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GOE 54 AIRFOIL (goe54-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 54 AIRFOIL (goe54-il)
Reynolds number: 500,000
Max Cl/Cd: 87.39 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe54-il-500000.txt
Download as CSV file: xf-goe54-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 54 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.4835   0.12985   0.12774   0.0371   1.0000   0.0171
 -10.500  -0.4846   0.12655   0.12445   0.0354   1.0000   0.0171
 -10.250  -0.6068   0.13275   0.13052   0.0539   1.0000   0.0170
 -10.000  -0.6024   0.12926   0.12705   0.0514   1.0000   0.0171
  -9.750  -0.5991   0.12580   0.12359   0.0486   1.0000   0.0171
  -9.250  -0.5883   0.11784   0.11567   0.0467   1.0000   0.0173
  -9.000  -0.5818   0.11435   0.11218   0.0464   1.0000   0.0174
  -8.750  -0.5759   0.11104   0.10889   0.0454   1.0000   0.0176
  -8.500  -0.5700   0.10776   0.10563   0.0441   1.0000   0.0178
  -8.250  -0.5641   0.10447   0.10236   0.0426   1.0000   0.0181
  -8.000  -0.5582   0.10115   0.09905   0.0408   1.0000   0.0184
  -7.750  -0.5524   0.09778   0.09570   0.0389   1.0000   0.0188
  -7.500  -0.5461   0.09432   0.09226   0.0364   1.0000   0.0193
  -7.250  -0.5341   0.09032   0.08826   0.0316   1.0000   0.0199
  -7.000  -0.4390   0.07265   0.07071   0.0111   1.0000   0.0203
  -6.750  -0.4316   0.06870   0.06678   0.0131   1.0000   0.0204
  -6.500  -0.4761   0.07521   0.07306   0.0093   1.0000   0.0204
  -6.250  -0.4638   0.07171   0.06957   0.0090   1.0000   0.0205
  -6.000  -0.4472   0.06819   0.06604   0.0070   1.0000   0.0207
  -5.750  -0.4271   0.06460   0.06243   0.0040   1.0000   0.0210
  -5.500  -0.4042   0.06095   0.05874   0.0007   1.0000   0.0215
  -5.250  -0.3792   0.05724   0.05497  -0.0028   1.0000   0.0222
  -5.000  -0.3369   0.05303   0.05051  -0.0089   1.0000   0.0236
  -4.750  -0.3005   0.04899   0.04616  -0.0126   1.0000   0.0237
  -4.500  -0.2858   0.04592   0.04237  -0.0124   0.6991   0.0239
  -4.250  -0.2658   0.04344   0.03952  -0.0131   0.5981   0.0241
  -4.000  -0.2420   0.04108   0.03686  -0.0142   0.5392   0.0244
  -3.750  -0.2156   0.03876   0.03430  -0.0153   0.5115   0.0249
  -3.500  -0.1875   0.03649   0.03181  -0.0163   0.4936   0.0257
  -3.250  -0.1490   0.03511   0.02996  -0.0165   0.4805   0.0276
  -2.750  -0.0934   0.02975   0.02418  -0.0179   0.4590   0.0281
  -2.500  -0.0673   0.02779   0.02213  -0.0185   0.4494   0.0284
  -2.250  -0.0398   0.02619   0.02038  -0.0190   0.4399   0.0289
  -2.000  -0.0112   0.02476   0.01879  -0.0192   0.4312   0.0297
  -1.750   0.0185   0.02360   0.01742  -0.0192   0.4222   0.0313
  -1.500   0.0525   0.02420   0.01747  -0.0180   0.4134   0.0324
  -1.250   0.0794   0.02112   0.01438  -0.0189   0.4042   0.0329
  -1.000   0.1074   0.01975   0.01296  -0.0192   0.3936   0.0335
  -0.750   0.1359   0.01877   0.01185  -0.0193   0.3829   0.0345
  -0.500   0.1652   0.01805   0.01095  -0.0192   0.3711   0.0363
  -0.250   0.1959   0.01812   0.01062  -0.0185   0.3570   0.0381
   0.000  -0.3200   0.05938   0.05527   0.0620   0.4236   0.0281
   0.250   0.2523   0.01577   0.00817  -0.0189   0.3226   0.0404
   0.500   0.2812   0.01548   0.00770  -0.0187   0.3061   0.0428
   0.750   0.3104   0.01500   0.00699  -0.0185   0.2923   0.0451
   1.000   0.3386   0.01427   0.00624  -0.0186   0.2807   0.0469
