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GOE 427 AIRFOIL (goe427-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 427 AIRFOIL (goe427-il)
Reynolds number: 200,000
Max Cl/Cd: 86.24 at α=2.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe427-il-200000-n5.txt
Download as CSV file: xf-goe427-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 427 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3235   0.10099   0.09763  -0.0232   1.0000   0.0181
  -7.750  -0.3296   0.09995   0.09666  -0.0216   1.0000   0.0183
  -7.500  -0.3384   0.09903   0.09581  -0.0193   1.0000   0.0185
  -7.250  -0.3199   0.09594   0.09273  -0.0255   0.9959   0.0187
  -7.000  -0.2951   0.09211   0.08889  -0.0328   0.9910   0.0189
  -6.750  -0.2672   0.08797   0.08473  -0.0405   0.9870   0.0190
  -6.500  -0.2420   0.08386   0.08059  -0.0463   0.9815   0.0191
  -6.250  -0.2121   0.07937   0.07607  -0.0531   0.9780   0.0191
  -6.000  -0.1868   0.07525   0.07192  -0.0583   0.9717   0.0191
  -4.750  -0.0330   0.05341   0.04976  -0.0860   0.9472   0.0192
  -4.500  -0.0115   0.04834   0.04465  -0.0891   0.9433   0.0167
  -4.250   0.0315   0.04367   0.03984  -0.0962   0.9408   0.0157
  -4.000   0.0639   0.03984   0.03587  -0.1000   0.9327   0.0152
  -3.750   0.1071   0.03532   0.03112  -0.1057   0.9289   0.0150
  -3.500   0.1443   0.03119   0.02673  -0.1093   0.9222   0.0160
  -3.250   0.1849   0.02629   0.02142  -0.1128   0.9168   0.0178
  -3.000   0.2254   0.02064   0.01510  -0.1158   0.9136   0.0185
  -2.750   0.2535   0.01742   0.01123  -0.1160   0.9056   0.0203
  -2.500   0.2856   0.01687   0.01057  -0.1171   0.9007   0.0245
  -2.250   0.3150   0.01508   0.00825  -0.1171   0.8935   0.0281
  -2.000   0.3467   0.01412   0.00696  -0.1177   0.8876   0.0334
  -1.750   0.3756   0.01349   0.00618  -0.1179   0.8797   0.0377
  -1.500   0.4074   0.01291   0.00540  -0.1184   0.8730   0.0418
  -1.250   0.4356   0.01210   0.00447  -0.1184   0.8639   0.0446
  -1.000   0.4655   0.01160   0.00392  -0.1187   0.8552   0.0479
  -0.750   0.4956   0.01126   0.00350  -0.1190   0.8454   0.0510
  -0.500   0.5244   0.01104   0.00318  -0.1190   0.8325   0.0555
  -0.250   0.5530   0.01078   0.00285  -0.1189   0.8185   0.0574
   0.000   0.5811   0.01060   0.00259  -0.1188   0.8040   0.0610
   0.250   0.6086   0.01047   0.00244  -0.1185   0.7901   0.0694
   0.500   0.6355   0.01033   0.00239  -0.1182   0.7762   0.1160
   0.750   0.6618   0.01020   0.00239  -0.1179   0.7618   0.1821
   1.000   0.6874   0.01001   0.00245  -0.1174   0.7470   0.3051
   1.500   0.7482   0.00897   0.00249  -0.1184   0.7153   1.0000
   1.750   0.7735   0.00911   0.00253  -0.1178   0.6975   1.0000
   2.000   0.7979   0.00929   0.00259  -0.1169   0.6713   1.0000
   2.250   0.8210   0.00952   0.00264  -0.1158   0.6345   1.0000
   2.500   0.8424   0.00985   0.00269  -0.1143   0.5873   1.0000
   2.750   0.8643   0.01021   0.00283  -0.1130   0.5530   1.0000
   3.000   0.8870   0.01056   0.00305  -0.1120   0.5271   1.0000
   3.250   0.9095   0.01092   0.00327  -0.1110   0.5001   1.0000
   3.500   0.9328   0.01123   0.00351  -0.1101   0.4771   1.0000
   3.750   0.9563   0.01152   0.00376  -0.1093   0.4542   1.0000
   4.000   0.9792   0.01184   0.00405  -0.1084   0.4257   1.0000
   4.250   1.0012   0.01222   0.00434  -0.1073   0.3903   1.0000
   4.500   1.0221   0.01271   0.00467  -0.1061   0.3488   1.0000
   4.750   1.0403   0.01345   0.00513  -0.1046   0.2873   1.0000
   5.000   1.0533   0.01485   0.00590  -0.1024   0.1671   1.0000
   5.250   1.0679   0.01619   0.00679  -0.1005   0.0815   1.0000
   5.500   1.0878   0.01694   0.00748  -0.0992   0.0522   1.0000
   5.750   1.1073   0.01770   0.00821  -0.0979   0.0427   1.0000
   6.000   1.1271   0.01841   0.00905  -0.0966   0.0373   1.0000
   6.250   1.1450   0.01931   0.01008  -0.0950   0.0321   1.0000
   6.500   1.1626   0.02020   0.01116  -0.0934   0.0262   1.0000
   6.750   1.1786   0.02123   0.01234  -0.0915   0.0220   1.0000
   7.000   1.1958   0.02211   0.01335  -0.0898   0.0169   1.0000
   7.250   1.2091   0.02335   0.01467  -0.0875   0.0140   1.0000
   7.500   1.2191   0.02498   0.01642  -0.0847   0.0127   1.0000
   7.750   1.2327   0.02632   0.01789  -0.0825   0.0114   1.0000
   8.000   1.2484   0.02728   0.01895  -0.0808   0.0099   1.0000
   8.250   1.2613   0.02847   0.02030  -0.0787   0.0090   1.0000
   8.500   1.2718   0.03063   0.02258  -0.0762   0.0084   1.0000
   8.750   1.2877   0.03346   0.02564  -0.0746   0.0079   1.0000
   9.000   1.3049   0.03615   0.02864  -0.0732   0.0076   1.0000
   9.250   1.3194   0.03909   0.03193  -0.0714   0.0073   1.0000
   9.500   1.3287   0.04168   0.03486  -0.0690   0.0068   1.0000
   9.750   1.3336   0.04385   0.03730  -0.0661   0.0063   1.0000
  10.000   1.3354   0.04549   0.03913  -0.0632   0.0059   1.0000
  10.250   1.3340   0.04769   0.04157  -0.0602   0.0056   1.0000
  10.500   1.3292   0.05067   0.04484  -0.0572   0.0056   1.0000
  10.750   1.3215   0.05378   0.04821  -0.0544   0.0055   1.0000
  11.000   1.3109   0.05723   0.05192  -0.0520   0.0054   1.0000
  11.250   1.2980   0.06115   0.05610  -0.0501   0.0054   1.0000
  11.500   1.2835   0.06550   0.06072  -0.0490   0.0054   1.0000
  11.750   1.2676   0.07024   0.06571  -0.0487   0.0054   1.0000
  12.000   1.2506   0.07552   0.07122  -0.0493   0.0054   1.0000
  12.250   1.2322   0.08159   0.07754  -0.0509   0.0054   1.0000
  12.500   1.2133   0.08818   0.08434  -0.0535   0.0054   1.0000
  12.750   1.1918   0.09620   0.09258  -0.0574   0.0055   1.0000
  13.000   1.1703   0.10496   0.10153  -0.0623   0.0056   1.0000
  13.250   1.1459   0.11563   0.11239  -0.0690   0.0058   1.0000
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