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GOE 574 AIRFOIL (goe574-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 574 AIRFOIL (goe574-il)
Reynolds number: 200,000
Max Cl/Cd: 73.11 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe574-il-200000-n5.txt
Download as CSV file: xf-goe574-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 574 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3147   0.10955   0.10627  -0.0294   1.0000   0.0206
  -8.750  -0.3141   0.10675   0.10351  -0.0296   1.0000   0.0213
  -8.500  -0.3159   0.10429   0.10111  -0.0304   1.0000   0.0227
  -8.250  -0.3113   0.10119   0.09804  -0.0324   0.9990   0.0229
  -8.000  -0.2975   0.09688   0.09374  -0.0387   0.9951   0.0232
  -7.750  -0.2914   0.08957   0.08644  -0.0442   0.9900   0.0151
  -7.500  -0.2789   0.08548   0.08235  -0.0473   0.9852   0.0147
  -7.250  -0.2674   0.08147   0.07835  -0.0513   0.9780   0.0144
  -7.000  -0.2570   0.07708   0.07397  -0.0551   0.9672   0.0140
  -6.750  -0.2526   0.07262   0.06952  -0.0579   0.9479   0.0142
  -6.500  -0.2474   0.06850   0.06539  -0.0600   0.9246   0.0143
  -6.250  -0.2297   0.06309   0.05989  -0.0652   0.9084   0.0144
  -6.000  -0.2030   0.05615   0.05277  -0.0723   0.8944   0.0152
  -5.750  -0.1760   0.04974   0.04614  -0.0778   0.8820   0.0153
  -5.500  -0.1460   0.04276   0.03884  -0.0829   0.8699   0.0154
  -5.250  -0.1161   0.03562   0.03126  -0.0872   0.8579   0.0158
  -5.000  -0.0740   0.03349   0.02889  -0.0925   0.8446   0.0171
  -4.750  -0.0307   0.03008   0.02505  -0.0973   0.8310   0.0196
  -4.500   0.0055   0.02460   0.01876  -0.0999   0.8174   0.0213
  -4.250   0.0402   0.02157   0.01485  -0.1013   0.8024   0.0243
  -4.000   0.0707   0.01993   0.01291  -0.1026   0.7863   0.0266
  -3.750   0.0997   0.01872   0.01134  -0.1029   0.7699   0.0288
  -3.500   0.1273   0.01798   0.01022  -0.1028   0.7536   0.0324
  -3.250   0.1538   0.01729   0.00915  -0.1023   0.7370   0.0338
  -3.000   0.1782   0.01601   0.00763  -0.1017   0.7210   0.0362
  -2.750   0.2028   0.01545   0.00690  -0.1011   0.7049   0.0384
  -2.500   0.2272   0.01490   0.00617  -0.1002   0.6893   0.0395
  -2.250   0.2510   0.01447   0.00558  -0.0993   0.6740   0.0407
  -2.000   0.2743   0.01411   0.00507  -0.0983   0.6588   0.0415
  -1.750   0.2973   0.01388   0.00470  -0.0972   0.6439   0.0433
  -1.250   0.3423   0.01347   0.00405  -0.0949   0.6151   0.0448
  -1.000   0.3646   0.01332   0.00376  -0.0938   0.6012   0.0450
  -0.750   0.3872   0.01322   0.00353  -0.0926   0.5877   0.0452
  -0.500   0.4100   0.01314   0.00333  -0.0916   0.5753   0.0458
  -0.250   0.4331   0.01309   0.00316  -0.0906   0.5641   0.0468
   0.000   0.4563   0.01307   0.00304  -0.0896   0.5538   0.0493
   0.250   0.4796   0.01305   0.00297  -0.0886   0.5442   0.0543
   0.500   0.5012   0.01281   0.00297  -0.0875   0.5356   0.1433
   0.750   0.5150   0.01193   0.00306  -0.0851   0.5284   0.4910
   1.250   0.7107   0.01186   0.00371  -0.1167   0.5070   1.0000
   1.500   0.7332   0.01200   0.00377  -0.1157   0.5011   1.0000
   1.750   0.7560   0.01215   0.00385  -0.1147   0.4962   1.0000
   2.000   0.7790   0.01229   0.00395  -0.1138   0.4912   1.0000
   2.250   0.8018   0.01244   0.00406  -0.1129   0.4869   1.0000
   2.500   0.8248   0.01262   0.00419  -0.1120   0.4832   1.0000
   2.750   0.8481   0.01276   0.00434  -0.1112   0.4792   1.0000
   3.000   0.8712   0.01293   0.00450  -0.1103   0.4755   1.0000
