0886   0.9551   0.0120
  -8.500  -0.5100   0.01443   0.01055  -0.0883   0.9477   0.0130
  -8.250  -0.4842   0.01377   0.00974  -0.0881   0.9381   0.0139
  -8.000  -0.4571   0.01393   0.00993  -0.0877   0.9273   0.0145
  -7.750  -0.4303   0.01411   0.01011  -0.0872   0.9116   0.0151
  -7.500  -0.4048   0.01422   0.01014  -0.0864   0.8820   0.0159
  -7.250  -0.3793   0.01420   0.00994  -0.0858   0.8461   0.0167
  -6.750  -0.3252   0.01372   0.00908  -0.0855   0.7983   0.0181
  -6.500  -0.2975   0.01364   0.00886  -0.0854   0.7776   0.0185
  -6.250  -0.2696   0.01365   0.00874  -0.0853   0.7558   0.0188
  -6.000  -0.2423   0.01275   0.00761  -0.0855   0.7316   0.0196
  -5.750  -0.2145   0.01261   0.00735  -0.0856   0.7027   0.0201
  -5.500  -0.1867   0.01252   0.00710  -0.0856   0.6686   0.0206
  -5.250  -0.1588   0.01242   0.00684  -0.0857   0.6342   0.0212
  -5.000  -0.1308   0.01224   0.00648  -0.0857   0.6030   0.0218
  -4.750  -0.1027   0.01196   0.00601  -0.0858   0.5755   0.0223
  -4.500  -0.0745   0.01172   0.00561  -0.0859   0.5513   0.0229
  -4.250  -0.0462   0.01145   0.00519  -0.0860   0.5303   0.0233
  -4.000  -0.0178   0.01116   0.00476  -0.0862   0.5115   0.0236
  -3.750   0.0106   0.01088   0.00434  -0.0863   0.4961   0.0238
  -3.500   0.0391   0.01061   0.00396  -0.0864   0.4841   0.0240
  -3.250   0.0676   0.01036   0.00361  -0.0865   0.4743   0.0242
  -3.000   0.0962   0.01012   0.00329  -0.0866   0.4659   0.0244
  -2.750   0.1248   0.00993   0.00303  -0.0867   0.4588   0.0246
  -2.500   0.1535   0.00978   0.00283  -0.0868   0.4524   0.0249
  -2.000   0.2109   0.00946   0.00239  -0.0870   0.4403   0.0252
  -1.750   0.2395   0.00934   0.00221  -0.0871   0.4339   0.0254
  -1.500   0.2682   0.00925   0.00207  -0.0872   0.4286   0.0256
  -1.250   0.2970   0.00909   0.00188  -0.0874   0.4237   0.0261
  -1.000   0.3257   0.00895   0.00167  -0.0875   0.4186   0.0272
  -0.750   0.3544   0.00888   0.00156  -0.0876   0.4147   0.0281
  -0.500   0.3832   0.00882   0.00149  -0.0877   0.4113   0.0288
  -0.250   0.4118   0.00878   0.00143  -0.0878   0.4072   0.0295
   0.000   0.4404   0.00876   0.00139  -0.0879   0.4030   0.0301
   0.250   0.4690   0.00875   0.00136  -0.0880   0.3995   0.0307
   0.500   0.4977   0.00873   0.00134  -0.0881   0.3961   0.0313
   0.750   0.5262   0.00873   0.00132  -0.0882   0.3919   0.0319
   1.000   0.5547   0.00875   0.00132  -0.0882   0.3870   0.0332
   1.500   0.6117   0.00872   0.00136  -0.0885   0.3750   0.0650
   1.750   0.6401   0.00874   0.00141  -0.0886   0.3705   0.0776
   2.000   0.6685   0.00876   0.00145  -0.0886   0.3667   0.0817
   2.250   0.6968   0.00880   0.00149  -0.0887   0.3591   0.0884
   2.500   0.7251   0.00884   0.00155  -0.0888   0.3530   0.0975
   2.750   0.7536   0.00876   0.00164  -0.0890   0.3451   0.1772
   3.000   0.7819   0.00869   0.00174  -0.0893   0.3351   0.2713
   3.250   0.8070   0.00755   0.00201  -0.0893   0.3222   0.8721
   3.750   0.8595   0.00778   0.00221  -0.0886   0.2800   1.0000
   4.000   0.8863   0.00813   0.00241  -0.0886   0.2526   1.0000
   4.250   0.9121   0.00868   0.00272  -0.0884   0.2124   1.0000
