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GOE 529 AIRFOIL (goe529-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 529 AIRFOIL (goe529-il)
Reynolds number: 1,000,000
Max Cl/Cd: 138.59 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe529-il-1000000.txt
Download as CSV file: xf-goe529-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 529 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.2741   0.11548   0.11386  -0.0352   1.0000   0.0138
 -10.500  -0.2730   0.11211   0.11050  -0.0364   1.0000   0.0139
 -10.250  -0.2708   0.10900   0.10741  -0.0370   1.0000   0.0139
 -10.000  -0.2692   0.10590   0.10433  -0.0375   1.0000   0.0139
  -9.750  -0.2677   0.10213   0.10059  -0.0376   0.9999   0.0141
  -9.500  -0.2480   0.09926   0.09771  -0.0407   0.9983   0.0144
  -9.250  -0.2332   0.09632   0.09477  -0.0434   0.9895   0.0148
  -9.000  -0.2170   0.09302   0.09147  -0.0470   0.9803   0.0154
  -8.750  -0.1954   0.08878   0.08721  -0.0528   0.9688   0.0164
  -8.500  -0.1683   0.08135   0.07974  -0.0657   0.9564   0.0175
  -8.250  -0.1291   0.07429   0.07261  -0.0788   0.9368   0.0175
  -8.000  -0.1071   0.06915   0.06728  -0.0863   0.8934   0.0181
  -7.750  -0.0970   0.06829   0.06622  -0.0856   0.8494   0.0185
  -7.500  -0.1032   0.06546   0.06328  -0.0859   0.8180   0.0184
  -7.250  -0.0950   0.06387   0.06158  -0.0863   0.7921   0.0189
  -7.000  -0.0866   0.06172   0.05933  -0.0877   0.7682   0.0203
  -6.250  -0.1054   0.01888   0.01480  -0.1109   0.7189   0.0217
  -6.000  -0.0881   0.01582   0.01120  -0.1102   0.7025   0.0228
  -5.750  -0.0626   0.01560   0.01089  -0.1099   0.6884   0.0233
  -5.500  -0.0361   0.01564   0.01089  -0.1097   0.6773   0.0240
  -5.250  -0.0104   0.01528   0.01040  -0.1093   0.6684   0.0248
  -5.000   0.0150   0.01449   0.00942  -0.1090   0.6607   0.0257
  -4.750   0.0405   0.01379   0.00851  -0.1086   0.6540   0.0264
  -4.500   0.0676   0.01350   0.00811  -0.1083   0.6486   0.0270
  -4.250   0.0933   0.01265   0.00703  -0.1080   0.6433   0.0278
  -4.000   0.1181   0.01144   0.00563  -0.1075   0.6385   0.0287
  -3.750   0.1450   0.01097   0.00510  -0.1073   0.6340   0.0294
  -3.500   0.1720   0.01065   0.00472  -0.1071   0.6295   0.0301
  -3.250   0.1989   0.01042   0.00442  -0.1068   0.6253   0.0310
  -3.000   0.2262   0.01009   0.00402  -0.1066   0.6215   0.0316
  -2.750   0.2534   0.00976   0.00364  -0.1064   0.6175   0.0322
  -2.500   0.2805   0.00947   0.00329  -0.1061   0.6133   0.0327
  -2.250   0.3075   0.00926   0.00301  -0.1058   0.6092   0.0333
  -2.000   0.3350   0.00906   0.00278  -0.1057   0.6058   0.0338
  -1.750   0.3626   0.00890   0.00260  -0.1055   0.6019   0.0344
  -1.500   0.3891   0.00853   0.00215  -0.1051   0.5977   0.0359
  -1.250   0.4161   0.00839   0.00197  -0.1049   0.5934   0.0373
  -1.000   0.4438   0.00825   0.00184  -0.1047   0.5898   0.0386
  -0.750   0.4714   0.00814   0.00172  -0.1046   0.5854   0.0401
  -0.500   0.4988   0.00808   0.00162  -0.1044   0.5807   0.0419
  -0.250   0.5261   0.00800   0.00153  -0.1042   0.5758   0.0459
   0.000   0.5535   0.00787   0.00147  -0.1040   0.5688   0.0645
   0.250   0.5804   0.00781   0.00145  -0.1037   0.5613   0.0906
   0.500   0.6079   0.00775   0.00143  -0.1036   0.5528   0.1074
   0.750   0.6349   0.00772   0.00143  -0.1034   0.5459   0.1297
   1.000   0.6623   0.00767   0.00144  -0.1033   0.5383   0.1582
   1.250   0.6891   0.00763   0.00146  -0.1031   0.5299   0.1938
   1.500   0.7154   0.00746   0.00151  -0.1028   0.5205   0.2919
   1.750   0.7632   0.00607   0.00170  -0.1077   0.5091   1.0000
   2.000   0.7886   0.00617   0.00173  -0.1072   0.4977   1.0000
   2.250   0.8139   0.00629   0.00177  -0.1066   0.4859   1.0000
   2.500   0.8390   0.00643   0.00183  -0.1060   0.4739   1.0000
   2.750   0.8645   0.00656   0.00189  -0.1055   0.4627   1.0000
   3.000   0.8899   0.00669   0.00197  -0.1050   0.4525   1.0000
