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GOE 54 AIRFOIL (goe54-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 54 AIRFOIL (goe54-il)
Reynolds number: 200,000
Max Cl/Cd: 58.66 at α=10.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe54-il-200000.txt
Download as CSV file: xf-goe54-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4468   0.09961   0.09643   0.0284   1.0000   0.0285
  -8.250  -0.4429   0.09597   0.09282   0.0277   1.0000   0.0289
  -8.000  -0.5522   0.10343   0.10012   0.0339   1.0000   0.0279
  -7.750  -0.5439   0.09948   0.09620   0.0344   1.0000   0.0282
  -7.500  -0.5365   0.09592   0.09266   0.0330   1.0000   0.0285
  -7.250  -0.5265   0.09224   0.08900   0.0304   1.0000   0.0290
  -7.000  -0.5147   0.08845   0.08523   0.0269   1.0000   0.0295
  -6.750  -0.5008   0.08453   0.08131   0.0228   1.0000   0.0301
  -6.500  -0.4842   0.08048   0.07725   0.0181   1.0000   0.0309
  -6.250  -0.4600   0.07620   0.07291   0.0107   1.0000   0.0319
  -6.000  -0.4239   0.07119   0.06767  -0.0009   1.0000   0.0325
  -5.750  -0.4138   0.06721   0.06378   0.0003   1.0000   0.0328
  -5.500  -0.3976   0.06361   0.06019  -0.0007   1.0000   0.0333
  -5.250  -0.3767   0.06007   0.05662  -0.0029   1.0000   0.0340
  -5.000  -0.3523   0.05654   0.05302  -0.0057   1.0000   0.0349
  -4.750  -0.3244   0.05306   0.04942  -0.0088   1.0000   0.0363
  -4.500  -0.2798   0.05004   0.04590  -0.0141   1.0000   0.0380
  -4.250  -0.2627   0.04613   0.04213  -0.0146   1.0000   0.0385
  -4.000  -0.2398   0.04316   0.03916  -0.0157   1.0000   0.0394
  -3.750  -0.2126   0.04047   0.03639  -0.0170   1.0000   0.0407
  -3.500  -0.1815   0.03808   0.03385  -0.0184   1.0000   0.0428
  -3.250  -0.1398   0.03608   0.03110  -0.0204   0.7765   0.0446
  -3.000  -0.1226   0.03407   0.02855  -0.0193   0.6557   0.0454
  -2.750  -0.0977   0.03232   0.02644  -0.0195   0.6005   0.0472
  -2.250  -0.0383   0.02929   0.02255  -0.0200   0.5442   0.0527
  -2.000  -0.0115   0.02759   0.02066  -0.0204   0.5250   0.0549
  -1.750   0.0213   0.02781   0.02027  -0.0199   0.5086   0.0604
  -1.500   0.0470   0.02502   0.01750  -0.0207   0.4941   0.0627
  -1.000   0.1039   0.02277   0.01480  -0.0211   0.4663   0.0753
  -0.750   0.1320   0.02180   0.01363  -0.0213   0.4524   0.0878
  -0.500   0.1601   0.02102   0.01262  -0.0216   0.4377   0.1119
  -0.250   0.1873   0.01985   0.01142  -0.0219   0.4224   0.1330
   0.000   0.2150   0.01878   0.01026  -0.0222   0.4070   0.1609
   0.250   0.2435   0.01809   0.00946  -0.0222   0.3919   0.1830
   0.500   0.2725   0.01725   0.00853  -0.0221   0.3780   0.1969
   0.750   0.3024   0.01670   0.00783  -0.0217   0.3659   0.1942
   1.250   0.3632   0.01619   0.00691  -0.0202   0.3446   0.1460
   1.500   0.3930   0.01620   0.00673  -0.0193   0.3350   0.1203
   1.750   0.4221   0.01597   0.00635  -0.0186   0.3261   0.1003
   2.000   0.4508   0.01579   0.00612  -0.0181   0.3175   0.0894
   2.250   0.4793   0.01585   0.00605  -0.0176   0.3104   0.0816
   2.500   0.5076   0.01551   0.00576  -0.0174   0.3039   0.0778
   2.750   0.5359   0.01535   0.00561  -0.0172   0.2973   0.0754
   3.000   0.5640   0.01534   0.00556  -0.0171   0.2915   0.0773
   3.250   0.5925   0.01532   0.00556  -0.0170   0.2851   0.0767
   3.500   0.6206   0.01542   0.00557  -0.0168   0.2797   0.0765
   3.750   0.6488   0.01562   0.00572  -0.0166   0.2744   0.0775
