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GOE 388 AIRFOIL (goe388-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 388 AIRFOIL (goe388-il)
Reynolds number: 200,000
Max Cl/Cd: 36.22 at α=2°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe388-il-200000-n5.txt
Download as CSV file: xf-goe388-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 388 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2454   0.10178   0.09517  -0.0470   0.1019   0.0376
  -8.750  -0.2431   0.09886   0.09227  -0.0512   0.1018   0.0382
  -8.500  -0.2376   0.09558   0.08900  -0.0542   0.1017   0.0384
  -8.250  -0.2318   0.09221   0.08565  -0.0570   0.1016   0.0385
  -8.000  -0.1613   0.07919   0.07287  -0.0632   0.0992   0.0387
  -7.750  -0.2152   0.08519   0.07863  -0.0639   0.1002   0.0386
  -7.500  -0.2037   0.08083   0.07426  -0.0689   0.0995   0.0388
  -7.250  -0.1998   0.07714   0.07059  -0.0661   0.0984   0.0399
  -7.000  -0.1871   0.07495   0.06838  -0.0660   0.0980   0.0409
  -6.750  -0.1732   0.07208   0.06550  -0.0684   0.0974   0.0417
  -6.500  -0.1577   0.06890   0.06228  -0.0719   0.0967   0.0426
  -6.000  -0.1105   0.05664   0.04972  -0.0891   0.0959   0.0377
  -5.500  -0.0587   0.04678   0.03940  -0.0992   0.0943   0.0385
  -5.250  -0.0396   0.04325   0.03575  -0.1011   0.0932   0.0376
  -5.000  -0.0152   0.03924   0.03148  -0.1037   0.0921   0.0371
  -4.750   0.0106   0.03536   0.02727  -0.1060   0.0912   0.0370
  -4.250   0.0630   0.02956   0.02065  -0.1086   0.0676   0.0372
  -4.000   0.0901   0.02800   0.01874  -0.1091   0.0658   0.0382
  -3.750   0.1165   0.02671   0.01718  -0.1094   0.0638   0.0385
  -3.500   0.1427   0.02521   0.01544  -0.1097   0.0617   0.0384
  -3.250   0.1689   0.02405   0.01406  -0.1098   0.0584   0.0384
  -3.000   0.1952   0.02312   0.01292  -0.1098   0.0549   0.0385
  -2.750   0.2215   0.02231   0.01192  -0.1098   0.0530   0.0387
  -2.500   0.2479   0.02122   0.01063  -0.1099   0.0516   0.0392
  -2.250   0.2740   0.02045   0.00972  -0.1099   0.0506   0.0397
  -2.000   0.2998   0.01996   0.00916  -0.1097   0.0495   0.0403
  -1.750   0.3259   0.01954   0.00868  -0.1097   0.0488   0.0410
  -1.500   0.3516   0.01927   0.00838  -0.1095   0.0479   0.0418
  -1.250   0.3770   0.01915   0.00824  -0.1093   0.0474   0.0434
  -1.000   0.4029   0.01898   0.00804  -0.1092   0.0468   0.0452
  -0.750   0.4283   0.01886   0.00790  -0.1090   0.0461   0.0462
  -0.500   0.4525   0.01891   0.00795  -0.1086   0.0456   0.0470
  -0.250   0.4785   0.01875   0.00775  -0.1085   0.0452   0.0479
   0.000   0.5036   0.01875   0.00773  -0.1083   0.0444   0.0491
   0.250   0.5271   0.01899   0.00796  -0.1078   0.0437   0.0502
   0.500   0.5506   0.01917   0.00811  -0.1074   0.0435   0.0530
   0.750   0.5756   0.01922   0.00814  -0.1072   0.0433   0.0571
   1.000   0.6000   0.01937   0.00826  -0.1069   0.0431   0.0632
   1.250   0.6238   0.01942   0.00853  -0.1067   0.0428   0.1162
   1.500   0.6464   0.01930   0.00896  -0.1066   0.0425   0.3297
