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GOE 381 AIRFOIL (goe381-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 381 AIRFOIL (goe381-il)
Reynolds number: 500,000
Max Cl/Cd: 100.71 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe381-il-500000.txt
Download as CSV file: xf-goe381-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 381 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.2894   0.09915   0.09714  -0.0233   1.0000   0.0122
  -7.750  -0.2925   0.09756   0.09559  -0.0235   1.0000   0.0122
  -7.500  -0.2899   0.09297   0.09104  -0.0211   0.9999   0.0125
  -7.250  -0.2710   0.08892   0.08698  -0.0248   0.9955   0.0127
  -7.000  -0.2485   0.08500   0.08306  -0.0303   0.9904   0.0131
  -6.750  -0.2239   0.08106   0.07911  -0.0365   0.9847   0.0135
  -6.500  -0.1993   0.07722   0.07525  -0.0424   0.9771   0.0139
  -6.250  -0.1732   0.07332   0.07133  -0.0485   0.9698   0.0146
  -6.000  -0.1507   0.06980   0.06778  -0.0533   0.9592   0.0153
  -5.750  -0.1201   0.06645   0.06437  -0.0602   0.9486   0.0163
  -5.500  -0.0875   0.06311   0.06093  -0.0675   0.9389   0.0165
  -5.250  -0.0606   0.05965   0.05738  -0.0717   0.9292   0.0166
  -5.000  -0.0342   0.05608   0.05372  -0.0751   0.9199   0.0166
  -4.750  -0.0230   0.05125   0.04886  -0.0757   0.9113   0.0171
  -4.500  -0.0039   0.04866   0.04623  -0.0766   0.9013   0.0177
  -4.250   0.0207   0.04613   0.04362  -0.0786   0.8915   0.0188
  -4.000   0.0505   0.04351   0.04087  -0.0811   0.8819   0.0210
  -3.750   0.0929   0.04128   0.03840  -0.0848   0.8716   0.0223
  -3.500   0.1237   0.03846   0.03542  -0.0866   0.8610   0.0225
  -3.250   0.1539   0.03545   0.03222  -0.0881   0.8505   0.0226
  -3.000   0.1798   0.03021   0.02676  -0.0903   0.8402   0.0235
  -2.750   0.2032   0.02858   0.02505  -0.0907   0.8270   0.0246
  -2.500   0.2301   0.02711   0.02344  -0.0912   0.8118   0.0275
  -2.250   0.2653   0.02637   0.02241  -0.0909   0.7941   0.0310
  -2.000   0.2951   0.02435   0.02008  -0.0910   0.7744   0.0312
  -1.750   0.3209   0.02044   0.01588  -0.0922   0.7519   0.0336
  -1.500   0.3465   0.01963   0.01487  -0.0922   0.7216   0.0367
  -1.250   0.3773   0.01978   0.01464  -0.0912   0.6905   0.0425
  -1.000   0.4033   0.01704   0.01161  -0.0919   0.6639   0.0458
  -0.750   0.4300   0.01650   0.01086  -0.0918   0.6390   0.0503
  -0.500   0.4580   0.01566   0.00973  -0.0917   0.6175   0.0581
  -0.250   0.4850   0.01526   0.00916  -0.0916   0.5987   0.0636
   0.000   0.5132   0.01448   0.00812  -0.0915   0.5829   0.0706
   0.250   0.5406   0.01394   0.00746  -0.0914   0.5696   0.0742
   0.500   0.5693   0.01474   0.00803  -0.0908   0.5575   0.0809
   0.750   0.5990   0.01076   0.00361  -0.0903   0.5488   0.0425
   1.000   0.6262   0.01029   0.00304  -0.0901   0.5385   0.0427
   1.250   0.6534   0.00988   0.00255  -0.0900   0.5283   0.0438
   1.500   0.6809   0.00970   0.00232  -0.0899   0.5180   0.0450
   1.750   0.7084   0.00964   0.00222  -0.0898   0.5078   0.0466
   2.000   0.7357   0.00964   0.00219  -0.0897   0.4971   0.0495
   2.250   0.7631   0.00965   0.00216  -0.0897   0.4855   0.0518
   2.500   0.7906   0.00968   0.00217  -0.0896   0.4724   0.0574
   2.750   0.8176   0.00976   0.00227  -0.0895   0.4558   0.0937
   3.000   0.8447   0.00986   0.00236  -0.0894   0.4358   0.1146
   3.250   0.8712   0.01002   0.00245  -0.0892   0.4122   0.1280
   3.500   0.8973   0.01023   0.00258  -0.0890   0.3818   0.1408
   3.750   0.9227   0.00998   0.00284  -0.0892   0.3488   0.5292
   4.000   0.9447   0.00938   0.00303  -0.0881   0.3220   1.0000
   4.250   0.9700   0.00977   0.00325  -0.0878   0.2979   1.0000
   4.500   0.9950   0.01018   0.00351  -0.0875   0.2737   1.0000
   4.750   1.0206   0.01051   0.00375  -0.0873   0.2590   1.0000
   5.250   1.0716   0.01114   0.00422  -0.0868   0.2312   1.0000
   5.500   1.0971   0.01145   0.00449  -0.0866   0.2178   1.0000
   5.750   1.1221   0.01181   0.00475  -0.0863   0.1970   1.0000
   6.000   1.1434   0.01266   0.00518  -0.0857   0.1342   1.0000
   6.250   1.1651   0.01345   0.00576  -0.0850   0.1050   1.0000
   6.750   1.2049   0.01551   0.00744  -0.0829   0.0183   1.0000
   7.000   1.2284   0.01603   0.00810  -0.0823   0.0160   1.0000
   7.250   1.2513   0.01661   0.00880  -0.0815   0.0153   1.0000
   7.500   1.2732   0.01730   0.00962  -0.0807   0.0146   1.0000
   7.750   1.2936   0.01814   0.01058  -0.0796   0.0140   1.0000
   8.000   1.3128   0.01906   0.01164  -0.0784   0.0131   1.0000
   8.250   1.3301   0.02012   0.01280  -0.0771   0.0122   1.0000
   8.500   1.3452   0.02133   0.01411  -0.0754   0.0117   1.0000
   8.750   1.3573   0.02271   0.01561  -0.0733   0.0114   1.0000
   9.000   1.3657   0.02429   0.01730  -0.0708   0.0111   1.0000
   9.250   1.3701   0.02598   0.01909  -0.0678   0.0109   1.0000
   9.500   1.3724   0.02768   0.02087  -0.0644   0.0108   1.0000
   9.750   1.3769   0.02933   0.02263  -0.0616   0.0109   1.0000
  10.000   1.3847   0.03083   0.02424  -0.0593   0.0112   1.0000
  10.250   1.3952   0.03290   0.02650  -0.0565   0.0137   1.0000
  10.500   1.4329   0.03477   0.02846  -0.0557   0.0204   1.0000
  10.750   1.4453   0.03661   0.03038  -0.0541   0.0191   1.0000
  11.000   1.4605   0.03886   0.03265  -0.0530   0.0178   1.0000
  14.250   1.2211   0.08019   0.07641  -0.0256   0.0126   1.0000
  14.500   1.2008   0.08535   0.08173  -0.0266   0.0126   1.0000
  14.750   1.1785   0.09053   0.08706  -0.0278   0.0126   1.0000
  15.000   1.1502   0.09522   0.09191  -0.0289   0.0127   1.0000
  15.250   1.1247   0.10011   0.09695  -0.0307   0.0128   1.0000
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