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GOE 360 AIRFOIL (goe360-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 360 AIRFOIL (goe360-il)
Reynolds number: 500,000
Max Cl/Cd: 105.29 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe360-il-500000.txt
Download as CSV file: xf-goe360-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 360 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.1462   0.09019   0.08814  -0.0432   0.9443   0.0189
  -9.000  -0.1421   0.08736   0.08527  -0.0432   0.9305   0.0192
  -8.750  -0.2393   0.09754   0.09546  -0.0361   0.9786   0.0187
  -8.500  -0.2246   0.09402   0.09193  -0.0382   0.9621   0.0189
  -8.250  -0.2150   0.09114   0.08902  -0.0396   0.9436   0.0192
  -8.000  -0.2090   0.08860   0.08642  -0.0402   0.9272   0.0195
  -7.750  -0.2029   0.08600   0.08378  -0.0411   0.9134   0.0199
  -7.500  -0.1959   0.08327   0.08101  -0.0426   0.9013   0.0204
  -7.250  -0.1878   0.08042   0.07812  -0.0450   0.8903   0.0211
  -7.000  -0.1711   0.07692   0.07455  -0.0516   0.8795   0.0220
  -6.750  -0.1438   0.07231   0.06984  -0.0642   0.8678   0.0222
  -6.500  -0.1258   0.06780   0.06526  -0.0685   0.8578   0.0223
  -6.250  -0.1168   0.06469   0.06212  -0.0671   0.8481   0.0225
  -6.000  -0.1022   0.06188   0.05928  -0.0677   0.8366   0.0228
  -5.750  -0.0838   0.05906   0.05639  -0.0697   0.8243   0.0231
  -5.500  -0.0626   0.05614   0.05339  -0.0725   0.8114   0.0237
  -5.250  -0.0391   0.05312   0.05027  -0.0756   0.7974   0.0244
  -5.000   0.0032   0.04947   0.04634  -0.0827   0.7823   0.0266
  -4.750   0.0362   0.04604   0.04262  -0.0863   0.7662   0.0268
  -4.500   0.0557   0.04183   0.03828  -0.0879   0.7495   0.0271
  -4.250   0.0753   0.03946   0.03581  -0.0885   0.7317   0.0274
  -4.000   0.0977   0.03741   0.03363  -0.0893   0.7151   0.0278
  -3.750   0.1222   0.03548   0.03154  -0.0902   0.7001   0.0285
  -3.500   0.1490   0.03348   0.02936  -0.0912   0.6867   0.0297
  -3.250   0.1866   0.03190   0.02737  -0.0921   0.6753   0.0323
  -2.750   0.2394   0.02653   0.02154  -0.0935   0.6559   0.0332
  -2.500   0.2642   0.02500   0.01991  -0.0940   0.6468   0.0337
  -2.250   0.2902   0.02376   0.01854  -0.0944   0.6375   0.0345
  -2.000   0.3175   0.02257   0.01720  -0.0946   0.6292   0.0359
  -1.750   0.3489   0.02215   0.01646  -0.0942   0.6211   0.0392
  -1.500   0.3777   0.02021   0.01415  -0.0943   0.6138   0.0403
  -1.250   0.4037   0.01868   0.01258  -0.0947   0.6055   0.0412
  -1.000   0.4308   0.01778   0.01161  -0.0949   0.5973   0.0424
  -0.750   0.4585   0.01707   0.01075  -0.0949   0.5889   0.0446
  -0.500   0.4885   0.01779   0.01122  -0.0944   0.5803   0.0485
  -0.250   0.5151   0.01555   0.00885  -0.0948   0.5723   0.0509
   0.000   0.5428   0.01490   0.00816  -0.0949   0.5630   0.0533
   1.500   0.7107   0.01190   0.00437  -0.0938   0.4978   0.0499
   1.750   0.7381   0.01186   0.00426  -0.0936   0.4849   0.0490
   2.000   0.7649   0.01134   0.00372  -0.0934   0.4728   0.0466
   2.250   0.7917   0.01115   0.00347  -0.0932   0.4614   0.0460
   2.500   0.8185   0.01106   0.00333  -0.0930   0.4503   0.0464
   2.750   0.8456   0.01102   0.00325  -0.0930   0.4398   0.0473
   3.000   0.8725   0.01105   0.00324  -0.0928   0.4301   0.0484