   2.000   0.6838   0.01888   0.00982  -0.1037   0.0420   1.0000
   2.250   0.7046   0.01954   0.01034  -0.1029   0.0418   1.0000
   2.500   0.7249   0.02029   0.01092  -0.1021   0.0417   1.0000
   2.750   0.7453   0.02114   0.01159  -0.1013   0.0415   1.0000
   3.250   0.7900   0.02239   0.01257  -0.1003   0.0415   1.0000
   3.500   0.8127   0.02294   0.01302  -0.0998   0.0414   1.0000
   3.750   0.8357   0.02351   0.01349  -0.0995   0.0414   1.0000
   4.000   0.8588   0.02411   0.01399  -0.0991   0.0414   1.0000
   4.250   0.8821   0.02472   0.01452  -0.0988   0.0414   1.0000
   4.500   0.9057   0.02536   0.01507  -0.0986   0.0413   1.0000
   4.750   0.9297   0.02603   0.01564  -0.0985   0.0413   1.0000
   5.000   0.9539   0.02670   0.01623  -0.0984   0.0413   1.0000
   5.250   0.9781   0.02738   0.01685  -0.0983   0.0413   1.0000
   5.500   1.0024   0.02805   0.01746  -0.0982   0.0412   1.0000
   5.750   1.0270   0.02875   0.01809  -0.0982   0.0412   1.0000
   6.000   1.0519   0.02947   0.01876  -0.0983   0.0411   1.0000
   6.250   1.0773   0.03025   0.01949  -0.0985   0.0411   1.0000
   6.500   1.1031   0.03106   0.02024  -0.0987   0.0411   1.0000
   6.750   1.1291   0.03189   0.02101  -0.0990   0.0411   1.0000
   7.000   1.1551   0.03275   0.02182  -0.0994   0.0411   1.0000
   7.250   1.1810   0.03363   0.02269  -0.0997   0.0411   1.0000
   7.500   1.2068   0.03453   0.02356  -0.1000   0.0411   1.0000
   7.750   1.2325   0.03546   0.02447  -0.1003   0.0411   1.0000
   8.000   1.2578   0.03639   0.02540  -0.1006   0.0411   1.0000
   8.250   1.2810   0.03719   0.02626  -0.1005   0.0409   1.0000
   8.500   1.3052   0.03814   0.02725  -0.1006   0.0403   1.0000
   8.750   1.3372   0.04004   0.02906  -0.1021   0.0396   1.0000
   9.000   1.3613   0.04117   0.03025  -0.1022   0.0392   1.0000
   9.250   1.3782   0.04154   0.03082  -0.1011   0.0384   1.0000
   9.500   1.4126   0.04426   0.03345  -0.1031   0.0372   1.0000
   9.750   1.4264   0.04442   0.03387  -0.1014   0.0356   1.0000
  10.250   1.4559   0.04582   0.03559  -0.0989   0.0275   1.0000
  10.750   1.4830   0.04658   0.03670  -0.0958   0.0213   1.0000
  11.000   1.5008   0.04746   0.03769  -0.0949   0.0188   1.0000
  11.250   1.5179   0.04828   0.03858  -0.0941   0.0173   1.0000
  11.500   1.5338   0.04899   0.03935  -0.0932   0.0163   1.0000
  11.750   1.5481   0.04951   0.03992  -0.0922   0.0158   1.0000
  12.000   1.5642   0.05058   0.04110  -0.0913   0.0151   1.0000
  12.250   1.5793   0.05162   0.04223  -0.0904   0.0145   1.0000
  12.500   1.5924   0.05247   0.04315  -0.0892   0.0140   1.0000
  12.750   1.6035   0.05320   0.04394  -0.0878   0.0137   1.0000
  13.000   1.6125   0.05388   0.04468  -0.0861   0.0134   1.0000
  13.500   1.6378   0.05720   0.04828  -0.0839   0.0123   1.0000
  13.750   1.6469   0.05869   0.04993  -0.0824   0.0118   1.0000
  14.000   1.6514   0.05979   0.05113  -0.0802   0.0114   1.0000
  14.250   1.6531   0.06079   0.05222  -0.0777   0.0111   1.0000
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