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GOE 362 AIRFOIL (goe362-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 362 AIRFOIL (goe362-il)
Reynolds number: 500,000
Max Cl/Cd: 109.4 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe362-il-500000.txt
Download as CSV file: xf-goe362-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 362 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.2417   0.08491   0.08281  -0.0256   1.0000   0.0158
  -8.250  -0.2396   0.08178   0.07970  -0.0260   1.0000   0.0166
  -8.000  -0.2388   0.07876   0.07671  -0.0265   1.0000   0.0172
  -7.750  -0.2446   0.07624   0.07424  -0.0276   1.0000   0.0177
  -7.500  -0.2494   0.07394   0.07199  -0.0270   1.0000   0.0178
  -7.250  -0.2603   0.07244   0.07054  -0.0247   1.0000   0.0178
  -7.000  -0.2551   0.06892   0.06705  -0.0274   0.9968   0.0179
  -6.750  -0.2416   0.06217   0.06031  -0.0327   0.9926   0.0183
  -6.500  -0.2224   0.05796   0.05609  -0.0357   0.9885   0.0186
  -6.250  -0.1994   0.05365   0.05177  -0.0404   0.9847   0.0192
  -6.000  -0.1761   0.04921   0.04732  -0.0461   0.9792   0.0199
  -5.750  -0.1492   0.04430   0.04238  -0.0533   0.9736   0.0207
  -5.500  -0.1197   0.03902   0.03705  -0.0616   0.9664   0.0223
  -5.250  -0.0798   0.03317   0.03108  -0.0731   0.9578   0.0237
  -5.000  -0.0501   0.02795   0.02574  -0.0796   0.9467   0.0239
  -4.750  -0.0329   0.02197   0.01966  -0.0836   0.9339   0.0251
  -4.500  -0.0113   0.01970   0.01732  -0.0847   0.9206   0.0260
  -4.250   0.0134   0.01690   0.01438  -0.0868   0.9069   0.0277
  -4.000   0.0500   0.01347   0.01059  -0.0906   0.8965   0.0318
  -3.750   0.0881   0.01658   0.01238  -0.1023   0.9223   0.0216
  -3.500   0.1153   0.01344   0.00860  -0.1020   0.9092   0.0214
  -3.250   0.1421   0.01212   0.00694  -0.1014   0.8952   0.0223
  -3.000   0.1690   0.01136   0.00592  -0.1007   0.8798   0.0235
  -2.750   0.1950   0.01024   0.00459  -0.1001   0.8637   0.0258
  -2.500   0.2215   0.00985   0.00410  -0.0995   0.8469   0.0283
  -2.250   0.2481   0.00946   0.00356  -0.0989   0.8302   0.0307
  -2.000   0.2743   0.00888   0.00283  -0.0982   0.8135   0.0346
  -1.750   0.3009   0.00869   0.00256  -0.0977   0.7969   0.0402
  -1.500   0.3274   0.00837   0.00214  -0.0971   0.7806   0.0469
  -1.250   0.3541   0.00822   0.00192  -0.0966   0.7637   0.0567
  -1.000   0.3808   0.00808   0.00178  -0.0961   0.7467   0.0761
  -0.750   0.4075   0.00803   0.00172  -0.0956   0.7298   0.1023
  -0.500   0.4341   0.00799   0.00163  -0.0952   0.7130   0.1200
  -0.250   0.4608   0.00795   0.00154  -0.0948   0.6966   0.1356
   0.000   0.4874   0.00792   0.00151  -0.0944   0.6804   0.1576
   0.250   0.5139   0.00788   0.00152  -0.0940   0.6644   0.2052
   0.500   0.5401   0.00774   0.00153  -0.0936   0.6484   0.2807
   0.750   0.5717   0.00625   0.00164  -0.0947   0.6318   1.0000
   1.000   0.5984   0.00638   0.00163  -0.0942   0.6149   1.0000
   1.250   0.6250   0.00651   0.00165  -0.0938   0.5972   1.0000
   1.500   0.6515   0.00666   0.00168  -0.0934   0.5783   1.0000
   1.750   0.6779   0.00682   0.00172  -0.0929   0.5583   1.0000
   2.000   0.7042   0.00698   0.00176  -0.0925   0.5364   1.0000
   2.250   0.7304   0.00716   0.00183  -0.0920   0.5151   1.0000
   2.500   0.7566   0.00736   0.00192  -0.0916   0.4948   1.0000
   2.750   0.7827   0.00756   0.00202  -0.0912   0.4777   1.0000
   3.000   0.8089   0.00777   0.00214  -0.0908   0.4630   1.0000
   3.250   0.8352   0.00797   0.00228  -0.0904   0.4503   1.0000
   3.500   0.8614   0.00817   0.00244  -0.0900   0.4392   1.0000
