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GOE 285 AIRFOIL (goe285-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 285 AIRFOIL (goe285-il)
Reynolds number: 1,000,000
Max Cl/Cd: 109.14 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe285-il-1000000.txt
Download as CSV file: xf-goe285-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.2918   0.10382   0.10214  -0.0343   1.0000   0.0265
 -10.750  -0.7605   0.03817   0.03575  -0.0662   1.0000   0.0243
 -10.500  -0.7771   0.03397   0.03120  -0.0634   0.9998   0.0245
 -10.250  -0.7579   0.03028   0.02712  -0.0658   0.9975   0.0247
 -10.000  -0.7320   0.02809   0.02465  -0.0676   0.9954   0.0249
  -9.750  -0.7062   0.02565   0.02187  -0.0694   0.9938   0.0251
  -9.500  -0.6874   0.02210   0.01798  -0.0701   0.9904   0.0254
  -9.250  -0.6589   0.02060   0.01636  -0.0712   0.9879   0.0257
  -9.000  -0.6277   0.01954   0.01520  -0.0725   0.9860   0.0260
  -8.750  -0.5950   0.01861   0.01419  -0.0741   0.9844   0.0263
  -8.500  -0.5603   0.01787   0.01338  -0.0759   0.9831   0.0267
  -8.250  -0.5315   0.01711   0.01255  -0.0763   0.9777   0.0270
  -8.000  -0.5002   0.01626   0.01158  -0.0773   0.9732   0.0273
  -7.750  -0.4713   0.01547   0.01069  -0.0776   0.9672   0.0276
  -7.500  -0.4430   0.01476   0.00988  -0.0778   0.9594   0.0278
  -7.250  -0.4156   0.01411   0.00915  -0.0776   0.9491   0.0281
  -7.000  -0.3881   0.01354   0.00848  -0.0775   0.9371   0.0284
  -6.750  -0.3612   0.01306   0.00790  -0.0771   0.9232   0.0286
  -6.500  -0.3349   0.01265   0.00739  -0.0767   0.9075   0.0288
  -6.250  -0.3085   0.01234   0.00696  -0.0762   0.8914   0.0290
  -6.000  -0.2833   0.01171   0.00621  -0.0756   0.8756   0.0294
  -5.750  -0.2584   0.01107   0.00548  -0.0749   0.8602   0.0300
  -5.500  -0.2322   0.01071   0.00506  -0.0745   0.8459   0.0305
  -5.250  -0.2055   0.01042   0.00470  -0.0741   0.8331   0.0309
  -5.000  -0.1787   0.01015   0.00437  -0.0737   0.8209   0.0313
  -4.750  -0.1518   0.00992   0.00407  -0.0734   0.8085   0.0318
  -4.500  -0.1247   0.00969   0.00377  -0.0731   0.7955   0.0322
  -4.250  -0.0973   0.00948   0.00351  -0.0728   0.7832   0.0328
  -4.000  -0.0699   0.00930   0.00326  -0.0725   0.7708   0.0332
  -3.750  -0.0426   0.00915   0.00304  -0.0722   0.7568   0.0336
  -3.500  -0.0155   0.00891   0.00273  -0.0719   0.7413   0.0345
  -3.250   0.0117   0.00872   0.00248  -0.0716   0.7249   0.0356
  -2.750   0.0666   0.00852   0.00215  -0.0711   0.6900   0.0382
  -2.500   0.0940   0.00843   0.00199  -0.0708   0.6727   0.0400
  -2.250   0.1213   0.00834   0.00186  -0.0706   0.6562   0.0435
  -2.000   0.1488   0.00821   0.00177  -0.0704   0.6420   0.0586
  -1.750   0.1766   0.00814   0.00174  -0.0703   0.6300   0.0753
  -1.500   0.2046   0.00812   0.00169  -0.0701   0.6187   0.0828
  -1.250   0.2325   0.00812   0.00165  -0.0700   0.6069   0.0883
  -1.000   0.2606   0.00808   0.00161  -0.0699   0.5951   0.0949
  -0.750   0.2885   0.00807   0.00158  -0.0698   0.5824   0.1016
  -0.500   0.3163   0.00805   0.00156  -0.0697   0.5679   0.1117
  -0.250   0.3440   0.00804   0.00154  -0.0696   0.5512   0.1263
   0.000   0.3715   0.00804   0.00153  -0.0694   0.5316   0.1452
   0.250   0.3988   0.00806   0.00152  -0.0692   0.5087   0.1669
   0.500   0.4255   0.00803   0.00154  -0.0690   0.4853   0.2091
   0.750   0.4510   0.00775   0.00158  -0.0688   0.4649   0.3517
   1.000   0.4744   0.00716   0.00165  -0.0682   0.4488   0.6077
   1.250   0.4918   0.00648   0.00178  -0.0657   0.4361   0.8814
   1.500   0.5215   0.00654   0.00191  -0.0657   0.4232   0.9673
   1.750   0.5605   0.00669   0.00199  -0.0680   0.4112   0.9856
   2.000   0.6006   0.00685   0.00207  -0.0706   0.3996   0.9937
   2.250   0.6536   0.00703   0.00216  -0.0761   0.3860   0.9999
   2.500   0.6789   0.00715   0.00221  -0.0755   0.3749   1.0000
   2.750   0.7037   0.00726   0.00227  -0.0749   0.3637   1.0000
   3.000   0.7282   0.00741   0.00235  -0.0741   0.3500   1.0000