   3.250   0.8942   0.01311   0.00468  -0.1095   0.4719   1.0000
   3.500   0.9175   0.01331   0.00486  -0.1087   0.4688   1.0000
   3.750   0.9405   0.01348   0.00508  -0.1078   0.4652   1.0000
   4.000   0.9637   0.01366   0.00533  -0.1070   0.4621   1.0000
   4.250   0.9867   0.01385   0.00556  -0.1061   0.4588   1.0000
   4.750   1.0277   0.01421   0.00600  -0.1033   0.4457   1.0000
   5.000   1.0435   0.01436   0.00617  -0.1009   0.4327   1.0000
   5.250   1.0596   0.01453   0.00635  -0.0985   0.4202   1.0000
   5.500   1.0732   0.01468   0.00651  -0.0956   0.4029   1.0000
   5.750   1.0862   0.01487   0.00668  -0.0926   0.3834   1.0000
   6.000   1.0985   0.01509   0.00689  -0.0895   0.3552   1.0000
   6.250   1.0992   0.01572   0.00715  -0.0842   0.2764   1.0000
   6.500   1.0804   0.01756   0.00826  -0.0757   0.1657   1.0000
   6.750   1.0565   0.01963   0.00966  -0.0666   0.0360   1.0000
   7.000   1.0621   0.02042   0.01043  -0.0626   0.0233   1.0000
   7.250   1.0711   0.02109   0.01120  -0.0593   0.0200   1.0000
   7.500   1.0778   0.02191   0.01216  -0.0557   0.0170   1.0000
   7.750   1.0870   0.02262   0.01302  -0.0527   0.0160   1.0000
   8.000   1.0943   0.02346   0.01403  -0.0494   0.0152   1.0000
   8.250   1.0994   0.02444   0.01517  -0.0459   0.0145   1.0000
   8.500   1.1025   0.02556   0.01645  -0.0425   0.0141   1.0000
   8.750   1.1039   0.02683   0.01789  -0.0390   0.0132   1.0000
   9.000   1.1029   0.02835   0.01953  -0.0356   0.0125   1.0000
   9.250   1.1011   0.03005   0.02133  -0.0327   0.0114   1.0000
   9.500   1.0975   0.03205   0.02344  -0.0299   0.0111   1.0000
   9.750   1.0905   0.03455   0.02604  -0.0274   0.0107   1.0000
  10.000   1.0848   0.03714   0.02874  -0.0252   0.0105   1.0000
  10.250   1.0814   0.03967   0.03135  -0.0234   0.0103   1.0000
  10.500   1.0786   0.04220   0.03395  -0.0215   0.0101   1.0000
  10.750   1.0795   0.04446   0.03625  -0.0194   0.0099   1.0000
  11.000   1.0870   0.04621   0.03805  -0.0176   0.0096   1.0000
  11.250   1.0970   0.04776   0.03969  -0.0162   0.0094   1.0000
  11.500   1.1056   0.04941   0.04147  -0.0152   0.0088   1.0000
  11.750   1.1160   0.05101   0.04317  -0.0139   0.0084   1.0000
  12.000   1.1259   0.05270   0.04502  -0.0127   0.0078   1.0000
  12.250   1.1389   0.05434   0.04678  -0.0113   0.0077   1.0000
  12.500   1.1501   0.05623   0.04881  -0.0100   0.0075   1.0000
  12.750   1.1605   0.05835   0.05110  -0.0087   0.0073   1.0000
  13.000   1.1684   0.06079   0.05373  -0.0076   0.0072   1.0000
  13.250   1.1734   0.06347   0.05661  -0.0066   0.0072   1.0000
  13.500   1.1747   0.06645   0.05979  -0.0057   0.0071   1.0000
  13.750   1.1731   0.06981   0.06337  -0.0050   0.0071   1.0000
  14.000   1.1685   0.07349   0.06729  -0.0046   0.0072   1.0000
  14.250   1.1612   0.07745   0.07147  -0.0045   0.0072   1.0000
  14.500   1.1517   0.08175   0.07599  -0.0046   0.0072   1.0000
  14.750   1.1408   0.08632   0.08077  -0.0052   0.0073   1.0000
  15.000   1.1277   0.09135   0.08603  -0.0061   0.0073   1.0000
  15.250   1.1144   0.09648   0.09135  -0.0075   0.0074   1.0000
  15.500   1.0998   0.10205   0.09713  -0.0093   0.0075   1.0000
  15.750   1.0859   0.10768   0.10293  -0.0114   0.0076   1.0000
  16.000   1.0689   0.11420   0.10964  -0.0142   0.0077   1.0000
  16.250   1.0534   0.12068   0.11629  -0.0173   0.0077   1.0000
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