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GOE 673 AIRFOIL (goe673-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 673 AIRFOIL (goe673-il)
Reynolds number: 200,000
Max Cl/Cd: 74.99 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe673-il-200000.txt
Download as CSV file: xf-goe673-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 673 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4284   0.09326   0.08982  -0.0403   1.0000   0.0470
  -9.000  -0.4346   0.08873   0.08536  -0.0434   1.0000   0.0489
  -8.750  -0.4495   0.08383   0.08058  -0.0476   1.0000   0.0500
  -8.500  -0.3735   0.07353   0.07055  -0.0415   1.0000   0.0559
  -8.250  -0.3880   0.07058   0.06766  -0.0402   1.0000   0.0568
  -8.000  -0.4075   0.06765   0.06481  -0.0386   1.0000   0.0572
  -7.750  -0.4330   0.06490   0.06214  -0.0367   1.0000   0.0568
  -7.500  -0.5468   0.06688   0.06338  -0.0473   1.0000   0.0508
  -7.250  -0.5561   0.06002   0.05656  -0.0468   1.0000   0.0520
  -7.000  -0.5482   0.05801   0.05470  -0.0446   1.0000   0.0535
  -6.750  -0.5437   0.05598   0.05267  -0.0431   1.0000   0.0556
  -6.500  -0.5324   0.05003   0.04589  -0.0482   0.9969   0.0644
  -6.250  -0.5051   0.04667   0.04277  -0.0500   0.9947   0.0679
  -6.000  -0.4781   0.04246   0.03814  -0.0539   0.9901   0.0794
  -5.750  -0.4481   0.03979   0.03533  -0.0567   0.9863   0.0933
  -5.500  -0.4147   0.03779   0.03329  -0.0596   0.9835   0.1102
  -5.250  -0.3693   0.02566   0.01893  -0.0588   0.9819   0.0366
  -5.000  -0.3364   0.02294   0.01580  -0.0596   0.9781   0.0343
  -4.750  -0.2999   0.02098   0.01354  -0.0611   0.9749   0.0337
  -4.500  -0.2617   0.01954   0.01192  -0.0631   0.9722   0.0352
  -4.250  -0.2211   0.01860   0.01085  -0.0656   0.9700   0.0383
  -4.000  -0.1905   0.01726   0.00947  -0.0663   0.9645   0.0401
  -3.750  -0.1533   0.01621   0.00837  -0.0686   0.9605   0.0454
  -3.500  -0.1122   0.01542   0.00750  -0.0714   0.9575   0.0609
  -3.250  -0.0723   0.01344   0.00690  -0.0752   0.9559   0.3530
  -3.000  -0.0437   0.01295   0.00683  -0.0757   0.9484   0.4733
  -2.750  -0.0058   0.01243   0.00670  -0.0778   0.9447   0.5810
  -2.500   0.0338   0.01207   0.00663  -0.0799   0.9421   0.6803
  -2.250   0.0612   0.01190   0.00653  -0.0795   0.9338   0.7279
  -2.000   0.0970   0.01161   0.00630  -0.0807   0.9297   0.7730
  -1.750   0.1241   0.01142   0.00616  -0.0800   0.9221   0.8140
  -1.500   0.1537   0.01117   0.00597  -0.0796   0.9165   0.8573
  -1.250   0.1810   0.01103   0.00586  -0.0786   0.9093   0.9033
  -1.000   0.2186   0.01086   0.00564  -0.0800   0.9035   0.9485
  -0.750   0.2711   0.01064   0.00534  -0.0848   0.9004   0.9829
  -0.500   0.3150   0.01051   0.00514  -0.0884   0.8919   1.0000
  -0.250   0.3410   0.01035   0.00489  -0.0881   0.8831   1.0000
   0.000   0.3670   0.01022   0.00468  -0.0876   0.8736   1.0000
   0.250   0.3917   0.01017   0.00455  -0.0870   0.8626   1.0000
   0.500   0.4179   0.01010   0.00442  -0.0865   0.8522   1.0000
   0.750   0.4452   0.01001   0.00428  -0.0862   0.8425   1.0000
   1.000   0.4716   0.00997   0.00418  -0.0858   0.8313   1.0000
   1.250   0.4976   0.00996   0.00413  -0.0853   0.8190   1.0000
   1.500   0.5240   0.00996   0.00409  -0.0849   0.8066   1.0000
   1.750   0.5507   0.00997   0.00408  -0.0845   0.7938   1.0000
   2.000   0.5774   0.00999   0.00407  -0.0841   0.7805   1.0000
   2.250   0.6041   0.01003   0.00407  -0.0838   0.7667   1.0000
   2.500   0.6308   0.01009   0.00412  -0.0834   0.7522   1.0000
   2.750   0.6574   0.01016   0.00417  -0.0831   0.7371   1.0000
   3.000   0.6840   0.01025   0.00424  -0.0827   0.7218   1.0000
   3.250   0.7107   0.01037   0.00434  -0.0824   0.7064   1.0000
   3.500   0.7373   0.01052   0.00449  -0.0821   0.6910   1.0000
   3.750   0.7636   0.01069   0.00466  -0.0817   0.6751   1.0000
   4.000   0.7898   0.01088   0.00488  -0.0814   0.6588   1.0000
   4.250   0.8154   0.01107   0.00508  -0.0809   0.6392   1.0000
   4.500   0.8380   0.01124   0.00515  -0.0795   0.6040   1.0000
   4.750   0.8601   0.01147   0.00529  -0.0782   0.5659   1.0000
   5.000   0.8806   0.01179   0.00547  -0.0767   0.5159   1.0000
   5.250   0.8984   0.01235   0.00576  -0.0747   0.4447   1.0000
   5.500   0.8934   0.01492   0.00677  -0.0695   0.1843   1.0000
   5.750   0.8969   0.01749   0.00847  -0.0659   0.0481   1.0000
   6.000   0.9154   0.01847   0.00961  -0.0643   0.0406   1.0000
   6.250   0.9312   0.01960   0.01084  -0.0623   0.0367   1.0000
   6.500   0.9405   0.02129   0.01259  -0.0593   0.0341   1.0000
   6.750   0.9587   0.02220   0.01359  -0.0578   0.0316   1.0000
   7.000   0.9745   0.02349   0.01495  -0.0558   0.0299   1.0000
   7.250   0.9923   0.02498   0.01647  -0.0541   0.0288   1.0000
   7.500   1.0141   0.02669   0.01823  -0.0530   0.0281   1.0000
   7.750   1.0414   0.02876   0.02043  -0.0527   0.0279   1.0000
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