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GOE 369 AIRFOIL (goe369-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 369 AIRFOIL (goe369-il)
Reynolds number: 1,000,000
Max Cl/Cd: 121.85 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe369-il-1000000.txt
Download as CSV file: xf-goe369-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 369 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3529   0.09324   0.09169  -0.0102   1.0000   0.0068
  -7.750  -0.3488   0.09068   0.08914  -0.0109   1.0000   0.0068
  -7.500  -0.3478   0.08821   0.08670  -0.0113   1.0000   0.0068
  -7.250  -0.3429   0.08531   0.08382  -0.0133   1.0000   0.0068
  -7.000  -0.3345   0.08215   0.08068  -0.0160   1.0000   0.0069
  -6.750  -0.3248   0.07899   0.07752  -0.0185   1.0000   0.0069
  -6.500  -0.3051   0.07492   0.07345  -0.0236   0.9975   0.0069
  -6.250  -0.2836   0.06977   0.06829  -0.0283   0.9797   0.0070
  -6.000  -0.2299   0.06423   0.06268  -0.0408   0.9484   0.0074
  -5.750  -0.1882   0.06006   0.05811  -0.0495   0.8436   0.0081
  -5.500  -0.1724   0.05738   0.05519  -0.0511   0.7980   0.0087
  -5.250  -0.1487   0.05433   0.05199  -0.0539   0.7740   0.0093
  -5.000  -0.1230   0.05122   0.04871  -0.0568   0.7552   0.0094
  -4.750  -0.0970   0.04802   0.04536  -0.0592   0.7398   0.0095
  -4.500  -0.0729   0.04503   0.04225  -0.0608   0.7262   0.0095
  -4.250  -0.0481   0.04206   0.03914  -0.0621   0.7142   0.0095
  -4.000  -0.0252   0.03796   0.03489  -0.0635   0.7032   0.0097
  -3.750  -0.0038   0.03560   0.03242  -0.0641   0.6918   0.0099
  -3.500   0.0202   0.03341   0.03011  -0.0647   0.6812   0.0101
  -3.250   0.0461   0.03117   0.02774  -0.0652   0.6720   0.0104
  -3.000   0.0726   0.02899   0.02539  -0.0655   0.6631   0.0109
  -2.750   0.1007   0.02667   0.02291  -0.0656   0.6550   0.0120
  -2.500   0.1333   0.02443   0.02039  -0.0647   0.6481   0.0127
  -2.250   0.1576   0.02107   0.01680  -0.0646   0.6419   0.0133
  -2.000   0.1828   0.01993   0.01554  -0.0645   0.6354   0.0140
  -1.750   0.2098   0.01857   0.01402  -0.0641   0.6290   0.0152
  -1.500   0.2404   0.01776   0.01295  -0.0629   0.6221   0.0168
  -1.250   0.2673   0.01631   0.01126  -0.0623   0.6154   0.0169
  -1.000   0.2923   0.01356   0.00826  -0.0618   0.6088   0.0177
  -0.750   0.3189   0.01264   0.00721  -0.0613   0.6021   0.0183
  -0.500   0.3468   0.01063   0.00484  -0.0602   0.5957   0.0161
  -0.250   0.3740   0.01002   0.00405  -0.0596   0.5894   0.0166
   0.000   0.4007   0.00919   0.00316  -0.0592   0.5831   0.0182
   0.250   0.4275   0.00885   0.00278  -0.0588   0.5763   0.0193
   0.500   0.4546   0.00851   0.00239  -0.0584   0.5691   0.0208
   0.750   0.4815   0.00839   0.00220  -0.0580   0.5606   0.0221
   1.000   0.5076   0.00793   0.00175  -0.0576   0.5512   0.0250
   1.250   0.5344   0.00779   0.00158  -0.0572   0.5393   0.0272
   1.500   0.5612   0.00771   0.00145  -0.0568   0.5268   0.0291
   1.750   0.5878   0.00757   0.00125  -0.0564   0.5142   0.0323
   2.000   0.6146   0.00753   0.00115  -0.0561   0.5008   0.0349
   2.250   0.6414   0.00754   0.00110  -0.0558   0.4837   0.0378
   2.500   0.6681   0.00759   0.00108  -0.0554   0.4641   0.0414
   2.750   0.6945   0.00765   0.00114  -0.0551   0.4428   0.0754
   3.000   0.7384   0.00606   0.00139  -0.0595   0.4105   1.0000
   3.250   0.7634   0.00631   0.00150  -0.0589   0.3809   1.0000
   3.500   0.7883   0.00658   0.00162  -0.0583   0.3528   1.0000
   3.750   0.8132   0.00685   0.00176  -0.0577   0.3269   1.0000
   4.000   0.8384   0.00709   0.00190  -0.0572   0.3052   1.0000
