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GOE 614 AIRFOIL (goe614-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 614 AIRFOIL (goe614-il)
Reynolds number: 500,000
Max Cl/Cd: 84.83 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe614-il-500000.txt
Download as CSV file: xf-goe614-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 614 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.0549   0.11013   0.10765  -0.1005   0.9703   0.0464
 -12.250  -0.4343   0.03671   0.03252  -0.1629   0.9437   0.0357
 -12.000  -0.4186   0.03478   0.03033  -0.1653   0.9372   0.0354
 -11.750  -0.4028   0.03359   0.02898  -0.1657   0.9277   0.0353
 -11.500  -0.3819   0.03196   0.02716  -0.1669   0.9202   0.0352
 -11.250  -0.3605   0.02929   0.02441  -0.1677   0.9115   0.0350
 -11.000  -0.3410   0.02756   0.02252  -0.1681   0.9026   0.0349
 -10.750  -0.3219   0.02606   0.02084  -0.1680   0.8926   0.0348
 -10.500  -0.3055   0.02491   0.01955  -0.1670   0.8820   0.0348
 -10.250  -0.2833   0.02381   0.01826  -0.1669   0.8729   0.0349
 -10.000  -0.2681   0.02293   0.01726  -0.1652   0.8619   0.0349
  -9.750  -0.2468   0.02210   0.01626  -0.1646   0.8532   0.0350
  -9.500  -0.2288   0.02134   0.01539  -0.1632   0.8428   0.0351
  -9.250  -0.2085   0.02076   0.01466  -0.1622   0.8337   0.0353
  -9.000  -0.1889   0.01956   0.01340  -0.1611   0.8243   0.0355
  -8.750  -0.1675   0.01863   0.01242  -0.1603   0.8159   0.0358
  -8.500  -0.1478   0.01798   0.01173  -0.1590   0.8063   0.0359
  -8.250  -0.1267   0.01738   0.01105  -0.1579   0.7975   0.0361
  -8.000  -0.1073   0.01682   0.01045  -0.1565   0.7878   0.0364
  -7.750  -0.0862   0.01632   0.00989  -0.1554   0.7792   0.0366
  -7.500  -0.0664   0.01585   0.00938  -0.1539   0.7697   0.0368
  -7.250  -0.0453   0.01543   0.00888  -0.1527   0.7608   0.0371
  -7.000  -0.0253   0.01502   0.00843  -0.1513   0.7508   0.0373
  -6.750  -0.0043   0.01465   0.00799  -0.1500   0.7413   0.0376
  -6.500   0.0162   0.01430   0.00757  -0.1486   0.7309   0.0380
  -6.250   0.0373   0.01397   0.00719  -0.1473   0.7211   0.0384
  -6.000   0.0585   0.01367   0.00682  -0.1459   0.7108   0.0387
  -5.750   0.0799   0.01338   0.00646  -0.1446   0.7007   0.0392
  -5.250   0.1233   0.01293   0.00586  -0.1421   0.6793   0.0402
  -5.000   0.1438   0.01261   0.00546  -0.1407   0.6686   0.0409
  -4.750   0.1651   0.01235   0.00513  -0.1393   0.6578   0.0418
  -4.500   0.1874   0.01218   0.00489  -0.1382   0.6477   0.0427
  -4.250   0.2097   0.01204   0.00466  -0.1369   0.6375   0.0437
  -4.000   0.2326   0.01192   0.00447  -0.1358   0.6278   0.0449
  -3.750   0.2549   0.01181   0.00427  -0.1346   0.6182   0.0468
  -3.500   0.2776   0.01165   0.00409  -0.1335   0.6089   0.0502
  -3.250   0.2977   0.01134   0.00391  -0.1320   0.5998   0.0911
  -3.000   0.3205   0.01121   0.00383  -0.1310   0.5913   0.1106
  -2.750   0.3427   0.01113   0.00373  -0.1298   0.5829   0.1264
  -2.500   0.3648   0.01094   0.00368  -0.1287   0.5755   0.1610
  -2.250   0.3875   0.01088   0.00369  -0.1277   0.5679   0.1931
  -2.000   0.4107   0.01091   0.00370  -0.1267   0.5610   0.2114
  -1.750   0.4345   0.01090   0.00370  -0.1258   0.5542   0.2247
  -1.500   0.4574   0.01094   0.00370  -0.1247   0.5474   0.2365
  -1.250   0.4806   0.01097   0.00372  -0.1237   0.5412   0.2472
  -1.000   0.5034   0.01099   0.00373  -0.1226   0.5346   0.2583
  -0.750   0.5248   0.01102   0.00374  -0.1213   0.5284   0.2697
  -0.500   0.5471   0.01105   0.00377  -0.1201   0.5227   0.2815
  -0.250   0.5684   0.01106   0.00380  -0.1187   0.5165   0.2945
   0.000   0.5893   0.01110   0.00383  -0.1173   0.5105   0.3091
   0.250   0.6112   0.01114   0.00389  -0.1161   0.5049   0.3245
   0.500   0.6327   0.01114   0.00394  -0.1148   0.4995   0.3427
   0.750   0.6534   0.01118   0.00401  -0.1134   0.4939   0.3659
   1.000   0.6750   0.01127   0.00412  -0.1122   0.4886   0.3918
   1.250   0.6962   0.01128   0.00421  -0.1108   0.4834   0.4153
   1.500   0.7166   0.01134   0.00430  -0.1094   0.4776   0.4390
   1.750   0.7367   0.01146   0.00442  -0.1079   0.4719   0.4648
