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GOE 802 B AIRFOIL (goe802b-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 802 B AIRFOIL (goe802b-il)
Reynolds number: 100,000
Max Cl/Cd: 53.84 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe802b-il-100000.txt
Download as CSV file: xf-goe802b-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 802 B 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3081   0.09884   0.09433  -0.0255   1.0000   0.0602
  -7.500  -0.3230   0.09815   0.09374  -0.0239   1.0000   0.0604
  -7.250  -0.3347   0.09727   0.09293  -0.0237   1.0000   0.0606
  -6.750  -0.3438   0.09264   0.08842  -0.0211   1.0000   0.0611
  -6.500  -0.3464   0.09017   0.08600  -0.0193   1.0000   0.0616
  -6.250  -0.3484   0.08794   0.08380  -0.0184   1.0000   0.0623
  -6.000  -0.3487   0.08572   0.08162  -0.0182   1.0000   0.0632
  -5.750  -0.3469   0.08344   0.07935  -0.0187   1.0000   0.0642
  -5.500  -0.3022   0.07902   0.07478  -0.0306   0.9932   0.0666
  -5.250  -0.2694   0.07441   0.07010  -0.0370   0.9860   0.0675
  -5.000  -0.2338   0.07018   0.06580  -0.0431   0.9801   0.0699
  -4.750  -0.1854   0.06661   0.06195  -0.0532   0.9706   0.0725
  -4.500  -0.1516   0.06217   0.05749  -0.0577   0.9653   0.0740
  -4.250  -0.1161   0.05894   0.05410  -0.0627   0.9554   0.0763
  -4.000  -0.0620   0.05533   0.05018  -0.0711   0.9497   0.0777
  -3.750  -0.0346   0.05211   0.04690  -0.0735   0.9391   0.0789
  -3.500   0.0165   0.04905   0.04354  -0.0800   0.9335   0.0813
  -3.250   0.0529   0.04660   0.04083  -0.0832   0.9226   0.0823
  -3.000   0.0987   0.04320   0.03728  -0.0883   0.9169   0.0846
  -2.500   0.1869   0.03840   0.03191  -0.0958   0.9003   0.0875
  -2.250   0.2296   0.03619   0.02943  -0.0989   0.8927   0.0897
  -2.000   0.2700   0.03536   0.02812  -0.1005   0.8823   0.0912
  -1.750   0.3044   0.03263   0.02534  -0.1022   0.8732   0.0927
  -1.500   0.3409   0.03151   0.02387  -0.1031   0.8633   0.0955
  -1.250   0.3707   0.02975   0.02197  -0.1033   0.8516   0.0978
  -1.000   0.4076   0.02898   0.02079  -0.1038   0.8431   0.1007
  -0.750   0.4339   0.02735   0.01908  -0.1033   0.8294   0.1025
  -0.500   0.4642   0.02673   0.01815  -0.1028   0.8178   0.1055
  -0.250   0.4946   0.02518   0.01645  -0.1026   0.8072   0.1092
   0.000   0.5211   0.02433   0.01538  -0.1018   0.7929   0.1148
   0.250   0.5485   0.02269   0.01358  -0.1013   0.7805   0.1270
   0.500   0.5779   0.02129   0.01208  -0.1008   0.7700   0.1352
   0.750   0.6032   0.02025   0.01118  -0.1000   0.7552   0.1437
   1.000   0.6288   0.01949   0.01056  -0.0991   0.7410   0.1515
   1.250   0.6548   0.01896   0.01005  -0.0979   0.7276   0.1566
   1.500   0.6831   0.01847   0.00947  -0.0971   0.7158   0.1617
   1.750   0.7095   0.01833   0.00925  -0.0963   0.7004   0.1662
   2.000   0.7363   0.01825   0.00911  -0.0956   0.6856   0.1696
   2.250   0.7633   0.01787   0.00908  -0.0951   0.6714   0.3049
   2.500   0.7918   0.01659   0.00896  -0.0943   0.6582   1.0000
   2.750   0.8190   0.01677   0.00888  -0.0935   0.6453   1.0000
   3.000   0.8444   0.01709   0.00907  -0.0929   0.6308   1.0000
   3.250   0.8700   0.01741   0.00927  -0.0923   0.6171   1.0000
   3.500   0.8964   0.01772   0.00942  -0.0919   0.6045   1.0000
   3.750   0.9229   0.01804   0.00961  -0.0914   0.5924   1.0000
