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

GOE 285 AIRFOIL (goe285-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 285 AIRFOIL (goe285-il)
Reynolds number: 500,000
Max Cl/Cd: 86.97 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe285-il-500000-n5.txt
Download as CSV file: xf-goe285-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 285 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.4522   0.12006   0.11742  -0.0228   1.0000   0.0209
 -12.000  -0.4458   0.11737   0.11473  -0.0238   1.0000   0.0211
 -11.000  -0.7788   0.03767   0.03428  -0.0688   1.0000   0.0238
 -10.750  -0.7866   0.03400   0.03025  -0.0669   0.9996   0.0240
 -10.500  -0.7671   0.03065   0.02649  -0.0691   0.9959   0.0243
 -10.250  -0.7435   0.02836   0.02387  -0.0706   0.9928   0.0244
 -10.000  -0.7198   0.02650   0.02175  -0.0715   0.9889   0.0246
  -9.750  -0.6950   0.02451   0.01956  -0.0725   0.9856   0.0248
  -9.500  -0.6667   0.02313   0.01805  -0.0737   0.9830   0.0251
  -9.250  -0.6408   0.02205   0.01686  -0.0741   0.9778   0.0253
  -9.000  -0.6114   0.02105   0.01574  -0.0750   0.9740   0.0255
  -8.750  -0.5835   0.02017   0.01476  -0.0755   0.9687   0.0258
  -8.500  -0.5553   0.01938   0.01387  -0.0760   0.9625   0.0261
  -8.250  -0.5260   0.01861   0.01300  -0.0766   0.9570   0.0265
  -8.000  -0.4981   0.01784   0.01211  -0.0768   0.9493   0.0268
  -7.750  -0.4688   0.01709   0.01124  -0.0773   0.9414   0.0270
  -7.500  -0.4392   0.01638   0.01041  -0.0778   0.9306   0.0273
  -7.250  -0.4106   0.01575   0.00965  -0.0780   0.9165   0.0276
  -7.000  -0.3828   0.01518   0.00897  -0.0779   0.9013   0.0279
  -6.750  -0.3559   0.01469   0.00835  -0.0776   0.8864   0.0281
  -6.500  -0.3294   0.01425   0.00778  -0.0773   0.8720   0.0283
  -6.250  -0.3030   0.01386   0.00728  -0.0769   0.8586   0.0285
  -6.000  -0.2767   0.01350   0.00681  -0.0764   0.8447   0.0288
  -5.750  -0.2512   0.01298   0.00621  -0.0759   0.8309   0.0292
  -5.500  -0.2250   0.01259   0.00575  -0.0755   0.8185   0.0296
  -5.250  -0.1986   0.01228   0.00538  -0.0751   0.8063   0.0300
  -4.750  -0.1451   0.01176   0.00473  -0.0744   0.7814   0.0312
  -4.500  -0.1183   0.01152   0.00442  -0.0741   0.7666   0.0317
  -4.250  -0.0915   0.01131   0.00413  -0.0737   0.7505   0.0321
  -4.000  -0.0647   0.01113   0.00386  -0.0733   0.7337   0.0326
  -3.750  -0.0377   0.01096   0.00361  -0.0730   0.7179   0.0331
  -3.500  -0.0107   0.01079   0.00336  -0.0726   0.7011   0.0337
  -3.250   0.0160   0.01063   0.00312  -0.0723   0.6830   0.0347
  -3.000   0.0430   0.01051   0.00293  -0.0719   0.6671   0.0358
  -2.750   0.0702   0.01041   0.00275  -0.0717   0.6539   0.0371
  -2.500   0.0974   0.01033   0.00260  -0.0714   0.6399   0.0387
  -2.250   0.1244   0.01022   0.00246  -0.0711   0.6251   0.0425
  -2.000   0.1515   0.01011   0.00237  -0.0708   0.6104   0.0529
  -1.750   0.1787   0.01006   0.00232  -0.0706   0.5946   0.0672
  -1.500   0.2060   0.01005   0.00226  -0.0703   0.5783   0.0752
  -1.250   0.2334   0.01002   0.00220  -0.0701   0.5629   0.0816
  -1.000   0.2609   0.01002   0.00214  -0.0699   0.5477   0.0872
  -0.750   0.2881   0.01001   0.00210  -0.0697   0.5300   0.0940
  -0.500   0.3152   0.01003   0.00207  -0.0695   0.5092   0.1012
   0.000   0.3687   0.01012   0.00207  -0.0689   0.4679   0.1268
   0.250   0.3956   0.01017   0.00208  -0.0687   0.4514   0.1412
   1.000   0.4755   0.00997   0.00219  -0.0681   0.4149   0.2933
   1.250   0.5006   0.00962   0.00226  -0.0677   0.4047   0.4555
   1.500   0.5246   0.00918   0.00234  -0.0671   0.3957   0.6368
   1.750   0.5436   0.00857   0.00253  -0.0646   0.3866   0.9210
   2.000   0.5993   0.00874   0.00266  -0.0704   0.3734   0.9916
   2.250   0.6418   0.00890   0.00275  -0.0737   0.3612   1.0000
   2.500   0.6662   0.00906   0.00282  -0.0729   0.3502   1.0000
