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GOE 372 AIRFOIL (goe372-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 372 AIRFOIL (goe372-il)
Reynolds number: 100,000
Max Cl/Cd: 60.09 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe372-il-100000-n5.txt
Download as CSV file: xf-goe372-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 372 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3465   0.09017   0.08553  -0.0290   1.0000   0.0261
  -7.250  -0.3515   0.08774   0.08321  -0.0283   1.0000   0.0253
  -7.000  -0.3553   0.08497   0.08053  -0.0283   1.0000   0.0247
  -6.750  -0.3577   0.08207   0.07773  -0.0289   1.0000   0.0243
  -6.500  -0.3599   0.07905   0.07479  -0.0297   1.0000   0.0238
  -6.250  -0.3613   0.07599   0.07179  -0.0305   1.0000   0.0236
  -6.000  -0.3614   0.07277   0.06862  -0.0316   1.0000   0.0234
  -5.750  -0.3533   0.06997   0.06583  -0.0330   0.9988   0.0244
  -5.500  -0.3209   0.06517   0.06094  -0.0410   0.9924   0.0272
  -5.250  -0.2834   0.05863   0.05426  -0.0511   0.9858   0.0283
  -5.000  -0.2435   0.05149   0.04690  -0.0611   0.9788   0.0290
  -4.750  -0.1983   0.04208   0.03706  -0.0721   0.9716   0.0313
  -4.500  -0.1587   0.03794   0.03258  -0.0778   0.9662   0.0362
  -4.250  -0.1182   0.02889   0.02238  -0.0840   0.9585   0.0425
  -4.000  -0.0818   0.02832   0.02175  -0.0865   0.9523   0.0489
  -3.750  -0.0474   0.02483   0.01738  -0.0887   0.9445   0.0561
  -3.500  -0.0106   0.02302   0.01519  -0.0909   0.9401   0.0594
  -3.250   0.0201   0.02150   0.01323  -0.0917   0.9328   0.0634
  -3.000   0.0556   0.02003   0.01120  -0.0931   0.9280   0.0677
  -2.750   0.0864   0.01940   0.01046  -0.0939   0.9208   0.0737
  -2.500   0.1200   0.01858   0.00939  -0.0950   0.9148   0.0791
  -2.250   0.1516   0.01771   0.00821  -0.0956   0.9080   0.0830
  -2.000   0.1835   0.01697   0.00748  -0.0964   0.9012   0.0886
  -1.750   0.2146   0.01641   0.00677  -0.0969   0.8939   0.0972
  -1.500   0.2461   0.01593   0.00629  -0.0976   0.8868   0.1074
  -1.250   0.2759   0.01562   0.00597  -0.0979   0.8784   0.1213
  -1.000   0.3085   0.01534   0.00567  -0.0988   0.8715   0.1412
  -0.750   0.3369   0.01505   0.00540  -0.0988   0.8620   0.1567
  -0.500   0.3670   0.01475   0.00513  -0.0991   0.8538   0.1775
  -0.250   0.3978   0.01445   0.00489  -0.0995   0.8452   0.2059
   0.000   0.4265   0.01415   0.00476  -0.0996   0.8354   0.2585
   0.250   0.4554   0.01348   0.00469  -0.0999   0.8266   0.4539
   0.500   0.4983   0.01238   0.00451  -0.1026   0.8182   1.0000
   0.750   0.5257   0.01247   0.00449  -0.1023   0.8074   1.0000
   1.000   0.5534   0.01255   0.00447  -0.1020   0.7968   1.0000
   1.250   0.5816   0.01263   0.00446  -0.1018   0.7866   1.0000
   1.500   0.6081   0.01275   0.00453  -0.1014   0.7750   1.0000
   1.750   0.6344   0.01288   0.00466  -0.1009   0.7631   1.0000
   2.000   0.6608   0.01301   0.00478  -0.1004   0.7514   1.0000
   2.250   0.6872   0.01315   0.00492  -0.0999   0.7394   1.0000
   2.500   0.7132   0.01328   0.00509  -0.0993   0.7259   1.0000
   2.750   0.7388   0.01342   0.00525  -0.0986   0.7112   1.0000
   3.000   0.7642   0.01356   0.00543  -0.0978   0.6956   1.0000
   3.250   0.7893   0.01370   0.00564  -0.0970   0.6792   1.0000
   3.500   0.8104   0.01370   0.00555  -0.0948   0.6353   1.0000
   3.750   0.8323   0.01385   0.00560  -0.0931   0.5937   1.0000
   4.000   0.8501   0.01429   0.00559  -0.0905   0.5194   1.0000
   4.250   0.8684   0.01490   0.00592  -0.0884   0.4467   1.0000
   4.500   0.8762   0.01663   0.00653  -0.0850   0.2451   1.0000
   4.750   0.8801   0.01951   0.00802  -0.0819   0.0321   1.0000
   5.000   0.9003   0.02039   0.00899  -0.0804   0.0261   1.0000
   5.250   0.9207   0.02122   0.01001  -0.0789   0.0241   1.0000
   5.500   0.9394   0.02225   0.01123  -0.0773   0.0214   1.0000
   5.750   0.9545   0.02366   0.01286  -0.0752   0.0192   1.0000
   6.000   0.9702   0.02492   0.01429  -0.0731   0.0186   1.0000
   6.250   0.9853   0.02623   0.01581  -0.0710   0.0182   1.0000
   6.500   1.0002   0.02771   0.01739  -0.0689   0.0179   1.0000
   6.750   1.0173   0.02934   0.01908  -0.0671   0.0177   1.0000
   7.000   1.0380   0.03105   0.02087  -0.0657   0.0171   1.0000
   7.250   1.0606   0.03279   0.02275  -0.0646   0.0160   1.0000
   7.500   1.0843   0.03484   0.02497  -0.0637   0.0152   1.0000
   7.750   1.1087   0.03721   0.02757  -0.0628   0.0153   1.0000
   8.000   1.1312   0.03983   0.03048  -0.0617   0.0154   1.0000
   8.250   1.1505   0.04267   0.03366  -0.0602   0.0157   1.0000
   8.500   1.1660   0.04566   0.03712  -0.0584   0.0161   1.0000
   8.750   1.1775   0.04894   0.04079  -0.0562   0.0165   1.0000
   9.000   1.1855   0.05229   0.04451  -0.0539   0.0169   1.0000
   9.250   1.1894   0.05597   0.04854  -0.0515   0.0174   1.0000
   9.500   1.1898   0.05996   0.05284  -0.0491   0.0179   1.0000
   9.750   1.2018   0.06239   0.05557  -0.0469   0.0205   1.0000
  10.000   1.1873   0.06551   0.05925  -0.0425   0.0222   1.0000
  10.250   1.1716   0.06899   0.06303  -0.0391   0.0233   1.0000
  10.500   1.1559   0.07254   0.06682  -0.0367   0.0239   1.0000
  10.750   1.1387   0.07651   0.07101  -0.0354   0.0245   1.0000
  11.000   1.1213   0.08085   0.07553  -0.0352   0.0248   1.0000
  11.250   1.1026   0.08570   0.08056  -0.0361   0.0251   1.0000
  11.500   1.0831   0.09116   0.08619  -0.0381   0.0251   1.0000
  11.750   1.0629   0.09731   0.09249  -0.0414   0.0249   1.0000
  12.000   1.0422   0.10455   0.09986  -0.0460   0.0246   1.0000
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