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GOE 562 AIRFOIL (goe562-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 562 AIRFOIL (goe562-il)
Reynolds number: 200,000
Max Cl/Cd: 70.43 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe562-il-200000.txt
Download as CSV file: xf-goe562-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 562 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.2218   0.12366   0.12048  -0.0371   1.0000   0.0347
 -10.500  -0.2207   0.12116   0.11804  -0.0371   1.0000   0.0352
 -10.250  -0.2219   0.11872   0.11567  -0.0370   1.0000   0.0364
 -10.000  -0.2176   0.11567   0.11267  -0.0427   0.9975   0.0379
  -9.750  -0.2045   0.11124   0.10825  -0.0537   0.9907   0.0383
  -9.500  -0.1803   0.10483   0.10183  -0.0564   0.9863   0.0390
  -9.250  -0.1538   0.10029   0.09727  -0.0589   0.9771   0.0399
  -9.000  -0.1442   0.09686   0.09388  -0.0599   0.9389   0.0407
  -8.750  -0.1213   0.09231   0.08929  -0.0654   0.9189   0.0424
  -8.500  -0.0913   0.08692   0.08382  -0.0750   0.9037   0.0447
  -8.250  -0.0616   0.07939   0.07612  -0.1009   0.8817   0.0468
  -8.000  -0.0046   0.07258   0.06919  -0.1059   0.8670   0.0489
  -7.750   0.0550   0.06680   0.06315  -0.1206   0.8392   0.0521
  -7.500   0.0739   0.06245   0.05854  -0.1294   0.8064   0.0550
  -7.250   0.0634   0.05945   0.05512  -0.1348   0.7809   0.0572
  -7.000   0.0607   0.05540   0.05085  -0.1343   0.7637   0.0579
  -6.750   0.0753   0.05234   0.04779  -0.1335   0.7481   0.0588
  -6.500   0.0883   0.05061   0.04599  -0.1322   0.7346   0.0604
  -6.250   0.0976   0.04886   0.04412  -0.1309   0.7222   0.0628
  -6.000   0.1043   0.04673   0.04183  -0.1298   0.7113   0.0661
  -5.750   0.0995   0.04398   0.03849  -0.1271   0.7035   0.0709
  -5.500   0.1129   0.04140   0.03597  -0.1261   0.6938   0.0722
  -5.250   0.1276   0.03975   0.03424  -0.1248   0.6855   0.0743
  -5.000   0.1401   0.03821   0.03257  -0.1230   0.6770   0.0782
  -4.750   0.1462   0.03626   0.03013  -0.1199   0.6704   0.0859
  -4.500   0.1623   0.03459   0.02852  -0.1187   0.6622   0.0891
  -4.250   0.1743   0.03372   0.02716  -0.1160   0.6562   0.1006
  -4.000   0.1904   0.03180   0.02536  -0.1147   0.6488   0.1038
  -3.750   0.2043   0.03104   0.02422  -0.1122   0.6429   0.1164
  -3.500   0.2228   0.02942   0.02267  -0.1111   0.6365   0.1211
  -3.250   0.2376   0.02836   0.02143  -0.1089   0.6301   0.1348
  -3.000   0.2565   0.02740   0.02029  -0.1076   0.6248   0.1507
  -2.750   0.2712   0.02648   0.01937  -0.1054   0.6183   0.1678
  -2.500   0.2892   0.02561   0.01845  -0.1038   0.6127   0.1873
  -2.250   0.3287   0.02182   0.01317  -0.1009   0.6090   0.0809
  -2.000   0.3516   0.02055   0.01169  -0.0995   0.6034   0.0758
  -1.750   0.3770   0.01977   0.01070  -0.0986   0.5979   0.0749
  -1.500   0.4068   0.01913   0.00977  -0.0986   0.5932   0.0726
  -1.250   0.4312   0.01862   0.00919  -0.0976   0.5876   0.0721
  -1.000   0.4573   0.01815   0.00866  -0.0971   0.5823   0.0720
  -0.750   0.4859   0.01766   0.00811  -0.0972   0.5778   0.0733
  -0.500   0.5090   0.01736   0.00785  -0.0962   0.5727   0.0756
  -0.250   0.5310   0.01709   0.00759  -0.0949   0.5669   0.0786
   0.000   0.5563   0.01684   0.00724  -0.0943   0.5619   0.0812
   0.250   0.5771   0.01670   0.00710  -0.0927   0.5567   0.0835
   0.500   0.5970   0.01646   0.00688  -0.0910   0.5512   0.0883
   0.750   0.6218   0.01636   0.00669  -0.0903   0.5466   0.0981
   1.000   0.6424   0.01613   0.00665  -0.0888   0.5416   0.1439
   1.250   0.8691   0.01473   0.00687  -0.1326   0.5277   1.0000
   1.500   0.8884   0.01487   0.00701  -0.1310   0.5226   1.0000
