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GOE 488 AIRFOIL (goe488-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 488 AIRFOIL (goe488-il)
Reynolds number: 100,000
Max Cl/Cd: 51.26 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe488-il-100000-n5.txt
Download as CSV file: xf-goe488-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 488 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4208   0.10146   0.09643  -0.0287   1.0000   0.0562
  -8.500  -0.4274   0.09898   0.09404  -0.0301   1.0000   0.0564
  -8.250  -0.4348   0.09644   0.09159  -0.0312   1.0000   0.0566
  -8.000  -0.4372   0.09328   0.08847  -0.0335   1.0000   0.0567
  -7.750  -0.4385   0.08992   0.08513  -0.0355   1.0000   0.0568
  -7.500  -0.4254   0.08550   0.08074  -0.0269   1.0000   0.0600
  -7.250  -0.4258   0.08270   0.07798  -0.0268   1.0000   0.0609
  -7.000  -0.4267   0.07987   0.07519  -0.0269   1.0000   0.0618
  -6.750  -0.4277   0.07691   0.07226  -0.0271   1.0000   0.0626
  -6.500  -0.4293   0.07221   0.06751  -0.0294   1.0000   0.0536
  -6.250  -0.4271   0.06866   0.06391  -0.0305   1.0000   0.0542
  -6.000  -0.4225   0.06495   0.06014  -0.0314   1.0000   0.0546
  -5.750  -0.4168   0.06143   0.05655  -0.0314   1.0000   0.0539
  -5.500  -0.4092   0.05778   0.05281  -0.0314   1.0000   0.0525
  -5.250  -0.3988   0.05390   0.04877  -0.0319   1.0000   0.0513
  -5.000  -0.3858   0.05003   0.04471  -0.0325   1.0000   0.0511
  -4.750  -0.3669   0.04611   0.04051  -0.0338   0.9993   0.0532
  -4.500  -0.3349   0.04138   0.03538  -0.0373   0.9953   0.0532
  -4.250  -0.3035   0.03705   0.03059  -0.0400   0.9911   0.0526
  -4.000  -0.2713   0.03329   0.02634  -0.0423   0.9872   0.0525
  -3.750  -0.2405   0.03033   0.02288  -0.0438   0.9832   0.0531
  -3.500  -0.2088   0.02819   0.02017  -0.0449   0.9793   0.0554
  -3.250  -0.1770   0.02630   0.01784  -0.0461   0.9761   0.0557
  -3.000  -0.1478   0.02471   0.01588  -0.0466   0.9719   0.0556
  -2.750  -0.1155   0.02333   0.01417  -0.0476   0.9686   0.0556
  -2.500  -0.0843   0.02220   0.01276  -0.0483   0.9644   0.0559
  -2.250  -0.0508   0.02122   0.01155  -0.0494   0.9594   0.0563
  -2.000  -0.0162   0.02031   0.01048  -0.0506   0.9541   0.0570
  -1.750   0.0188   0.01930   0.00943  -0.0520   0.9478   0.0587
  -1.500   0.0524   0.01860   0.00872  -0.0531   0.9407   0.0607
  -1.250   0.0891   0.01800   0.00811  -0.0548   0.9348   0.0637
  -1.000   0.1204   0.01756   0.00765  -0.0553   0.9270   0.0681
  -0.750   0.1590   0.01702   0.00715  -0.0573   0.9212   0.0763
  -0.500   0.1889   0.01664   0.00676  -0.0575   0.9124   0.0834
  -0.250   0.2296   0.01605   0.00628  -0.0597   0.9067   0.1023
   0.000   0.2602   0.01547   0.00607  -0.0600   0.8959   0.1898
   0.250   0.2927   0.01495   0.00584  -0.0607   0.8856   0.2963
   0.750   0.3952   0.01301   0.00554  -0.0694   0.8717   1.0000
   1.000   0.4266   0.01292   0.00537  -0.0696   0.8606   1.0000
   1.250   0.4568   0.01285   0.00523  -0.0697   0.8481   1.0000
   1.500   0.4845   0.01280   0.00513  -0.0692   0.8333   1.0000
   1.750   0.5108   0.01277   0.00508  -0.0684   0.8163   1.0000
   2.000   0.5370   0.01275   0.00504  -0.0676   0.7965   1.0000