   3.250   0.7523   0.00760   0.00243  -0.0733   0.3308   1.0000
   3.500   0.7756   0.00786   0.00255  -0.0724   0.3062   1.0000
   3.750   0.7992   0.00809   0.00267  -0.0715   0.2870   1.0000
   4.000   0.8232   0.00830   0.00280  -0.0707   0.2744   1.0000
   4.250   0.8476   0.00849   0.00293  -0.0700   0.2651   1.0000
   4.500   0.8719   0.00867   0.00307  -0.0693   0.2572   1.0000
   4.750   0.8967   0.00885   0.00321  -0.0686   0.2506   1.0000
   5.000   0.9212   0.00906   0.00337  -0.0680   0.2442   1.0000
   5.250   0.9469   0.00918   0.00350  -0.0675   0.2412   1.0000
   5.500   0.9724   0.00934   0.00364  -0.0670   0.2371   1.0000
   5.750   0.9976   0.00953   0.00381  -0.0665   0.2328   1.0000
   6.000   1.0227   0.00973   0.00399  -0.0660   0.2283   1.0000
   6.250   1.0490   0.00986   0.00413  -0.0657   0.2254   1.0000
   6.500   1.0746   0.01003   0.00430  -0.0653   0.2208   1.0000
   6.750   1.0996   0.01026   0.00450  -0.0648   0.2152   1.0000
   7.000   1.1255   0.01042   0.00466  -0.0645   0.2111   1.0000
   7.250   1.1513   0.01058   0.00483  -0.0642   0.2061   1.0000
   7.500   1.1759   0.01084   0.00506  -0.0637   0.1991   1.0000
   7.750   1.2016   0.01101   0.00523  -0.0633   0.1912   1.0000
   8.000   1.2246   0.01140   0.00548  -0.0626   0.1688   1.0000
   8.250   1.2357   0.01275   0.00640  -0.0601   0.1010   1.0000
   8.500   1.2541   0.01349   0.00700  -0.0587   0.0769   1.0000
   8.750   1.2680   0.01458   0.00782  -0.0566   0.0415   1.0000
   9.000   1.2886   0.01509   0.00831  -0.0556   0.0378   1.0000
   9.250   1.3092   0.01558   0.00881  -0.0545   0.0353   1.0000
   9.500   1.3305   0.01599   0.00926  -0.0535   0.0343   1.0000
   9.750   1.3508   0.01645   0.00975  -0.0524   0.0333   1.0000
  10.000   1.3698   0.01697   0.01029  -0.0512   0.0322   1.0000
  10.250   1.3868   0.01759   0.01094  -0.0496   0.0311   1.0000
  10.500   1.4011   0.01822   0.01162  -0.0475   0.0301   1.0000
  10.750   1.4174   0.01871   0.01215  -0.0458   0.0297   1.0000
  11.000   1.4327   0.01927   0.01276  -0.0440   0.0292   1.0000
  11.250   1.4472   0.01989   0.01343  -0.0422   0.0286   1.0000
  11.500   1.4608   0.02058   0.01417  -0.0404   0.0280   1.0000
  11.750   1.4733   0.02135   0.01499  -0.0385   0.0274   1.0000
  12.000   1.4836   0.02230   0.01598  -0.0365   0.0268   1.0000
  12.250   1.4900   0.02353   0.01728  -0.0343   0.0262   1.0000
  12.500   1.4912   0.02522   0.01906  -0.0319   0.0256   1.0000
  12.750   1.5034   0.02621   0.02011  -0.0306   0.0254   1.0000
  13.000   1.5147   0.02731   0.02127  -0.0295   0.0250   1.0000
  13.250   1.5246   0.02858   0.02261  -0.0284   0.0246   1.0000
  13.500   1.5328   0.03004   0.02414  -0.0273   0.0242   1.0000
  13.750   1.5396   0.03170   0.02586  -0.0264   0.0237   1.0000
  14.000   1.5452   0.03354   0.02777  -0.0255   0.0234   1.0000
  14.250   1.5490   0.03563   0.02993  -0.0248   0.0230   1.0000
  14.500   1.5510   0.03799   0.03237  -0.0243   0.0227   1.0000
  14.750   1.5494   0.04086   0.03532  -0.0239   0.0224   1.0000
  15.000   1.5425   0.04444   0.03899  -0.0238   0.0220   1.0000
  15.250   1.5290   0.04893   0.04360  -0.0240   0.0217   1.0000
  15.500   1.5229   0.05270   0.04747  -0.0243   0.0215   1.0000
  15.750   1.5243   0.05563   0.05048  -0.0247   0.0213   1.0000
  16.000   1.5236   0.05889   0.05384  -0.0252   0.0211   1.0000
  16.250   1.5201   0.06261   0.05765  -0.0259   0.0208   1.0000
  16.500   1.5149   0.06661   0.06175  -0.0267   0.0206   1.0000
  16.750   1.5089   0.07079   0.06602  -0.0277   0.0204   1.0000
  17.000   1.5012   0.07531   0.07064  -0.0289   0.0202   1.0000
  17.250   1.4934   0.07986   0.07528  -0.0301   0.0199   1.0000
  17.500   1.4854   0.08447   0.07997  -0.0314   0.0197   1.0000
  17.750   1.4771   0.08918   0.08476  -0.0327   0.0195   1.0000
  18.000   1.4688   0.09392   0.08959  -0.0342   0.0193   1.0000
  18.250   1.4602   0.09871   0.09445  -0.0357   0.0192   1.0000
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