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GOE 57 AIRFOIL (goe57-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 57 AIRFOIL (goe57-il)
Reynolds number: 100,000
Max Cl/Cd: 59.23 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe57-il-100000-n5.txt
Download as CSV file: xf-goe57-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 57 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  -0.3050   0.09734   0.09270  -0.0244   1.0000   0.0436
  -7.250  -0.3115   0.09645   0.09193  -0.0244   1.0000   0.0448
  -7.000  -0.3161   0.09578   0.09136  -0.0261   1.0000   0.0455
  -6.750  -0.3180   0.09476   0.09041  -0.0283   1.0000   0.0458
  -6.500  -0.3156   0.09314   0.08881  -0.0307   1.0000   0.0461
  -6.250  -0.2946   0.08964   0.08526  -0.0371   0.9970   0.0462
  -6.000  -0.2854   0.08309   0.07876  -0.0359   0.9939   0.0471
  -5.750  -0.2709   0.07870   0.07438  -0.0353   0.9898   0.0484
  -5.500  -0.2468   0.07488   0.07053  -0.0387   0.9853   0.0509
  -5.250  -0.1943   0.07159   0.06701  -0.0538   0.9775   0.0592
  -5.000  -0.1444   0.06771   0.06283  -0.0659   0.9705   0.0599
  -4.750  -0.1246   0.06199   0.05716  -0.0679   0.9661   0.0608
  -4.500  -0.1100   0.05854   0.05377  -0.0670   0.9609   0.0631
  -4.250  -0.0796   0.05555   0.05070  -0.0707   0.9552   0.0689
  -4.000  -0.0084   0.05249   0.04701  -0.0852   0.9506   0.0745
  -3.750   0.0085   0.04808   0.04271  -0.0857   0.9439   0.0759
  -3.500   0.0392   0.04500   0.03959  -0.0884   0.9396   0.0782
  -3.250   0.0905   0.04291   0.03702  -0.0954   0.9348   0.0892
  -3.000   0.1141   0.03976   0.03395  -0.0965   0.9285   0.0918
  -2.750   0.1524   0.03722   0.03125  -0.1001   0.9243   0.0945
  -2.500   0.2061   0.03234   0.02556  -0.1050   0.9192   0.0589
  -2.250   0.2415   0.02993   0.02296  -0.1074   0.9120   0.0576
  -2.000   0.2807   0.02762   0.02034  -0.1099   0.9037   0.0568
  -1.750   0.3210   0.02546   0.01782  -0.1122   0.8940   0.0566
  -1.500   0.3568   0.02412   0.01601  -0.1130   0.8812   0.0596
  -1.250   0.3897   0.02258   0.01416  -0.1138   0.8683   0.0606
  -0.750   0.4520   0.02040   0.01145  -0.1142   0.8425   0.0599
  -0.500   0.4819   0.01945   0.01028  -0.1141   0.8295   0.0600
  -0.250   0.5109   0.01853   0.00921  -0.1140   0.8162   0.0604
   0.000   0.5391   0.01772   0.00830  -0.1137   0.8020   0.0613
   0.250   0.5664   0.01711   0.00763  -0.1132   0.7865   0.0627
   0.500   0.5934   0.01662   0.00712  -0.1127   0.7705   0.0648
   0.750   0.6199   0.01620   0.00665  -0.1120   0.7521   0.0678
   1.000   0.6463   0.01586   0.00622  -0.1112   0.7318   0.0725
   1.250   0.6719   0.01561   0.00596  -0.1104   0.7080   0.0810
   1.500   0.6987   0.01541   0.00560  -0.1097   0.6824   0.0891
   1.750   0.7251   0.01524   0.00528  -0.1089   0.6530   0.0994
   2.000   0.7513   0.01515   0.00509  -0.1082   0.6237   0.1217
   2.250   0.7746   0.01352   0.00508  -0.1072   0.5986   1.0000
   2.500   0.8000   0.01377   0.00505  -0.1064   0.5720   1.0000
   2.750   0.8249   0.01405   0.00513  -0.1056   0.5435   1.0000
   3.000   0.8493   0.01436   0.00524  -0.1047   0.5125   1.0000
   3.500   0.8968   0.01514   0.00561  -0.1029   0.4480   1.0000
   3.750   0.9201   0.01559   0.00586  -0.1020   0.4178   1.0000
