Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

GOE 777 AIRFOIL (goe777-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 777 AIRFOIL (goe777-il)
Reynolds number: 1,000,000
Max Cl/Cd: 101.81 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe777-il-1000000-n5.txt
Download as CSV file: xf-goe777-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 777 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -19.750  -1.0824   0.07117   0.06665  -0.0704   0.7348   0.0219
 -19.500  -1.1021   0.06492   0.06023  -0.0741   0.7206   0.0220
 -19.250  -1.1155   0.05961   0.05475  -0.0773   0.7064   0.0221
 -19.000  -1.1260   0.05484   0.04984  -0.0801   0.6928   0.0223
 -18.750  -1.1326   0.05078   0.04563  -0.0823   0.6799   0.0225
 -18.500  -1.1360   0.04730   0.04200  -0.0841   0.6655   0.0226
 -18.250  -1.1370   0.04421   0.03879  -0.0855   0.6519   0.0228
 -18.000  -1.1358   0.04146   0.03590  -0.0866   0.6377   0.0230
 -17.750  -1.1325   0.03901   0.03333  -0.0875   0.6225   0.0232
 -17.500  -1.1274   0.03680   0.03100  -0.0881   0.6087   0.0233
 -17.250  -1.1204   0.03483   0.02890  -0.0887   0.5954   0.0235
 -17.000  -1.1121   0.03304   0.02700  -0.0890   0.5839   0.0236
 -16.750  -1.1053   0.03116   0.02502  -0.0893   0.5745   0.0239
 -16.500  -1.0972   0.02946   0.02325  -0.0893   0.5668   0.0241
 -16.250  -1.0872   0.02801   0.02171  -0.0892   0.5589   0.0243
 -16.000  -1.0758   0.02674   0.02037  -0.0889   0.5525   0.0246
 -15.750  -1.0632   0.02562   0.01918  -0.0884   0.5475   0.0248
 -15.500  -1.0496   0.02462   0.01812  -0.0877   0.5426   0.0251
 -15.250  -1.0353   0.02374   0.01717  -0.0870   0.5379   0.0254
 -14.750  -1.0039   0.02223   0.01554  -0.0851   0.5307   0.0260
 -14.500  -0.9870   0.02158   0.01484  -0.0841   0.5283   0.0263
 -14.250  -0.9694   0.02099   0.01420  -0.0830   0.5259   0.0266
 -14.000  -0.9510   0.02046   0.01361  -0.0819   0.5233   0.0268
 -13.750  -0.9339   0.01990   0.01299  -0.0806   0.5208   0.0271
 -13.500  -0.9187   0.01938   0.01243  -0.0788   0.5184   0.0275
 -13.250  -0.9021   0.01895   0.01196  -0.0771   0.5159   0.0278
 -13.000  -0.8818   0.01852   0.01149  -0.0760   0.5133   0.0282
 -12.500  -0.8383   0.01775   0.01065  -0.0740   0.5095   0.0290
 -12.250  -0.8154   0.01739   0.01026  -0.0732   0.5084   0.0294
 -12.000  -0.7919   0.01706   0.00990  -0.0724   0.5071   0.0299
 -11.750  -0.7679   0.01674   0.00955  -0.0717   0.5058   0.0303
 -11.500  -0.7441   0.01640   0.00918  -0.0709   0.5044   0.0307
 -11.250  -0.7204   0.01604   0.00879  -0.0702   0.5029   0.0312
 -11.000  -0.6960   0.01572   0.00845  -0.0695   0.5014   0.0317
 -10.750  -0.6711   0.01542   0.00813  -0.0688   0.4999   0.0323
 -10.500  -0.6458   0.01514   0.00783  -0.0683   0.4982   0.0329
 -10.250  -0.6202   0.01490   0.00754  -0.0677   0.4964   0.0336
 -10.000  -0.5942   0.01467   0.00728  -0.0672   0.4946   0.0341
  -9.750  -0.5687   0.01439   0.00698  -0.0667   0.4929   0.0349
  -9.500  -0.5428   0.01414   0.00672  -0.0662   0.4912   0.0357
  -9.250  -0.5166   0.01392   0.00648  -0.0657   0.4895   0.0366
  -9.000  -0.4899   0.01370   0.00625  -0.0654   0.4889   0.0377
  -8.750  -0.4632   0.01347   0.00601  -0.0650   0.4882   0.0389
  -8.500  -0.4364   0.01324   0.00579  -0.0646   0.4875   0.0404
  -8.250  -0.4092   0.01304   0.00558  -0.0643   0.4868   0.0421
  -8.000  -0.3821   0.01283   0.00538  -0.0640   0.4858   0.0441