   1.750   0.9105   0.01500   0.00707  -0.1299   0.5180   1.0000
   2.000   0.9349   0.01515   0.00710  -0.1292   0.5142   1.0000
   2.250   0.9556   0.01533   0.00727  -0.1279   0.5097   1.0000
   2.500   0.9760   0.01549   0.00742  -0.1265   0.5049   1.0000
   2.750   0.9990   0.01563   0.00749  -0.1256   0.5007   1.0000
   3.000   1.0235   0.01582   0.00759  -0.1250   0.4968   1.0000
   3.250   1.0414   0.01601   0.00784  -0.1231   0.4918   1.0000
   3.500   1.0627   0.01616   0.00797  -0.1219   0.4872   1.0000
   3.750   1.0867   0.01632   0.00806  -0.1212   0.4831   1.0000
   4.000   1.1060   0.01654   0.00831  -0.1196   0.4784   1.0000
   4.250   1.1252   0.01672   0.00851  -0.1180   0.4732   1.0000
   4.500   1.1478   0.01686   0.00860  -0.1170   0.4686   1.0000
   4.750   1.1680   0.01708   0.00882  -0.1157   0.4638   1.0000
   5.000   1.1855   0.01727   0.00907  -0.1137   0.4582   1.0000
   5.250   1.2070   0.01741   0.00916  -0.1126   0.4532   1.0000
   5.500   1.2259   0.01764   0.00942  -0.1109   0.4479   1.0000
   5.750   1.2426   0.01783   0.00967  -0.1089   0.4420   1.0000
   6.000   1.2641   0.01800   0.00979  -0.1077   0.4369   1.0000
   6.250   1.2795   0.01826   0.01012  -0.1054   0.4308   1.0000
   6.500   1.2962   0.01845   0.01035  -0.1034   0.4246   1.0000
   6.750   1.3164   0.01869   0.01055  -0.1021   0.4191   1.0000
   7.000   1.3281   0.01895   0.01092  -0.0990   0.4120   1.0000
   7.250   1.3471   0.01917   0.01108  -0.0975   0.4059   1.0000
   7.500   1.3579   0.01949   0.01152  -0.0944   0.3987   1.0000
   7.750   1.3730   0.01975   0.01177  -0.0921   0.3920   1.0000
   8.000   1.3839   0.02009   0.01217  -0.0890   0.3846   1.0000
   8.250   1.3935   0.02033   0.01241  -0.0857   0.3773   1.0000
   8.500   1.3981   0.02061   0.01274  -0.0814   0.3693   1.0000
   8.750   1.4036   0.02084   0.01294  -0.0773   0.3613   1.0000
   9.000   1.4083   0.02121   0.01340  -0.0733   0.3532   1.0000
   9.250   1.4157   0.02156   0.01369  -0.0698   0.3456   1.0000
   9.500   1.4228   0.02206   0.01431  -0.0665   0.3385   1.0000
   9.750   1.4316   0.02254   0.01478  -0.0636   0.3322   1.0000
  10.000   1.4383   0.02312   0.01544  -0.0605   0.3252   1.0000
  10.250   1.4444   0.02372   0.01606  -0.0574   0.3182   1.0000
  10.500   1.4508   0.02441   0.01682  -0.0545   0.3117   1.0000
  10.750   1.4555   0.02519   0.01764  -0.0516   0.3046   1.0000
  11.000   1.4617   0.02603   0.01852  -0.0490   0.2989   1.0000
  11.250   1.4650   0.02703   0.01962  -0.0463   0.2916   1.0000
  11.500   1.4662   0.02821   0.02083  -0.0436   0.2841   1.0000
  11.750   1.4674   0.02953   0.02224  -0.0412   0.2764   1.0000
  12.000   1.4670   0.03107   0.02383  -0.0388   0.2686   1.0000
  12.250   1.4644   0.03287   0.02566  -0.0366   0.2601   1.0000
  12.500   1.4605   0.03495   0.02783  -0.0347   0.2504   1.0000
  12.750   1.4531   0.03745   0.03036  -0.0328   0.2403   1.0000
  13.000   1.4428   0.04040   0.03332  -0.0311   0.2292   1.0000
  13.250   1.4286   0.04396   0.03692  -0.0298   0.2149   1.0000
  13.500   1.4114   0.04811   0.04111  -0.0287   0.1926   1.0000
  13.750   1.3866   0.05319   0.04609  -0.0279   0.1469   1.0000
  14.000   1.3583   0.05884   0.05156  -0.0272   0.1185   1.0000
  14.250   1.3323   0.06445   0.05710  -0.0267   0.0970   1.0000
  14.500   1.3011   0.07092   0.06348  -0.0266   0.0718   1.0000
  14.750   1.2756   0.07705   0.06961  -0.0267   0.0598   1.0000
  15.000   1.2564   0.08261   0.07524  -0.0271   0.0525   1.0000
  15.250   1.2380   0.08825   0.08096  -0.0277   0.0483   1.0000
  15.500   1.2204   0.09394   0.08678  -0.0285   0.0433   1.0000
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