   4.000   0.6769   0.01578   0.00588  -0.0164   0.2686   0.0800
   4.250   0.7046   0.01603   0.00605  -0.0162   0.2633   0.0906
   4.500   0.7277   0.01452   0.00640  -0.0152   0.2583   1.0000
   4.750   0.7555   0.01483   0.00667  -0.0150   0.2523   1.0000
   5.000   0.7828   0.01533   0.00701  -0.0148   0.2470   1.0000
   5.250   0.8105   0.01569   0.00744  -0.0146   0.2410   1.0000
   5.500   0.8379   0.01607   0.00778  -0.0144   0.2351   1.0000
   5.750   0.8649   0.01671   0.00834  -0.0143   0.2299   1.0000
   6.000   0.8923   0.01707   0.00884  -0.0142   0.2236   1.0000
   6.250   0.9194   0.01751   0.00922  -0.0140   0.2183   1.0000
   6.500   0.9461   0.01823   0.00996  -0.0139   0.2135   1.0000
   6.750   0.9731   0.01868   0.01058  -0.0137   0.2082   1.0000
   7.000   0.9999   0.01904   0.01091  -0.0135   0.2032   1.0000
   7.250   1.0262   0.01960   0.01148  -0.0134   0.1980   1.0000
   7.500   1.0529   0.01985   0.01192  -0.0132   0.1921   1.0000
   7.750   1.0794   0.02015   0.01222  -0.0130   0.1877   1.0000
   8.000   1.1054   0.02074   0.01283  -0.0129   0.1835   1.0000
   8.250   1.1317   0.02094   0.01327  -0.0127   0.1778   1.0000
   8.500   1.1579   0.02112   0.01347  -0.0125   0.1732   1.0000
   8.750   1.1836   0.02159   0.01400  -0.0123   0.1690   1.0000
   9.000   1.2095   0.02184   0.01447  -0.0121   0.1633   1.0000
   9.250   1.2354   0.02187   0.01451  -0.0118   0.1580   1.0000
   9.500   1.2609   0.02215   0.01501  -0.0117   0.1512   1.0000
   9.750   1.2863   0.02220   0.01503  -0.0114   0.1439   1.0000
  10.000   1.3115   0.02236   0.01543  -0.0113   0.1338   1.0000
  10.250   1.3356   0.02277   0.01594  -0.0112   0.1210   1.0000
  10.500   1.3578   0.02363   0.01681  -0.0111   0.1056   1.0000
  10.750   1.3793   0.02475   0.01801  -0.0110   0.0908   1.0000
  11.000   1.4001   0.02593   0.01927  -0.0109   0.0795   1.0000
  11.250   1.4189   0.02736   0.02073  -0.0107   0.0715   1.0000
  11.500   1.4360   0.02901   0.02251  -0.0104   0.0656   1.0000
  11.750   1.4475   0.03126   0.02473  -0.0100   0.0608   1.0000
  12.000   1.4606   0.03322   0.02694  -0.0096   0.0572   1.0000
  12.250   1.4690   0.03554   0.02938  -0.0094   0.0539   1.0000
  12.500   1.4696   0.03858   0.03237  -0.0086   0.0513   1.0000
  12.750   1.4709   0.04134   0.03544  -0.0088   0.0496   1.0000
  13.000   1.4645   0.04510   0.03941  -0.0103   0.0482   1.0000
  13.250   1.4581   0.05015   0.04463  -0.0145   0.0470   1.0000
  13.500   1.4514   0.05519   0.04978  -0.0180   0.0458   1.0000
  13.750   1.4443   0.05989   0.05453  -0.0204   0.0446   1.0000
  14.000   1.4380   0.06368   0.05831  -0.0207   0.0432   1.0000
  14.250   1.4265   0.06909   0.06386  -0.0234   0.0424   1.0000
  14.500   1.4127   0.07506   0.07002  -0.0269   0.0419   1.0000
  14.750   1.3976   0.08121   0.07634  -0.0303   0.0414   1.0000
  15.000   1.3813   0.08756   0.08285  -0.0337   0.0410   1.0000
  15.250   1.3640   0.09418   0.08963  -0.0373   0.0406   1.0000
  15.500   1.3450   0.10121   0.09682  -0.0411   0.0402   1.0000
  15.750   1.3246   0.10897   0.10474  -0.0454   0.0400   1.0000
  16.000   1.3002   0.11804   0.11397  -0.0507   0.0400   1.0000
  16.250   1.2690   0.12916   0.12529  -0.0574   0.0403   1.0000
  16.500   1.2197   0.14528   0.14162  -0.0673   0.0414   1.0000
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