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GOE 422 AIRFOIL (goe422-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 422 AIRFOIL (goe422-il)
Reynolds number: 50,000
Max Cl/Cd: 19.38 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe422-il-50000-n5.txt
Download as CSV file: xf-goe422-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 422 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.0906   0.12695   0.11976  -0.0763   0.9333   0.1366
  -9.500  -0.0967   0.12522   0.11805  -0.0813   0.9275   0.1398
  -9.250  -0.1076   0.12373   0.11661  -0.0825   0.9176   0.1403
  -9.000  -0.0817   0.11886   0.11174  -0.0839   0.9141   0.1415
  -8.750  -0.0635   0.11537   0.10823  -0.0845   0.9088   0.1431
  -8.500  -0.0554   0.11271   0.10559  -0.0849   0.9015   0.1445
  -8.250  -0.0408   0.10931   0.10217  -0.0878   0.8973   0.1457
  -8.000  -0.0576   0.10483   0.09765  -0.0892   0.8865   0.1093
  -7.750  -0.0760   0.09937   0.09214  -0.0928   0.8784   0.0906
  -7.500  -0.0766   0.09715   0.08996  -0.0919   0.8698   0.0897
  -6.750  -0.0741   0.08731   0.08011  -0.0969   0.8485   0.0870
  -6.500  -0.0904   0.08499   0.07781  -0.0955   0.8370   0.0859
  -6.250  -0.0972   0.07638   0.06890  -0.1043   0.8306   0.0822
  -6.000  -0.1052   0.07460   0.06711  -0.1018   0.8199   0.0818
  -5.750  -0.0914   0.07071   0.06305  -0.1042   0.8144   0.0813
  -5.500  -0.0702   0.06607   0.05815  -0.1081   0.8108   0.0808
  -5.250  -0.0791   0.06434   0.05630  -0.1053   0.7991   0.0805
  -5.000  -0.0574   0.06019   0.05179  -0.1082   0.7943   0.0805
  -4.750  -0.0279   0.05578   0.04680  -0.1120   0.7910   0.0816
  -4.500  -0.0292   0.05426   0.04495  -0.1095   0.7798   0.0824
  -4.250  -0.0018   0.05277   0.04338  -0.1105   0.7749   0.0841
  -4.000   0.0325   0.05043   0.04071  -0.1126   0.7715   0.0860
  -3.750   0.0396   0.04962   0.03966  -0.1105   0.7615   0.0868
  -3.500   0.0676   0.04782   0.03746  -0.1113   0.7559   0.0883
  -3.250   0.1043   0.04577   0.03482  -0.1131   0.7523   0.0911
  -3.000   0.1221   0.04534   0.03438  -0.1121   0.7446   0.0936
  -2.750   0.1429   0.04481   0.03371  -0.1115   0.7369   0.0969
  -2.500   0.1792   0.04345   0.03189  -0.1126   0.7330   0.1013
  -2.250   0.2179   0.04215   0.03057  -0.1140   0.7301   0.1063
  -2.000   0.2211   0.04274   0.03107  -0.1110   0.7177   0.1100
  -1.750   0.2560   0.04172   0.02995  -0.1118   0.7135   0.1173
  -1.500   0.2955   0.04054   0.02863  -0.1129   0.7106   0.1281
  -1.250   0.2990   0.04131   0.02945  -0.1100   0.6978   0.1340
  -1.000   0.3356   0.04036   0.02845  -0.1108   0.6938   0.1491
  -0.750   0.3510   0.04068   0.02879  -0.1094   0.6839   0.1619
  -0.500   0.3802   0.04020   0.02833  -0.1094   0.6775   0.1830
  -0.250   0.4191   0.03914   0.02737  -0.1104   0.6740   0.2158
   0.000   0.4275   0.03995   0.02831  -0.1083   0.6620   0.2424
   0.250   0.4628   0.03888   0.02762  -0.1091   0.6574   0.3244
   0.500   0.4955   0.03689   0.02689  -0.1085   0.6547   0.5977
   0.750   0.4939   0.03746   0.02809  -0.1037   0.6412   1.0000
   1.000   0.5318   0.03698   0.02719  -0.1044   0.6374   1.0000
   1.250   0.5367   0.03840   0.02845  -0.1020   0.6251   1.0000
   1.500   0.5706   0.03809   0.02785  -0.1023   0.6204   1.0000
   1.750   0.6073   0.03762   0.02710  -0.1029   0.6167   1.0000
   2.000   0.6092   0.03926   0.02866  -0.1003   0.6037   1.0000
   2.250   0.6467   0.03869   0.02785  -0.1009   0.6003   1.0000
   2.500   0.6477   0.04052   0.02962  -0.0984   0.5873   1.0000
   2.750   0.6821   0.04009   0.02900  -0.0987   0.5832   1.0000
   3.250   0.7163   0.04169   0.03038  -0.0965   0.5663   1.0000
   3.500   0.7538   0.04102   0.02955  -0.0970   0.5632   1.0000
   4.000   0.7841   0.04295   0.03131  -0.0946   0.5461   1.0000
   4.250   0.8207   0.04235   0.03057  -0.0950   0.5429   1.0000
   4.500   0.8109   0.04534   0.03359  -0.0922   0.5292   1.0000
   4.750   0.8467   0.04475   0.03288  -0.0924   0.5263   1.0000
   5.250   0.8665   0.04784   0.03590  -0.0898   0.5092   1.0000
   5.500   0.9038   0.04708   0.03503  -0.0900   0.5067   1.0000
   6.000   0.9130   0.05134   0.03929  -0.0871   0.4896   1.0000
   6.250   0.9489   0.05070   0.03856  -0.0873   0.4876   1.0000
   6.750   0.9460   0.05643   0.04434  -0.0842   0.4703   1.0000
   7.250   0.9364   0.06344   0.05143  -0.0817   0.4532   1.0000
   7.500   0.9655   0.06331   0.05126  -0.0814   0.4513   1.0000
   9.000   0.8998   0.09221   0.08050  -0.0783   0.4058   1.0000
   9.250   0.9097   0.09446   0.08278  -0.0780   0.4016   1.0000
   9.500   0.9280   0.09571   0.08405  -0.0776   0.3991   1.0000
   9.750   0.9496   0.09660   0.08495  -0.0773   0.3973   1.0000
  10.250   0.9184   0.10775   0.09625  -0.0777   0.3835   1.0000
  10.500   0.9369   0.10900   0.09753  -0.0774   0.3810   1.0000
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