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GOE 450 AIRFOIL (goe450-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 450 AIRFOIL (goe450-il)
Reynolds number: 500,000
Max Cl/Cd: 107.98 at α=3°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe450-il-500000-n5.txt
Download as CSV file: xf-goe450-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 450 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.2363   0.08618   0.08379  -0.0629   0.9694   0.0128
  -8.500  -0.2330   0.08046   0.07807  -0.0676   0.9608   0.0136
  -8.250  -0.2296   0.07595   0.07356  -0.0711   0.9505   0.0139
  -8.000  -0.2190   0.07373   0.07133  -0.0729   0.9425   0.0141
  -7.750  -0.2057   0.07101   0.06859  -0.0759   0.9352   0.0144
  -7.500  -0.1919   0.06783   0.06539  -0.0797   0.9274   0.0147
  -7.250  -0.1762   0.06415   0.06167  -0.0844   0.9198   0.0153
  -7.000  -0.1582   0.05863   0.05609  -0.0920   0.9114   0.0164
  -6.750  -0.1350   0.04905   0.04633  -0.1044   0.9033   0.0176
  -6.500  -0.1122   0.04671   0.04394  -0.1072   0.8967   0.0179
  -6.250  -0.0880   0.04378   0.04091  -0.1105   0.8903   0.0184
  -6.000  -0.0618   0.03986   0.03684  -0.1146   0.8837   0.0194
  -5.750  -0.0336   0.02355   0.01948  -0.1245   0.8761   0.0221
  -5.500  -0.0080   0.02283   0.01866  -0.1248   0.8701   0.0225
  -5.250   0.0178   0.02191   0.01762  -0.1252   0.8633   0.0230
  -5.000   0.0437   0.01994   0.01535  -0.1256   0.8569   0.0235
  -4.750   0.0699   0.01807   0.01316  -0.1259   0.8493   0.0241
  -4.500   0.0966   0.01660   0.01138  -0.1261   0.8423   0.0248
  -4.250   0.1237   0.01556   0.01008  -0.1261   0.8342   0.0256
  -4.000   0.1509   0.01460   0.00887  -0.1261   0.8262   0.0261
  -3.750   0.1782   0.01386   0.00793  -0.1260   0.8170   0.0264
  -3.500   0.2055   0.01327   0.00715  -0.1259   0.8076   0.0267
  -3.250   0.2328   0.01278   0.00649  -0.1258   0.7974   0.0269
  -3.000   0.2601   0.01236   0.00593  -0.1256   0.7855   0.0271
  -2.750   0.2870   0.01155   0.00496  -0.1255   0.7732   0.0276
  -2.500   0.3139   0.01098   0.00430  -0.1254   0.7606   0.0283
  -2.250   0.3409   0.01062   0.00385  -0.1252   0.7477   0.0286
  -2.000   0.3679   0.01033   0.00346  -0.1250   0.7344   0.0290
  -1.750   0.3949   0.01009   0.00314  -0.1248   0.7208   0.0294
  -1.250   0.4491   0.00972   0.00264  -0.1245   0.6953   0.0304
  -1.000   0.4764   0.00958   0.00245  -0.1244   0.6844   0.0309
  -0.750   0.5036   0.00947   0.00229  -0.1242   0.6744   0.0315
  -0.500   0.5310   0.00938   0.00215  -0.1241   0.6646   0.0320
  -0.250   0.5584   0.00931   0.00204  -0.1240   0.6553   0.0325
   0.250   0.6133   0.00925   0.00191  -0.1239   0.6379   0.0342
   0.500   0.6406   0.00924   0.00185  -0.1238   0.6297   0.0349
   0.750   0.6680   0.00922   0.00179  -0.1237   0.6200   0.0363
   1.000   0.6951   0.00924   0.00178  -0.1235   0.6093   0.0384
   1.250   0.7218   0.00929   0.00179  -0.1233   0.5967   0.0416
   1.500   0.7485   0.00929   0.00184  -0.1231   0.5835   0.0789
   1.750   0.7750   0.00913   0.00194  -0.1231   0.5693   0.2093
   2.000   0.8014   0.00874   0.00214  -0.1232   0.5573   0.4733
   2.250   0.8248   0.00773   0.00226  -0.1222   0.5462   1.0000
   2.500   0.8509   0.00790   0.00234  -0.1219   0.5293   1.0000
   2.750   0.8763   0.00812   0.00244  -0.1215   0.5084   1.0000
   3.000   0.9016   0.00835   0.00256  -0.1210   0.4843   1.0000
   3.250   0.9267   0.00860   0.00270  -0.1206   0.4640   1.0000
   3.500   0.9520   0.00884   0.00285  -0.1202   0.4463   1.0000
   3.750   0.9773   0.00909   0.00302  -0.1198   0.4285   1.0000
   4.000   1.0023   0.00936   0.00321  -0.1193   0.4107   1.0000
   4.250   1.0263   0.00970   0.00343  -0.1187   0.3874   1.0000
   4.500   1.0508   0.01000   0.00365  -0.1182   0.3684   1.0000
   4.750   1.0748   0.01033   0.00390  -0.1177   0.3468   1.0000