   2.250   0.5640   0.01270   0.00496  -0.0669   0.7737   1.0000
   2.500   0.5893   0.01270   0.00492  -0.0659   0.7444   1.0000
   2.750   0.6157   0.01269   0.00485  -0.0649   0.7049   1.0000
   3.000   0.6443   0.01273   0.00467  -0.0643   0.6499   1.0000
   3.250   0.6690   0.01305   0.00460  -0.0630   0.5835   1.0000
   3.500   0.6897   0.01352   0.00476  -0.0612   0.5162   1.0000
   3.750   0.7099   0.01405   0.00498  -0.0596   0.4650   1.0000
   4.000   0.7312   0.01453   0.00527  -0.0582   0.4323   1.0000
   4.250   0.7531   0.01500   0.00560  -0.0570   0.4076   1.0000
   4.500   0.7754   0.01545   0.00598  -0.0559   0.3864   1.0000
   4.750   0.7978   0.01590   0.00637  -0.0549   0.3670   1.0000
   5.000   0.8202   0.01635   0.00679  -0.0539   0.3497   1.0000
   5.250   0.8428   0.01678   0.00722  -0.0529   0.3337   1.0000
   5.500   0.8660   0.01719   0.00771  -0.0520   0.3206   1.0000
   5.750   0.8891   0.01761   0.00821  -0.0511   0.3076   1.0000
   6.000   0.9101   0.01803   0.00862  -0.0499   0.2838   1.0000
   6.250   0.9303   0.01841   0.00896  -0.0486   0.2464   1.0000
   6.500   0.9516   0.01884   0.00943  -0.0475   0.2169   1.0000
   6.750   0.9716   0.01943   0.00990  -0.0463   0.1825   1.0000
   7.000   0.9905   0.02024   0.01054  -0.0450   0.1458   1.0000
   7.250   1.0087   0.02125   0.01138  -0.0436   0.1028   1.0000
   7.500   1.0231   0.02281   0.01255  -0.0419   0.0541   1.0000
   7.750   1.0392   0.02414   0.01389  -0.0401   0.0363   1.0000
   8.250   1.0717   0.02647   0.01646  -0.0365   0.0270   1.0000
   8.500   1.0862   0.02769   0.01785  -0.0346   0.0249   1.0000
   8.750   1.0981   0.02909   0.01935  -0.0325   0.0231   1.0000
   9.000   1.1085   0.03055   0.02097  -0.0301   0.0216   1.0000
   9.250   1.1188   0.03196   0.02258  -0.0277   0.0207   1.0000
   9.500   1.1272   0.03354   0.02435  -0.0252   0.0200   1.0000
   9.750   1.1342   0.03521   0.02618  -0.0225   0.0194   1.0000
  10.000   1.1413   0.03696   0.02816  -0.0199   0.0190   1.0000
  10.250   1.1484   0.03891   0.03029  -0.0174   0.0186   1.0000
  10.500   1.1555   0.04104   0.03261  -0.0152   0.0183   1.0000
  10.750   1.1614   0.04328   0.03507  -0.0131   0.0179   1.0000
  11.000   1.1649   0.04567   0.03768  -0.0109   0.0174   1.0000
  11.250   1.1656   0.04811   0.04033  -0.0089   0.0169   1.0000
  11.500   1.1633   0.05083   0.04326  -0.0071   0.0164   1.0000
  11.750   1.1587   0.05386   0.04649  -0.0056   0.0160   1.0000
  12.000   1.1515   0.05723   0.05009  -0.0044   0.0157   1.0000
  12.250   1.1404   0.06122   0.05431  -0.0039   0.0154   1.0000
  12.500   1.1295   0.06534   0.05866  -0.0040   0.0154   1.0000
  12.750   1.1179   0.06975   0.06332  -0.0048   0.0154   1.0000
  13.000   1.1032   0.07498   0.06878  -0.0067   0.0154   1.0000
  13.250   1.0869   0.08099   0.07501  -0.0097   0.0154   1.0000
  13.500   1.0696   0.08780   0.08203  -0.0137   0.0155   1.0000
  13.750   1.0521   0.09539   0.08985  -0.0187   0.0157   1.0000
  14.000   1.0301   0.10485   0.09953  -0.0251   0.0160   1.0000
  14.250   0.9980   0.11803   0.11294  -0.0338   0.0168   1.0000
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