   2.750   0.6908   0.00921   0.00290  -0.0722   0.3379   1.0000
   3.000   0.7152   0.00937   0.00299  -0.0714   0.3248   1.0000
   3.250   0.7394   0.00956   0.00310  -0.0707   0.3114   1.0000
   3.500   0.7634   0.00977   0.00321  -0.0699   0.2980   1.0000
   3.750   0.7872   0.01001   0.00336  -0.0691   0.2835   1.0000
   4.000   0.8110   0.01026   0.00351  -0.0683   0.2708   1.0000
   4.250   0.8355   0.01047   0.00367  -0.0676   0.2613   1.0000
   4.500   0.8600   0.01070   0.00384  -0.0670   0.2540   1.0000
   4.750   0.8848   0.01090   0.00401  -0.0664   0.2473   1.0000
   5.000   0.9093   0.01114   0.00420  -0.0657   0.2411   1.0000
   5.250   0.9345   0.01133   0.00438  -0.0652   0.2365   1.0000
   5.500   0.9597   0.01152   0.00456  -0.0647   0.2324   1.0000
   5.750   0.9846   0.01173   0.00477  -0.0642   0.2286   1.0000
   6.000   1.0092   0.01197   0.00499  -0.0636   0.2248   1.0000
   6.250   1.0345   0.01216   0.00519  -0.0632   0.2209   1.0000
   6.500   1.0596   0.01237   0.00540  -0.0627   0.2165   1.0000
   6.750   1.0841   0.01261   0.00564  -0.0622   0.2120   1.0000
   7.000   1.1085   0.01287   0.00589  -0.0616   0.2075   1.0000
   7.250   1.1336   0.01306   0.00611  -0.0612   0.2028   1.0000
   7.500   1.1578   0.01333   0.00637  -0.0606   0.1962   1.0000
   7.750   1.1819   0.01359   0.00663  -0.0600   0.1875   1.0000
   8.000   1.2053   0.01390   0.00690  -0.0594   0.1745   1.0000
   8.250   1.2191   0.01497   0.00758  -0.0574   0.1158   1.0000
   8.500   1.2378   0.01563   0.00817  -0.0561   0.1005   1.0000
   8.750   1.2569   0.01624   0.00873  -0.0548   0.0880   1.0000
   9.000   1.2732   0.01702   0.00941  -0.0532   0.0665   1.0000
   9.250   1.2856   0.01806   0.01026  -0.0511   0.0426   1.0000
   9.500   1.3030   0.01866   0.01087  -0.0496   0.0388   1.0000
   9.750   1.3198   0.01921   0.01145  -0.0480   0.0370   1.0000
  10.000   1.3349   0.01980   0.01207  -0.0461   0.0355   1.0000
  10.250   1.3490   0.02047   0.01278  -0.0441   0.0342   1.0000
  10.500   1.3637   0.02111   0.01347  -0.0424   0.0332   1.0000
  10.750   1.3783   0.02177   0.01419  -0.0407   0.0325   1.0000
  11.000   1.3919   0.02252   0.01500  -0.0390   0.0319   1.0000
  11.250   1.4045   0.02334   0.01589  -0.0372   0.0312   1.0000
  11.500   1.4156   0.02430   0.01690  -0.0355   0.0305   1.0000
  11.750   1.4253   0.02539   0.01805  -0.0338   0.0298   1.0000
  12.000   1.4329   0.02669   0.01941  -0.0320   0.0291   1.0000
  12.250   1.4387   0.02819   0.02100  -0.0303   0.0286   1.0000
  12.500   1.4484   0.02947   0.02235  -0.0292   0.0282   1.0000
  12.750   1.4569   0.03090   0.02387  -0.0281   0.0278   1.0000
  13.000   1.4639   0.03252   0.02558  -0.0271   0.0273   1.0000
  13.250   1.4698   0.03433   0.02748  -0.0262   0.0268   1.0000
  13.500   1.4742   0.03634   0.02958  -0.0254   0.0264   1.0000
  13.750   1.4773   0.03858   0.03191  -0.0248   0.0260   1.0000
  14.000   1.4792   0.04105   0.03447  -0.0245   0.0256   1.0000
  14.250   1.4788   0.04386   0.03737  -0.0243   0.0252   1.0000
  14.500   1.4760   0.04705   0.04066  -0.0243   0.0248   1.0000
  14.750   1.4705   0.05069   0.04439  -0.0245   0.0245   1.0000
  15.000   1.4618   0.05481   0.04862  -0.0250   0.0242   1.0000
  15.250   1.4564   0.05866   0.05257  -0.0255   0.0240   1.0000
  15.500   1.4529   0.06235   0.05638  -0.0262   0.0237   1.0000
  15.750   1.4478   0.06635   0.06050  -0.0270   0.0235   1.0000
  16.000   1.4419   0.07055   0.06481  -0.0280   0.0232   1.0000
  16.250   1.4355   0.07490   0.06927  -0.0291   0.0230   1.0000
  16.500   1.4284   0.07941   0.07388  -0.0303   0.0227   1.0000
  16.750   1.4207   0.08401   0.07859  -0.0316   0.0224   1.0000
  17.000   1.4133   0.08863   0.08330  -0.0329   0.0221   1.0000
<< Back to GOE 285 AIRFOIL (goe285-il)

Polar data table (+)

Polar graphs


<< Back to GOE 285 AIRFOIL (goe285-il)