   3.750   0.8875   0.00839   0.00259  -0.0896   0.4274   1.0000
   4.000   0.9135   0.00861   0.00276  -0.0892   0.4147   1.0000
   4.250   0.9394   0.00882   0.00292  -0.0888   0.4018   1.0000
   4.500   0.9657   0.00900   0.00310  -0.0885   0.3897   1.0000
   4.750   0.9918   0.00918   0.00327  -0.0881   0.3774   1.0000
   5.000   1.0178   0.00937   0.00345  -0.0877   0.3647   1.0000
   5.250   1.0437   0.00957   0.00364  -0.0873   0.3529   1.0000
   5.500   1.0695   0.00979   0.00385  -0.0869   0.3397   1.0000
   5.750   1.0951   0.01001   0.00406  -0.0865   0.3245   1.0000
   6.000   1.1206   0.01025   0.00429  -0.0861   0.3088   1.0000
   6.250   1.1456   0.01053   0.00454  -0.0856   0.2908   1.0000
   6.500   1.1701   0.01087   0.00484  -0.0851   0.2701   1.0000
   6.750   1.1937   0.01131   0.00518  -0.0844   0.2432   1.0000
   7.000   1.2159   0.01192   0.00562  -0.0836   0.2039   1.0000
   7.250   1.2353   0.01287   0.00624  -0.0826   0.1479   1.0000
   7.500   1.2538   0.01393   0.00701  -0.0814   0.0998   1.0000
   7.750   1.2744   0.01471   0.00769  -0.0804   0.0814   1.0000
   8.000   1.2961   0.01532   0.00829  -0.0795   0.0715   1.0000
   8.250   1.3184   0.01583   0.00884  -0.0787   0.0642   1.0000
   8.500   1.3392   0.01649   0.00951  -0.0777   0.0568   1.0000
   8.750   1.3616   0.01694   0.01000  -0.0770   0.0508   1.0000
   9.000   1.3826   0.01752   0.01060  -0.0760   0.0427   1.0000
   9.250   1.4018   0.01827   0.01130  -0.0749   0.0312   1.0000
   9.500   1.4185   0.01926   0.01224  -0.0733   0.0225   1.0000
   9.750   1.4342   0.02029   0.01333  -0.0716   0.0188   1.0000
  10.000   1.4500   0.02122   0.01434  -0.0699   0.0167   1.0000
  10.250   1.4584   0.02272   0.01594  -0.0673   0.0149   1.0000
  10.500   1.4718   0.02366   0.01700  -0.0653   0.0140   1.0000
  10.750   1.4825   0.02465   0.01809  -0.0630   0.0131   1.0000
  11.000   1.4886   0.02576   0.01929  -0.0601   0.0124   1.0000
  11.250   1.4919   0.02705   0.02068  -0.0570   0.0119   1.0000
  11.500   1.4914   0.02870   0.02243  -0.0538   0.0114   1.0000
  11.750   1.4868   0.03082   0.02467  -0.0508   0.0110   1.0000
  12.000   1.4737   0.03396   0.02798  -0.0477   0.0106   1.0000
  12.250   1.4751   0.03604   0.03021  -0.0461   0.0105   1.0000
  12.500   1.4772   0.03819   0.03250  -0.0449   0.0102   1.0000
  12.750   1.4776   0.04066   0.03511  -0.0439   0.0100   1.0000
  13.000   1.4760   0.04350   0.03810  -0.0431   0.0098   1.0000
  13.250   1.4745   0.04647   0.04121  -0.0427   0.0096   1.0000
  13.500   1.4724   0.04965   0.04453  -0.0427   0.0094   1.0000
  13.750   1.4683   0.05324   0.04827  -0.0428   0.0091   1.0000
  14.000   1.4653   0.05679   0.05195  -0.0433   0.0089   1.0000
  14.250   1.4606   0.06072   0.05601  -0.0441   0.0087   1.0000
  14.500   1.4554   0.06482   0.06023  -0.0452   0.0085   1.0000
  14.750   1.4487   0.06933   0.06487  -0.0465   0.0084   1.0000
  15.000   1.4417   0.07402   0.06968  -0.0482   0.0082   1.0000
  15.250   1.4326   0.07924   0.07504  -0.0500   0.0081   1.0000
  15.500   1.4232   0.08470   0.08064  -0.0522   0.0080   1.0000
  15.750   1.4129   0.09050   0.08657  -0.0546   0.0079   1.0000
  16.000   1.4015   0.09669   0.09291  -0.0573   0.0078   1.0000
  16.250   1.3898   0.10316   0.09954  -0.0604   0.0078   1.0000
  16.500   1.3764   0.11012   0.10666  -0.0639   0.0077   1.0000
  16.750   1.3638   0.11719   0.11388  -0.0677   0.0077   1.0000
  17.000   1.3496   0.12482   0.12167  -0.0719   0.0077   1.0000
  17.250   1.3369   0.13242   0.12943  -0.0764   0.0077   1.0000
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