   5.000   1.0981   0.01073   0.00417  -0.1170   0.3221   1.0000
   5.250   1.1208   0.01117   0.00448  -0.1162   0.2944   1.0000
   5.500   1.1425   0.01168   0.00482  -0.1153   0.2584   1.0000
   5.750   1.1588   0.01266   0.00542  -0.1136   0.1877   1.0000
   6.000   1.1791   0.01328   0.00589  -0.1125   0.1607   1.0000
   6.250   1.2007   0.01376   0.00631  -0.1116   0.1430   1.0000
   6.500   1.2162   0.01474   0.00697  -0.1098   0.0894   1.0000
   6.750   1.2356   0.01535   0.00752  -0.1085   0.0720   1.0000
   7.000   1.2540   0.01602   0.00808  -0.1071   0.0471   1.0000
   7.250   1.2729   0.01661   0.00861  -0.1058   0.0383   1.0000
   7.500   1.2924   0.01713   0.00914  -0.1045   0.0350   1.0000
   7.750   1.3112   0.01767   0.00972  -0.1031   0.0321   1.0000
   8.000   1.3298   0.01813   0.01023  -0.1017   0.0308   1.0000
   8.250   1.3473   0.01861   0.01077  -0.1001   0.0294   1.0000
   8.500   1.3637   0.01917   0.01138  -0.0983   0.0279   1.0000
   8.750   1.3789   0.01981   0.01207  -0.0965   0.0263   1.0000
   9.000   1.3918   0.02061   0.01293  -0.0943   0.0245   1.0000
   9.250   1.4071   0.02125   0.01363  -0.0926   0.0234   1.0000
   9.500   1.4230   0.02186   0.01431  -0.0910   0.0222   1.0000
   9.750   1.4377   0.02255   0.01506  -0.0893   0.0208   1.0000
  10.000   1.4515   0.02332   0.01587  -0.0876   0.0194   1.0000
  10.250   1.4627   0.02428   0.01688  -0.0856   0.0180   1.0000
  10.500   1.4760   0.02511   0.01778  -0.0839   0.0170   1.0000
  10.750   1.4887   0.02601   0.01874  -0.0823   0.0159   1.0000
  11.000   1.5003   0.02701   0.01979  -0.0806   0.0149   1.0000
  11.250   1.5104   0.02814   0.02095  -0.0788   0.0140   1.0000
  11.500   1.5186   0.02946   0.02235  -0.0769   0.0132   1.0000
  11.750   1.5277   0.03075   0.02373  -0.0753   0.0125   1.0000
  12.000   1.5361   0.03211   0.02518  -0.0737   0.0118   1.0000
  12.250   1.5440   0.03357   0.02671  -0.0721   0.0112   1.0000
  12.500   1.5504   0.03521   0.02840  -0.0706   0.0106   1.0000
  12.750   1.5535   0.03719   0.03046  -0.0690   0.0101   1.0000
  13.000   1.5576   0.03915   0.03253  -0.0676   0.0098   1.0000
  13.250   1.5614   0.04121   0.03472  -0.0663   0.0094   1.0000
  13.500   1.5641   0.04342   0.03704  -0.0652   0.0091   1.0000
  13.750   1.5661   0.04578   0.03950  -0.0641   0.0088   1.0000
  14.000   1.5676   0.04827   0.04211  -0.0632   0.0085   1.0000
  14.250   1.5687   0.05089   0.04483  -0.0625   0.0083   1.0000
  14.500   1.5689   0.05370   0.04773  -0.0619   0.0080   1.0000
  14.750   1.5679   0.05672   0.05085  -0.0614   0.0078   1.0000
  15.000   1.5649   0.06008   0.05431  -0.0611   0.0076   1.0000
  15.250   1.5590   0.06390   0.05824  -0.0610   0.0074   1.0000
  15.500   1.5553   0.06751   0.06198  -0.0610   0.0072   1.0000
  15.750   1.5523   0.07110   0.06572  -0.0611   0.0071   1.0000
  16.000   1.5486   0.07489   0.06963  -0.0614   0.0069   1.0000
  16.250   1.5438   0.07889   0.07376  -0.0618   0.0068   1.0000
  16.500   1.5387   0.08299   0.07799  -0.0624   0.0066   1.0000
  16.750   1.5326   0.08734   0.08247  -0.0632   0.0065   1.0000
  17.000   1.5262   0.09183   0.08708  -0.0641   0.0064   1.0000
  17.250   1.5193   0.09648   0.09186  -0.0653   0.0063   1.0000
  17.500   1.5116   0.10131   0.09681  -0.0666   0.0062   1.0000
  17.750   1.5040   0.10620   0.10182  -0.0680   0.0061   1.0000
  18.000   1.4956   0.11130   0.10705  -0.0697   0.0060   1.0000
  18.250   1.4874   0.11648   0.11234  -0.0716   0.0059   1.0000
  18.500   1.4788   0.12181   0.11779  -0.0736   0.0058   1.0000
  18.750   1.4699   0.12723   0.12334  -0.0759   0.0058   1.0000
  19.000   1.4609   0.13278   0.12900  -0.0783   0.0057   1.0000
  19.250   1.4517   0.13847   0.13480  -0.0810   0.0056   1.0000
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