  -7.750  -0.3547   0.01264   0.00520  -0.0637   0.4846   0.0466
  -7.500  -0.3272   0.01245   0.00503  -0.0634   0.4832   0.0497
  -7.250  -0.2995   0.01229   0.00488  -0.0632   0.4815   0.0531
  -7.000  -0.2714   0.01216   0.00475  -0.0631   0.4797   0.0567
  -6.750  -0.2434   0.01203   0.00462  -0.0629   0.4776   0.0597
  -6.500  -0.2151   0.01193   0.00450  -0.0628   0.4756   0.0622
  -6.250  -0.1870   0.01182   0.00440  -0.0626   0.4739   0.0644
  -6.000  -0.1586   0.01174   0.00430  -0.0625   0.4725   0.0666
  -5.750  -0.1302   0.01168   0.00421  -0.0624   0.4707   0.0683
  -5.500  -0.1018   0.01157   0.00411  -0.0623   0.4693   0.0702
  -5.250  -0.0731   0.01146   0.00401  -0.0623   0.4682   0.0722
  -5.000  -0.0442   0.01137   0.00392  -0.0623   0.4669   0.0739
  -4.750  -0.0152   0.01129   0.00383  -0.0623   0.4656   0.0751
  -4.500   0.0133   0.01117   0.00372  -0.0623   0.4640   0.0767
  -4.250   0.0420   0.01108   0.00363  -0.0623   0.4622   0.0783
  -4.000   0.0708   0.01100   0.00355  -0.0623   0.4603   0.0801
  -3.750   0.0996   0.01094   0.00347  -0.0623   0.4584   0.0818
  -3.500   0.1283   0.01087   0.00339  -0.0623   0.4565   0.0838
  -3.250   0.1568   0.01079   0.00332  -0.0623   0.4544   0.0862
  -3.000   0.1853   0.01074   0.00326  -0.0623   0.4523   0.0888
  -2.750   0.2143   0.01069   0.00321  -0.0624   0.4510   0.0911
  -2.500   0.2432   0.01060   0.00315  -0.0625   0.4498   0.0943
  -2.250   0.2721   0.01052   0.00310  -0.0626   0.4484   0.0978
  -2.000   0.3011   0.01045   0.00305  -0.0627   0.4467   0.1027
  -1.750   0.3298   0.01037   0.00300  -0.0628   0.4447   0.1108
  -1.500   0.3578   0.01023   0.00294  -0.0628   0.4425   0.1330
  -1.250   0.3843   0.00994   0.00285  -0.0626   0.4401   0.1942
  -1.000   0.4109   0.00970   0.00280  -0.0625   0.4374   0.2543
  -0.750   0.4381   0.00954   0.00278  -0.0624   0.4345   0.3040
  -0.500   0.4662   0.00938   0.00277  -0.0625   0.4322   0.3447
  -0.250   0.4943   0.00926   0.00276  -0.0625   0.4289   0.3807
   0.000   0.5222   0.00914   0.00275  -0.0626   0.4252   0.4195
   0.250   0.5485   0.00892   0.00275  -0.0624   0.4210   0.4937
   0.500   0.5760   0.00885   0.00280  -0.0624   0.4170   0.5441
   0.750   0.6047   0.00885   0.00284  -0.0625   0.4121   0.5677
   1.000   0.6328   0.00888   0.00290  -0.0626   0.4050   0.5896
   1.250   0.6609   0.00894   0.00296  -0.0627   0.3977   0.6034
   1.500   0.6886   0.00907   0.00304  -0.0627   0.3876   0.6126
   1.750   0.7159   0.00919   0.00314  -0.0627   0.3772   0.6228
   2.000   0.7427   0.00936   0.00327  -0.0626   0.3669   0.6352
   2.500   0.7959   0.00969   0.00355  -0.0624   0.3494   0.6574
   2.750   0.8222   0.00987   0.00372  -0.0623   0.3419   0.6676
   3.000   0.8488   0.01002   0.00387  -0.0622   0.3363   0.6802
   3.250   0.8753   0.01015   0.00402  -0.0621   0.3311   0.6938
   3.500   0.9012   0.01032   0.00420  -0.0620   0.3261   0.7083
   3.750   0.9273   0.01046   0.00436  -0.0619   0.3222   0.7225
   4.000   0.9537   0.01055   0.00451  -0.0618   0.3197   0.7431
   4.250   0.9794   0.01063   0.00468  -0.0615   0.3170   0.7700
   4.500   1.0046   0.01074   0.00486  -0.0613   0.3143   0.7960
   4.750   1.0294   0.01088   0.00506  -0.0609   0.3117   0.8203
   5.000   1.0536   0.01103   0.00527  -0.0605   0.3090   0.8460
   5.500   1.1019   0.01127   0.00567  -0.0595   0.3052   0.9004