   4.250   0.8635   0.00734   0.00206  -0.0567   0.2842   1.0000
   4.500   0.8884   0.00763   0.00223  -0.0562   0.2584   1.0000
   4.750   0.9127   0.00798   0.00243  -0.0556   0.2250   1.0000
   5.000   0.9364   0.00841   0.00268  -0.0549   0.1906   1.0000
   5.250   0.9607   0.00877   0.00292  -0.0543   0.1706   1.0000
   5.500   0.9854   0.00907   0.00317  -0.0538   0.1563   1.0000
   5.750   1.0102   0.00936   0.00340  -0.0533   0.1451   1.0000
   6.000   1.0354   0.00959   0.00361  -0.0529   0.1362   1.0000
   6.250   1.0603   0.00985   0.00384  -0.0524   0.1263   1.0000
   6.500   1.0850   0.01014   0.00411  -0.0519   0.1157   1.0000
   6.750   1.1094   0.01046   0.00437  -0.0514   0.1064   1.0000
   7.000   1.1342   0.01073   0.00465  -0.0509   0.1005   1.0000
   7.250   1.1583   0.01107   0.00495  -0.0504   0.0943   1.0000
   7.500   1.1829   0.01134   0.00527  -0.0499   0.0906   1.0000
   7.750   1.2073   0.01162   0.00558  -0.0494   0.0874   1.0000
   8.000   1.2309   0.01200   0.00594  -0.0488   0.0821   1.0000
   8.250   1.2552   0.01227   0.00626  -0.0483   0.0779   1.0000
   8.500   1.2793   0.01256   0.00656  -0.0478   0.0738   1.0000
   8.750   1.3020   0.01300   0.00699  -0.0472   0.0675   1.0000
   9.000   1.3265   0.01323   0.00727  -0.0467   0.0647   1.0000
   9.250   1.3495   0.01361   0.00764  -0.0461   0.0591   1.0000
   9.500   1.3723   0.01399   0.00804  -0.0455   0.0542   1.0000
   9.750   1.3943   0.01444   0.00847  -0.0448   0.0483   1.0000
  10.000   1.4163   0.01489   0.00893  -0.0441   0.0435   1.0000
  10.250   1.4367   0.01547   0.00948  -0.0432   0.0369   1.0000
  10.500   1.4567   0.01607   0.01009  -0.0422   0.0301   1.0000
  10.750   1.4698   0.01734   0.01120  -0.0404   0.0139   1.0000
  11.000   1.4851   0.01834   0.01225  -0.0388   0.0099   1.0000
  11.250   1.5002   0.01932   0.01330  -0.0372   0.0083   1.0000
  11.500   1.5148   0.02028   0.01436  -0.0355   0.0072   1.0000
  11.750   1.5301   0.02108   0.01526  -0.0340   0.0068   1.0000
  12.000   1.5431   0.02200   0.01628  -0.0322   0.0062   1.0000
  12.250   1.5527   0.02303   0.01740  -0.0300   0.0058   1.0000
  12.500   1.5544   0.02429   0.01878  -0.0266   0.0054   1.0000
  12.750   1.5472   0.02617   0.02083  -0.0226   0.0050   1.0000
  13.000   1.5518   0.02741   0.02218  -0.0204   0.0049   1.0000
  13.250   1.5557   0.02884   0.02371  -0.0187   0.0048   1.0000
  13.500   1.5566   0.03069   0.02569  -0.0172   0.0046   1.0000
  13.750   1.5556   0.03295   0.02807  -0.0163   0.0045   1.0000
  14.000   1.5561   0.03529   0.03052  -0.0158   0.0043   1.0000
  14.250   1.5532   0.03817   0.03354  -0.0156   0.0042   1.0000
  14.500   1.5524   0.04096   0.03644  -0.0158   0.0040   1.0000
  14.750   1.5432   0.04491   0.04054  -0.0164   0.0040   1.0000
  15.000   1.5430   0.04786   0.04357  -0.0169   0.0038   1.0000
  15.250   1.5327   0.05225   0.04810  -0.0180   0.0038   1.0000
  15.500   1.5191   0.05730   0.05329  -0.0196   0.0037   1.0000
  15.750   1.5072   0.06231   0.05842  -0.0213   0.0037   1.0000
  16.000   1.4919   0.06806   0.06430  -0.0236   0.0036   1.0000
  16.250   1.4742   0.07459   0.07097  -0.0265   0.0036   1.0000
  16.500   1.4545   0.08192   0.07845  -0.0300   0.0035   1.0000
  16.750   1.4348   0.08958   0.08625  -0.0337   0.0036   1.0000
  17.000   1.4145   0.09766   0.09448  -0.0377   0.0037   1.0000
  17.250   1.3905   0.10671   0.10367  -0.0424   0.0037   1.0000
  17.500   1.3670   0.11591   0.11301  -0.0472   0.0037   1.0000
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