   3.250   0.9151   0.00685   0.00207  -0.1045   0.4430   1.0000
   3.500   0.9406   0.00699   0.00217  -0.1040   0.4339   1.0000
   3.750   0.9661   0.00713   0.00227  -0.1036   0.4259   1.0000
   4.000   0.9915   0.00728   0.00238  -0.1031   0.4180   1.0000
   4.250   1.0171   0.00742   0.00250  -0.1027   0.4110   1.0000
   4.500   1.0426   0.00757   0.00263  -0.1023   0.4037   1.0000
   4.750   1.0681   0.00773   0.00276  -0.1019   0.3961   1.0000
   5.000   1.0932   0.00790   0.00290  -0.1014   0.3874   1.0000
   5.250   1.1184   0.00807   0.00304  -0.1009   0.3765   1.0000
   5.500   1.1426   0.00830   0.00320  -0.1004   0.3609   1.0000
   5.750   1.1672   0.00851   0.00336  -0.0998   0.3485   1.0000
   6.000   1.1915   0.00873   0.00355  -0.0993   0.3360   1.0000
   6.250   1.2154   0.00898   0.00374  -0.0987   0.3217   1.0000
   6.500   1.2391   0.00924   0.00395  -0.0980   0.3077   1.0000
   6.750   1.2614   0.00958   0.00421  -0.0972   0.2875   1.0000
   7.000   1.2825   0.01001   0.00452  -0.0961   0.2647   1.0000
   7.250   1.3029   0.01047   0.00486  -0.0950   0.2419   1.0000
   7.500   1.3228   0.01095   0.00523  -0.0938   0.2194   1.0000
   7.750   1.3410   0.01152   0.00566  -0.0923   0.1928   1.0000
   8.000   1.3470   0.01284   0.00656  -0.0889   0.1261   1.0000
   8.250   1.3615   0.01356   0.00716  -0.0868   0.1065   1.0000
   8.500   1.3771   0.01417   0.00769  -0.0850   0.0863   1.0000
   8.750   1.3743   0.01561   0.00880  -0.0800   0.0353   1.0000
   9.000   1.3779   0.01654   0.00962  -0.0761   0.0179   1.0000
   9.250   1.3889   0.01717   0.01029  -0.0734   0.0156   1.0000
   9.500   1.4005   0.01780   0.01097  -0.0710   0.0142   1.0000
   9.750   1.4129   0.01842   0.01164  -0.0688   0.0136   1.0000
  10.000   1.4240   0.01912   0.01240  -0.0666   0.0128   1.0000
  10.250   1.4330   0.01998   0.01331  -0.0642   0.0121   1.0000
  10.500   1.4387   0.02108   0.01448  -0.0616   0.0114   1.0000
  10.750   1.4426   0.02237   0.01587  -0.0590   0.0109   1.0000
  11.000   1.4523   0.02337   0.01692  -0.0573   0.0107   1.0000
  11.250   1.4612   0.02448   0.01809  -0.0556   0.0103   1.0000
  11.500   1.4680   0.02581   0.01949  -0.0539   0.0100   1.0000
  11.750   1.4732   0.02733   0.02109  -0.0523   0.0097   1.0000
  12.000   1.4791   0.02888   0.02270  -0.0509   0.0094   1.0000
  12.250   1.4822   0.03076   0.02466  -0.0495   0.0091   1.0000
  12.500   1.4850   0.03275   0.02673  -0.0483   0.0089   1.0000
  12.750   1.4826   0.03536   0.02943  -0.0472   0.0086   1.0000
  13.000   1.4803   0.03807   0.03222  -0.0463   0.0084   1.0000
  13.250   1.4680   0.04197   0.03626  -0.0454   0.0082   1.0000
  13.500   1.4642   0.04507   0.03945  -0.0449   0.0080   1.0000
  13.750   1.4657   0.04767   0.04213  -0.0446   0.0079   1.0000
  14.000   1.4689   0.05012   0.04465  -0.0444   0.0078   1.0000
  14.250   1.4668   0.05325   0.04787  -0.0442   0.0077   1.0000
  14.500   1.4648   0.05643   0.05114  -0.0442   0.0075   1.0000
  14.750   1.4611   0.05992   0.05472  -0.0443   0.0074   1.0000
  15.000   1.4586   0.06336   0.05825  -0.0446   0.0073   1.0000
  15.250   1.4562   0.06685   0.06182  -0.0450   0.0072   1.0000
  15.500   1.4521   0.07067   0.06572  -0.0455   0.0070   1.0000
  15.750   1.4508   0.07421   0.06935  -0.0461   0.0068   1.0000
  16.000   1.4458   0.07833   0.07355  -0.0469   0.0067   1.0000
  16.250   1.4427   0.08224   0.07755  -0.0478   0.0067   1.0000
  16.500   1.4398   0.08623   0.08161  -0.0487   0.0065   1.0000
  16.750   1.4352   0.09051   0.08597  -0.0498   0.0065   1.0000
  17.000   1.4319   0.09467   0.09019  -0.0511   0.0063   1.0000
  17.250   1.4283   0.09886   0.09446  -0.0523   0.0063   1.0000
  17.500   1.4238   0.10325   0.09893  -0.0537   0.0062   1.0000
  17.750   1.4195   0.10760   0.10335  -0.0550   0.0061   1.0000
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