   3.250   0.8993   0.01104   0.00318  -0.0928   0.4207   0.0517
   3.500   0.9264   0.01109   0.00323  -0.0927   0.4124   0.0553
   3.750   0.9531   0.01123   0.00330  -0.0926   0.4047   0.0599
   4.000   0.9767   0.00965   0.00355  -0.0921   0.3982   1.0000
   4.250   1.0032   0.00987   0.00367  -0.0920   0.3912   1.0000
   4.500   1.0297   0.01008   0.00383  -0.0919   0.3849   1.0000
   4.750   1.0563   0.01027   0.00399  -0.0918   0.3785   1.0000
   5.000   1.0821   0.01055   0.00419  -0.0916   0.3726   1.0000
   5.250   1.1090   0.01070   0.00437  -0.0915   0.3675   1.0000
   5.500   1.1353   0.01092   0.00458  -0.0914   0.3623   1.0000
   5.750   1.1607   0.01123   0.00483  -0.0912   0.3574   1.0000
   6.000   1.1874   0.01138   0.00504  -0.0911   0.3528   1.0000
   6.250   1.2131   0.01161   0.00526  -0.0909   0.3461   1.0000
   6.500   1.2387   0.01185   0.00549  -0.0907   0.3396   1.0000
   6.750   1.2645   0.01204   0.00571  -0.0906   0.3331   1.0000
   7.000   1.2894   0.01231   0.00596  -0.0903   0.3257   1.0000
   7.250   1.3151   0.01249   0.00619  -0.0902   0.3190   1.0000
   7.500   1.3393   0.01282   0.00648  -0.0898   0.3122   1.0000
   7.750   1.3649   0.01297   0.00669  -0.0896   0.3030   1.0000
   8.000   1.3892   0.01325   0.00699  -0.0893   0.2945   1.0000
   8.250   1.4132   0.01353   0.00727  -0.0889   0.2849   1.0000
   8.500   1.4368   0.01384   0.00757  -0.0885   0.2706   1.0000
   8.750   1.4585   0.01429   0.00794  -0.0879   0.2457   1.0000
   9.000   1.4643   0.01606   0.00910  -0.0852   0.1578   1.0000
   9.250   1.4460   0.01957   0.01181  -0.0794   0.0407   1.0000
   9.500   1.4501   0.02092   0.01309  -0.0762   0.0263   1.0000
   9.750   1.4613   0.02182   0.01408  -0.0741   0.0240   1.0000
  10.000   1.4696   0.02296   0.01530  -0.0719   0.0221   1.0000
  10.250   1.4753   0.02436   0.01679  -0.0697   0.0206   1.0000
  10.500   1.4845   0.02557   0.01810  -0.0680   0.0198   1.0000
  10.750   1.4913   0.02702   0.01965  -0.0664   0.0189   1.0000
  11.000   1.4958   0.02873   0.02146  -0.0647   0.0181   1.0000
  11.250   1.4979   0.03076   0.02359  -0.0632   0.0175   1.0000
  11.500   1.4953   0.03335   0.02628  -0.0617   0.0170   1.0000
  11.750   1.4882   0.03660   0.02967  -0.0605   0.0166   1.0000
  12.000   1.4767   0.04057   0.03378  -0.0597   0.0163   1.0000
  12.250   1.4763   0.04351   0.03683  -0.0594   0.0161   1.0000
  12.500   1.4739   0.04677   0.04020  -0.0592   0.0158   1.0000
  12.750   1.4697   0.05032   0.04388  -0.0591   0.0156   1.0000
  13.000   1.4641   0.05407   0.04774  -0.0591   0.0154   1.0000
  13.250   1.4579   0.05795   0.05173  -0.0592   0.0151   1.0000
  13.500   1.4517   0.06192   0.05581  -0.0595   0.0148   1.0000
  13.750   1.4456   0.06594   0.05992  -0.0598   0.0145   1.0000
  14.000   1.4393   0.07002   0.06409  -0.0601   0.0143   1.0000
  14.250   1.4337   0.07408   0.06824  -0.0606   0.0140   1.0000
  14.500   1.4278   0.07820   0.07243  -0.0611   0.0137   1.0000
  14.750   1.4224   0.08223   0.07653  -0.0615   0.0135   1.0000
  15.000   1.4176   0.08617   0.08053  -0.0619   0.0133   1.0000
  15.250   1.4139   0.08981   0.08422  -0.0621   0.0131   1.0000
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