   4.000   0.9432   0.01607   0.00617  -0.1011   0.3897   1.0000
   4.250   0.9664   0.01656   0.00652  -0.1003   0.3630   1.0000
   4.500   0.9895   0.01706   0.00693  -0.0995   0.3383   1.0000
   4.750   1.0123   0.01759   0.00736  -0.0986   0.3164   1.0000
   5.000   1.0354   0.01811   0.00781  -0.0979   0.2976   1.0000
   5.250   1.0584   0.01863   0.00830  -0.0971   0.2825   1.0000
   5.500   1.0813   0.01917   0.00883  -0.0962   0.2705   1.0000
   5.750   1.1036   0.01972   0.00933  -0.0954   0.2541   1.0000
   6.000   1.1256   0.02028   0.00982  -0.0946   0.2368   1.0000
   6.250   1.1467   0.02090   0.01033  -0.0937   0.2183   1.0000
   6.500   1.1677   0.02154   0.01092  -0.0927   0.2017   1.0000
   6.750   1.1892   0.02214   0.01153  -0.0918   0.1900   1.0000
   7.000   1.2103   0.02277   0.01218  -0.0909   0.1771   1.0000
   7.250   1.2311   0.02343   0.01288  -0.0899   0.1633   1.0000
   7.500   1.2519   0.02409   0.01358  -0.0889   0.1452   1.0000
   7.750   1.2705   0.02502   0.01430  -0.0877   0.0770   1.0000
   8.000   1.2771   0.02750   0.01630  -0.0850   0.0268   1.0000
   8.250   1.2928   0.02882   0.01769  -0.0833   0.0235   1.0000
   8.500   1.3090   0.02998   0.01907  -0.0817   0.0223   1.0000
   8.750   1.3236   0.03126   0.02057  -0.0798   0.0214   1.0000
   9.000   1.3359   0.03265   0.02220  -0.0778   0.0206   1.0000
   9.250   1.3450   0.03421   0.02399  -0.0755   0.0196   1.0000
   9.750   1.3486   0.03784   0.02811  -0.0694   0.0179   1.0000
  10.000   1.3456   0.04003   0.03049  -0.0664   0.0173   1.0000
  10.250   1.3412   0.04242   0.03309  -0.0637   0.0170   1.0000
  10.500   1.3357   0.04509   0.03594  -0.0614   0.0168   1.0000
  10.750   1.3298   0.04799   0.03901  -0.0596   0.0166   1.0000
  11.000   1.3239   0.05109   0.04225  -0.0581   0.0165   1.0000
  11.250   1.3193   0.05424   0.04553  -0.0568   0.0163   1.0000
  11.500   1.3179   0.05720   0.04856  -0.0556   0.0162   1.0000
  11.750   1.3194   0.05995   0.05143  -0.0546   0.0161   1.0000
  12.000   1.3225   0.06261   0.05420  -0.0535   0.0160   1.0000
  12.250   1.3269   0.06525   0.05697  -0.0524   0.0159   1.0000
  12.500   1.3303   0.06807   0.05994  -0.0516   0.0157   1.0000
  12.750   1.3318   0.07116   0.06321  -0.0510   0.0154   1.0000
  13.000   1.3310   0.07459   0.06685  -0.0509   0.0151   1.0000
  13.250   1.3288   0.07830   0.07082  -0.0510   0.0148   1.0000
  13.500   1.3247   0.08234   0.07507  -0.0514   0.0146   1.0000
  13.750   1.3193   0.08666   0.07960  -0.0522   0.0144   1.0000
  14.000   1.3126   0.09129   0.08444  -0.0533   0.0142   1.0000
  14.250   1.3049   0.09624   0.08962  -0.0548   0.0141   1.0000
  14.500   1.2961   0.10155   0.09514  -0.0568   0.0141   1.0000
  14.750   1.2864   0.10727   0.10107  -0.0592   0.0141   1.0000
  15.000   1.2757   0.11342   0.10743  -0.0623   0.0141   1.0000
  15.250   1.2641   0.11999   0.11420  -0.0658   0.0142   1.0000
  15.500   1.2519   0.12702   0.12143  -0.0700   0.0142   1.0000
  15.750   1.2395   0.13442   0.12902  -0.0745   0.0143   1.0000
  16.000   1.2269   0.14230   0.13707  -0.0796   0.0144   1.0000
  16.250   1.2144   0.15057   0.14551  -0.0851   0.0145   1.0000
  16.500   1.2015   0.15938   0.15447  -0.0910   0.0146   1.0000
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