   1.250   0.3675   0.01505   0.00677  -0.0181   0.2717   0.0514
   2.750  -0.47831384.765501384.76099   0.1717   0.3077   0.0342
   3.000   0.5663   0.01195   0.00372  -0.0174   0.2384   0.0657
   3.250   0.5948   0.01217   0.00380  -0.0170   0.2346   0.0519
   3.500   0.6232   0.01207   0.00370  -0.0170   0.2305   0.0496
   3.750   0.6516   0.01202   0.00370  -0.0169   0.2275   0.0507
   4.000   0.6801   0.01197   0.00369  -0.0168   0.2239   0.0506
   4.250   0.7084   0.01200   0.00371  -0.0167   0.2200   0.0506
   4.500   0.7363   0.01221   0.00387  -0.0166   0.2153   0.0513
   4.750   0.7647   0.01217   0.00388  -0.0166   0.2123   0.0536
   5.000   0.7929   0.01222   0.00395  -0.0165   0.2081   0.0587
   5.250   0.8208   0.01235   0.00407  -0.0163   0.2035   0.0672
   5.500   0.8440   0.01087   0.00439  -0.0157   0.1989   1.0000
   5.750   0.8721   0.01097   0.00452  -0.0155   0.1943   1.0000
   6.000   0.8999   0.01111   0.00464  -0.0154   0.1884   1.0000
   6.250   0.9277   0.01130   0.00481  -0.0154   0.1820   1.0000
   6.500   0.9555   0.01143   0.00496  -0.0152   0.1760   1.0000
   6.750   0.9829   0.01170   0.00519  -0.0152   0.1701   1.0000
   7.000   1.0107   0.01183   0.00537  -0.0151   0.1645   1.0000
   7.250   1.0381   0.01207   0.00560  -0.0150   0.1591   1.0000
   7.500   1.0654   0.01234   0.00590  -0.0149   0.1547   1.0000
   7.750   1.0928   0.01258   0.00617  -0.0147   0.1503   1.0000
   8.000   1.1198   0.01287   0.00646  -0.0146   0.1454   1.0000
   8.250   1.1468   0.01315   0.00680  -0.0145   0.1406   1.0000
   8.500   1.1737   0.01343   0.00711  -0.0144   0.1360   1.0000
   8.750   1.2000   0.01386   0.00752  -0.0143   0.1306   1.0000
   9.000   1.2270   0.01410   0.00787  -0.0142   0.1258   1.0000
   9.250   1.2531   0.01452   0.00828  -0.0142   0.1190   1.0000
   9.500   1.2795   0.01483   0.00867  -0.0140   0.1123   1.0000
   9.750   1.3053   0.01531   0.00915  -0.0140   0.1029   1.0000
  10.000   1.3310   0.01579   0.00964  -0.0139   0.0869   1.0000
  10.250   1.3541   0.01691   0.01057  -0.0138   0.0626   1.0000
  10.500   1.3771   0.01798   0.01165  -0.0137   0.0546   1.0000
  10.750   1.4002   0.01897   0.01273  -0.0135   0.0498   1.0000
  11.000   1.4230   0.01992   0.01376  -0.0133   0.0463   1.0000
  11.250   1.4436   0.02128   0.01519  -0.0131   0.0426   1.0000
  11.500   1.4666   0.02203   0.01608  -0.0128   0.0402   1.0000
  11.750   1.4874   0.02315   0.01728  -0.0126   0.0375   1.0000
  12.000   1.5050   0.02475   0.01899  -0.0124   0.0349   1.0000
  12.250   1.5257   0.02570   0.02007  -0.0121   0.0329   1.0000
  12.500   1.5438   0.02701   0.02147  -0.0119   0.0308   1.0000
  12.750   1.5553   0.02920   0.02378  -0.0117   0.0287   1.0000
  13.000   1.5723   0.03047   0.02519  -0.0115   0.0272   1.0000
  13.250   1.5853   0.03221   0.02706  -0.0114   0.0258   1.0000
  13.500   1.5910   0.03484   0.02981  -0.0118   0.0247   1.0000
  13.750   1.5796   0.04014   0.03533  -0.0152   0.0241   1.0000
  14.000   1.5580   0.05059   0.04604  -0.0258   0.0241   1.0000
  14.250   1.5316   0.05876   0.05436  -0.0308   0.0243   1.0000
  14.500   1.5047   0.06646   0.06219  -0.0349   0.0244   1.0000
  14.750   1.4789   0.07388   0.06972  -0.0384   0.0244   1.0000
  15.000   1.4553   0.08095   0.07689  -0.0417   0.0244   1.0000
  15.250   1.4339   0.08770   0.08371  -0.0447   0.0242   1.0000
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