   5.750   1.1285   0.01140   0.00589  -0.0594   0.3038   0.9385
   6.000   1.1655   0.01162   0.00614  -0.0617   0.3021   0.9705
   6.250   1.1993   0.01185   0.00637  -0.0634   0.3003   0.9873
   6.500   1.2314   0.01210   0.00661  -0.0648   0.2986   0.9961
   6.750   1.2574   0.01235   0.00686  -0.0650   0.2969   1.0000
   7.000   1.2722   0.01259   0.00710  -0.0629   0.2953   1.0000
   7.250   1.2874   0.01287   0.00738  -0.0610   0.2936   1.0000
   7.500   1.3037   0.01320   0.00771  -0.0594   0.2918   1.0000
   7.750   1.3210   0.01355   0.00807  -0.0581   0.2901   1.0000
   8.000   1.3416   0.01383   0.00837  -0.0574   0.2893   1.0000
   8.250   1.3619   0.01414   0.00870  -0.0567   0.2884   1.0000
   8.500   1.3818   0.01450   0.00908  -0.0560   0.2874   1.0000
   8.750   1.4014   0.01489   0.00950  -0.0554   0.2864   1.0000
   9.000   1.4205   0.01533   0.00997  -0.0548   0.2853   1.0000
   9.250   1.4389   0.01584   0.01050  -0.0542   0.2839   1.0000
   9.500   1.4565   0.01641   0.01110  -0.0535   0.2824   1.0000
   9.750   1.4730   0.01709   0.01179  -0.0529   0.2806   1.0000
  10.000   1.4884   0.01788   0.01260  -0.0523   0.2789   1.0000
  10.250   1.5026   0.01880   0.01354  -0.0517   0.2772   1.0000
  10.500   1.5158   0.01984   0.01461  -0.0511   0.2756   1.0000
  10.750   1.5291   0.02092   0.01572  -0.0507   0.2743   1.0000
  11.000   1.5462   0.02177   0.01662  -0.0506   0.2735   1.0000
  11.250   1.5624   0.02270   0.01760  -0.0505   0.2724   1.0000
  11.500   1.5770   0.02377   0.01871  -0.0503   0.2710   1.0000
  11.750   1.5902   0.02497   0.01995  -0.0501   0.2694   1.0000
  12.000   1.6017   0.02631   0.02133  -0.0498   0.2675   1.0000
  12.250   1.6105   0.02789   0.02294  -0.0495   0.2653   1.0000
  12.500   1.6155   0.02978   0.02487  -0.0490   0.2629   1.0000
  12.750   1.6175   0.03195   0.02706  -0.0484   0.2605   1.0000
  13.000   1.6233   0.03379   0.02894  -0.0480   0.2590   1.0000
  13.250   1.6336   0.03522   0.03043  -0.0477   0.2580   1.0000
  13.500   1.6414   0.03691   0.03218  -0.0475   0.2566   1.0000
  13.750   1.6495   0.03857   0.03389  -0.0472   0.2549   1.0000
  14.000   1.6544   0.04056   0.03593  -0.0469   0.2531   1.0000
  14.250   1.6595   0.04251   0.03792  -0.0466   0.2511   1.0000
  14.500   1.6601   0.04493   0.04038  -0.0463   0.2489   1.0000
  14.750   1.6601   0.04739   0.04287  -0.0459   0.2465   1.0000
  15.000   1.6628   0.04966   0.04518  -0.0457   0.2445   1.0000
  15.250   1.6716   0.05131   0.04688  -0.0456   0.2425   1.0000
  15.500   1.6756   0.05346   0.04908  -0.0455   0.2395   1.0000
  15.750   1.6752   0.05605   0.05170  -0.0453   0.2356   1.0000
  16.000   1.6714   0.05898   0.05464  -0.0450   0.2319   1.0000
  16.250   1.6761   0.06110   0.05681  -0.0450   0.2296   1.0000
  16.500   1.6818   0.06307   0.05883  -0.0450   0.2266   1.0000
  16.750   1.6829   0.06555   0.06133  -0.0449   0.2222   1.0000
  17.000   1.6754   0.06898   0.06478  -0.0448   0.2176   1.0000
  17.250   1.6765   0.07149   0.06731  -0.0448   0.2117   1.0000
  17.500   1.6652   0.07535   0.07118  -0.0447   0.2055   1.0000
  17.750   1.6566   0.07894   0.07477  -0.0447   0.1969   1.0000
  18.000   1.6404   0.08347   0.07929  -0.0447   0.1881   1.0000
  18.250   1.6248   0.08791   0.08372  -0.0447   0.1795   1.0000
<< Back to GOE 777 AIRFOIL (goe777-il)

Polar data table (+)

Polar graphs


<< Back to GOE 777 AIRFOIL (goe777-il)