   4.000   0.9476   0.01845   0.00999  -0.0909   0.5787   1.0000
   4.250   0.9727   0.01879   0.01024  -0.0903   0.5651   1.0000
   4.500   0.9984   0.01907   0.01038  -0.0896   0.5516   1.0000
   4.750   1.0239   0.01936   0.01056  -0.0890   0.5382   1.0000
   5.000   1.0477   0.01978   0.01102  -0.0884   0.5252   1.0000
   5.250   1.0729   0.02020   0.01139  -0.0879   0.5141   1.0000
   5.500   1.0984   0.02058   0.01171  -0.0875   0.5030   1.0000
   5.750   1.1219   0.02106   0.01227  -0.0869   0.4914   1.0000
   6.000   1.1481   0.02146   0.01256  -0.0865   0.4815   1.0000
   6.250   1.1710   0.02191   0.01310  -0.0858   0.4697   1.0000
   6.500   1.1950   0.02237   0.01358  -0.0852   0.4587   1.0000
   6.750   1.2205   0.02271   0.01386  -0.0847   0.4479   1.0000
   7.000   1.2420   0.02318   0.01446  -0.0838   0.4352   1.0000
   7.250   1.2653   0.02363   0.01492  -0.0831   0.4236   1.0000
   7.500   1.2905   0.02397   0.01516  -0.0825   0.4118   1.0000
   7.750   1.3106   0.02437   0.01567  -0.0813   0.3970   1.0000
   8.000   1.3308   0.02473   0.01607  -0.0801   0.3813   1.0000
   8.250   1.3505   0.02511   0.01645  -0.0788   0.3650   1.0000
   8.500   1.3696   0.02556   0.01691  -0.0775   0.3486   1.0000
   8.750   1.3880   0.02609   0.01747  -0.0761   0.3323   1.0000
   9.000   1.4061   0.02672   0.01810  -0.0747   0.3167   1.0000
   9.250   1.4239   0.02742   0.01878  -0.0733   0.3017   1.0000
   9.500   1.4417   0.02814   0.01945  -0.0719   0.2875   1.0000
   9.750   1.4573   0.02890   0.02024  -0.0702   0.2737   1.0000
  10.000   1.4710   0.02975   0.02122  -0.0683   0.2602   1.0000
  10.250   1.4842   0.03059   0.02211  -0.0664   0.2477   1.0000
  10.500   1.4970   0.03140   0.02287  -0.0645   0.2360   1.0000
  10.750   1.5068   0.03225   0.02376  -0.0623   0.2245   1.0000
  11.000   1.5145   0.03330   0.02490  -0.0598   0.2136   1.0000
  11.250   1.5229   0.03433   0.02589  -0.0575   0.2041   1.0000
  11.500   1.5268   0.03547   0.02714  -0.0546   0.1951   1.0000
  11.750   1.5342   0.03678   0.02845  -0.0525   0.1869   1.0000
  12.000   1.5393   0.03812   0.02989  -0.0502   0.1791   1.0000
  12.250   1.5490   0.03957   0.03132  -0.0486   0.1722   1.0000
  12.500   1.5523   0.04119   0.03314  -0.0464   0.1660   1.0000
  12.750   1.5634   0.04257   0.03450  -0.0451   0.1601   1.0000
  13.000   1.5662   0.04442   0.03653  -0.0432   0.1548   1.0000
  13.250   1.5654   0.04629   0.03858  -0.0413   0.1494   1.0000
  13.500   1.5722   0.04779   0.04004  -0.0400   0.1439   1.0000
  13.750   1.5698   0.05007   0.04255  -0.0384   0.1395   1.0000
  14.000   1.5649   0.05250   0.04521  -0.0370   0.1349   1.0000
  14.250   1.5649   0.05457   0.04736  -0.0360   0.1302   1.0000
  14.500   1.5632   0.05700   0.04988  -0.0351   0.1257   1.0000
  14.750   1.5518   0.06045   0.05363  -0.0345   0.1215   1.0000
  15.000   1.5450   0.06355   0.05688  -0.0343   0.1170   1.0000
  15.250   1.5415   0.06632   0.05963  -0.0341   0.1120   1.0000
  15.500   1.5248   0.07110   0.06476  -0.0348   0.1081   1.0000
  15.750   1.5120   0.07557   0.06941  -0.0357   0.1032   1.0000
  16.000   1.5026   0.07965   0.07346  -0.0367   0.0978   1.0000
  16.250   1.4832   0.08585   0.07999  -0.0388   0.0933   1.0000
  16.500   1.4683   0.09141   0.08564  -0.0410   0.0880   1.0000
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