   4.500   0.9389   0.00901   0.00295  -0.0884   0.1914   1.0000
   4.750   0.9596   0.01047   0.00379  -0.0877   0.0657   1.0000
   5.000   0.9863   0.01077   0.00405  -0.0876   0.0554   1.0000
   5.250   1.0133   0.01100   0.00427  -0.0876   0.0507   1.0000
   5.500   1.0399   0.01130   0.00455  -0.0874   0.0441   1.0000
   5.750   1.0666   0.01154   0.00479  -0.0873   0.0390   1.0000
   6.000   1.0917   0.01207   0.00517  -0.0871   0.0174   1.0000
   6.250   1.1178   0.01238   0.00549  -0.0869   0.0130   1.0000
   6.500   1.1440   0.01268   0.00582  -0.0867   0.0117   1.0000
   6.750   1.1697   0.01303   0.00619  -0.0864   0.0104   1.0000
   7.000   1.1948   0.01346   0.00665  -0.0861   0.0089   1.0000
   7.250   1.2204   0.01379   0.00702  -0.0858   0.0084   1.0000
   7.500   1.2456   0.01415   0.00740  -0.0856   0.0077   1.0000
   7.750   1.2703   0.01455   0.00783  -0.0852   0.0071   1.0000
   8.000   1.2945   0.01501   0.00830  -0.0848   0.0066   1.0000
   8.250   1.3175   0.01562   0.00896  -0.0842   0.0060   1.0000
   8.500   1.3413   0.01607   0.00947  -0.0837   0.0058   1.0000
   8.750   1.3645   0.01658   0.01003  -0.0832   0.0055   1.0000
   9.000   1.3871   0.01711   0.01061  -0.0826   0.0052   1.0000
   9.250   1.4095   0.01765   0.01118  -0.0819   0.0049   1.0000
   9.500   1.4315   0.01818   0.01175  -0.0813   0.0046   1.0000
   9.750   1.4525   0.01879   0.01239  -0.0805   0.0044   1.0000
  10.000   1.4710   0.01961   0.01329  -0.0794   0.0041   1.0000
  10.250   1.4882   0.02051   0.01426  -0.0781   0.0039   1.0000
  10.500   1.5062   0.02125   0.01508  -0.0769   0.0038   1.0000
  10.750   1.5226   0.02207   0.01597  -0.0755   0.0037   1.0000
  11.000   1.5373   0.02296   0.01694  -0.0739   0.0036   1.0000
  11.250   1.5498   0.02392   0.01798  -0.0721   0.0035   1.0000
  11.500   1.5575   0.02492   0.01908  -0.0695   0.0034   1.0000
  11.750   1.5633   0.02609   0.02034  -0.0669   0.0033   1.0000
  12.000   1.5680   0.02744   0.02179  -0.0645   0.0032   1.0000
  12.250   1.5724   0.02897   0.02340  -0.0626   0.0032   1.0000
  12.500   1.5758   0.03074   0.02527  -0.0609   0.0031   1.0000
  12.750   1.5777   0.03288   0.02751  -0.0598   0.0031   1.0000
  13.000   1.5802   0.03519   0.02991  -0.0591   0.0030   1.0000
  13.250   1.5812   0.03786   0.03269  -0.0588   0.0029   1.0000
  13.500   1.5802   0.04098   0.03592  -0.0588   0.0029   1.0000
  13.750   1.5795   0.04424   0.03928  -0.0592   0.0028   1.0000
  14.000   1.5760   0.04802   0.04317  -0.0599   0.0028   1.0000
  14.250   1.5718   0.05200   0.04725  -0.0607   0.0028   1.0000
  14.500   1.5650   0.05635   0.05171  -0.0617   0.0027   1.0000
  14.750   1.5571   0.06087   0.05634  -0.0626   0.0027   1.0000
  15.000   1.5478   0.06559   0.06118  -0.0637   0.0027   1.0000
  15.250   1.5366   0.07052   0.06622  -0.0647   0.0026   1.0000
  15.500   1.5249   0.07563   0.07143  -0.0659   0.0026   1.0000
  15.750   1.5129   0.08082   0.07674  -0.0671   0.0026   1.0000
  16.000   1.4987   0.08642   0.08244  -0.0685   0.0025   1.0000
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