   2.000   0.7578   0.01149   0.00455  -0.1066   0.4674   0.4939
   2.250   0.7778   0.01152   0.00467  -0.1051   0.4620   0.5250
   2.500   0.7976   0.01160   0.00480  -0.1035   0.4574   0.5594
   2.750   0.8175   0.01168   0.00496  -0.1020   0.4531   0.5988
   3.000   0.8365   0.01162   0.00511  -0.1003   0.4497   0.6549
   3.250   0.9299   0.01136   0.00555  -0.1144   0.4431   1.0000
   3.500   0.9496   0.01154   0.00567  -0.1128   0.4392   1.0000
   3.750   0.9699   0.01176   0.00582  -0.1115   0.4354   1.0000
   4.000   0.9908   0.01189   0.00595  -0.1103   0.4318   1.0000
   4.250   1.0114   0.01205   0.00609  -0.1090   0.4278   1.0000
   4.500   1.0314   0.01225   0.00625  -0.1076   0.4238   1.0000
   4.750   1.0506   0.01249   0.00643  -0.1062   0.4198   1.0000
   5.000   1.0710   0.01269   0.00662  -0.1049   0.4159   1.0000
   5.250   1.0918   0.01287   0.00681  -0.1038   0.4121   1.0000
   5.500   1.1111   0.01310   0.00701  -0.1024   0.4074   1.0000
   5.750   1.1298   0.01338   0.00724  -0.1009   0.4033   1.0000
   6.000   1.1493   0.01363   0.00749  -0.0997   0.3993   1.0000
   6.250   1.1698   0.01385   0.00773  -0.0986   0.3951   1.0000
   6.500   1.1889   0.01412   0.00798  -0.0973   0.3905   1.0000
   6.750   1.2056   0.01448   0.00829  -0.0957   0.3856   1.0000
   7.000   1.2251   0.01477   0.00860  -0.0945   0.3813   1.0000
   7.250   1.2447   0.01506   0.00890  -0.0934   0.3766   1.0000
   7.500   1.2619   0.01543   0.00926  -0.0920   0.3716   1.0000
   7.750   1.2782   0.01588   0.00966  -0.0904   0.3668   1.0000
   8.000   1.2979   0.01619   0.01002  -0.0895   0.3621   1.0000
   8.250   1.3151   0.01662   0.01045  -0.0882   0.3567   1.0000
   8.500   1.3304   0.01714   0.01094  -0.0866   0.3516   1.0000
   8.750   1.3485   0.01757   0.01140  -0.0855   0.3465   1.0000
   9.000   1.3653   0.01806   0.01190  -0.0843   0.3408   1.0000
   9.250   1.3786   0.01873   0.01254  -0.0827   0.3351   1.0000
   9.500   1.3958   0.01925   0.01309  -0.0817   0.3293   1.0000
   9.750   1.4105   0.01990   0.01375  -0.0803   0.3231   1.0000
  10.000   1.4231   0.02069   0.01452  -0.0788   0.3169   1.0000
  10.250   1.4383   0.02137   0.01522  -0.0777   0.3103   1.0000
  10.500   1.4496   0.02228   0.01611  -0.0762   0.3041   1.0000
  10.750   1.4625   0.02313   0.01699  -0.0749   0.2974   1.0000
  11.000   1.4745   0.02407   0.01793  -0.0736   0.2913   1.0000
  11.250   1.4838   0.02520   0.01905  -0.0722   0.2851   1.0000
  11.500   1.4936   0.02635   0.02020  -0.0708   0.2768   1.0000
  11.750   1.5002   0.02773   0.02157  -0.0693   0.2699   1.0000
  12.000   1.5091   0.02900   0.02286  -0.0680   0.2628   1.0000
  12.250   1.5134   0.03065   0.02449  -0.0665   0.2563   1.0000
  12.500   1.5237   0.03190   0.02578  -0.0655   0.2508   1.0000
  12.750   1.5286   0.03359   0.02748  -0.0642   0.2445   1.0000
  13.000   1.5337   0.03530   0.02920  -0.0630   0.2399   1.0000
  13.250   1.5419   0.03681   0.03075  -0.0621   0.2345   1.0000
  13.500   1.5453   0.03876   0.03272  -0.0610   0.2293   1.0000
  13.750   1.5486   0.04075   0.03473  -0.0600   0.2249   1.0000
  14.000   1.5555   0.04246   0.03649  -0.0592   0.2199   1.0000
  14.250   1.5562   0.04478   0.03884  -0.0582   0.2146   1.0000
  14.500   1.5571   0.04712   0.04121  -0.0574   0.2095   1.0000
  14.750   1.5611   0.04922   0.04336  -0.0567   0.2038   1.0000
  15.000   1.5549   0.05235   0.04650  -0.0558   0.1971   1.0000
  15.250   1.5592   0.05448   0.04869  -0.0553   0.1919   1.0000
  15.500   1.5540   0.05762   0.05185  -0.0546   0.1842   1.0000
  15.750   1.5509   0.06060   0.05486  -0.0541   0.1752   1.0000
  16.000   1.5319   0.06535   0.05957  -0.0534   0.1567   1.0000
  16.250   1.5056   0.07103   0.06518  -0.0528   0.1403   1.0000
  16.500   1.4909   0.07551   0.06967  -0.0525   0.1335   1.0000
  16.750   1.4793   0.07969   0.07388  -0.0523   0.1300   1.0000
  17.000   1.4702   0.08361   0.07785  -0.0523   0.1273   1.0000
  17.250   1.4612   0.08757   0.08185  -0.0523   0.1248   1.0000
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