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GOE 628 AIRFOIL (goe628-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 628 AIRFOIL (goe628-il)
Reynolds number: 100,000
Max Cl/Cd: 43.66 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe628-il-100000.txt
Download as CSV file: xf-goe628-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 628 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.1520   0.10095   0.09630  -0.0548   0.9664   0.1903
  -8.500  -0.1355   0.09797   0.09331  -0.0588   0.9566   0.1970
  -8.250  -0.1452   0.09445   0.08981  -0.0668   0.9456   0.2021
  -8.000  -0.3052   0.05703   0.05195  -0.1002   0.9181   0.1279
  -7.750  -0.3194   0.05015   0.04467  -0.1032   0.9043   0.1259
  -7.500  -0.3035   0.04327   0.03714  -0.1091   0.8988   0.1256
  -7.250  -0.3029   0.04045   0.03392  -0.1075   0.8859   0.1258
  -7.000  -0.2697   0.03688   0.02975  -0.1109   0.8815   0.1264
  -6.750  -0.2602   0.03537   0.02788  -0.1089   0.8700   0.1270
  -6.500  -0.2223   0.03324   0.02558  -0.1113   0.8653   0.1288
  -6.250  -0.1765   0.03173   0.02399  -0.1145   0.8622   0.1323
  -6.000  -0.1657   0.03115   0.02328  -0.1119   0.8504   0.1344
  -5.750  -0.1250   0.02965   0.02150  -0.1140   0.8459   0.1378
  -5.500  -0.0806   0.02810   0.01973  -0.1166   0.8427   0.1417
  -5.250  -0.0698   0.02784   0.01954  -0.1138   0.8304   0.1445
  -5.000  -0.0280   0.02678   0.01838  -0.1157   0.8261   0.1519
  -4.750  -0.0090   0.02638   0.01800  -0.1141   0.8162   0.1581
  -4.500   0.0264   0.02551   0.01710  -0.1148   0.8098   0.1703
  -4.250   0.0695   0.02448   0.01624  -0.1166   0.8056   0.1921
  -4.000   0.0837   0.02450   0.01636  -0.1140   0.7933   0.2201
  -3.750   0.1252   0.02441   0.01638  -0.1151   0.7878   0.2616
  -3.500   0.1437   0.02485   0.01683  -0.1131   0.7764   0.2819
  -3.250   0.1814   0.02474   0.01664  -0.1137   0.7701   0.3032
  -3.000   0.2039   0.02495   0.01685  -0.1123   0.7603   0.3167
  -2.750   0.2359   0.02490   0.01675  -0.1122   0.7526   0.3335
  -2.500   0.2651   0.02492   0.01667  -0.1119   0.7448   0.3496
  -2.250   0.2895   0.02500   0.01676  -0.1108   0.7351   0.3627
  -2.000   0.3275   0.02465   0.01634  -0.1116   0.7294   0.3780
  -1.750   0.3428   0.02487   0.01655  -0.1093   0.7175   0.3898
  -1.500   0.3790   0.02454   0.01607  -0.1099   0.7110   0.4064
  -1.250   0.3959   0.02468   0.01632  -0.1078   0.6995   0.4170
  -1.000   0.4304   0.02424   0.01574  -0.1083   0.6923   0.4302
  -0.750   0.4494   0.02433   0.01580  -0.1066   0.6811   0.4407
  -0.500   0.4828   0.02386   0.01524  -0.1069   0.6733   0.4517
  -0.250   0.5031   0.02394   0.01523  -0.1055   0.6619   0.4625
   0.000   0.5360   0.02347   0.01472  -0.1057   0.6539   0.4736
   0.250   0.5562   0.02352   0.01473  -0.1042   0.6424   0.4841
   0.500   0.5896   0.02310   0.01423  -0.1046   0.6344   0.4967
   0.750   0.6091   0.02312   0.01429  -0.1030   0.6223   0.5074
   1.000   0.6448   0.02270   0.01370  -0.1037   0.6145   0.5220
   1.250   0.6631   0.02274   0.01384  -0.1019   0.6018   0.5344
   1.500   0.6937   0.02248   0.01353  -0.1019   0.5929   0.5503
   1.750   0.7165   0.02242   0.01351  -0.1007   0.5816   0.5664
   2.000   0.7432   0.02234   0.01345  -0.1002   0.5714   0.5865
   2.250   0.7727   0.02212   0.01324  -0.1001   0.5614   0.6129
   2.500   0.7958   0.02210   0.01338  -0.0991   0.5504   0.6470
   2.750   0.8270   0.02143   0.01313  -0.0990   0.5418   0.7538
   3.000   0.8792   0.02160   0.01338  -0.1041   0.5290   1.0000
   3.250   0.9136   0.02173   0.01317  -0.1049   0.5215   1.0000
   3.500   0.9294   0.02227   0.01371  -0.1029   0.5108   1.0000
   3.750   0.9630   0.02241   0.01355  -0.1036   0.5038   1.0000
   4.000   0.9770   0.02305   0.01424  -0.1014   0.4941   1.0000
   4.250   1.0069   0.02330   0.01431  -0.1015   0.4874   1.0000
   4.500   1.0252   0.02395   0.01497  -0.1000   0.4797   1.0000
   4.750   1.0483   0.02439   0.01534  -0.0992   0.4725   1.0000
   5.000   1.0796   0.02473   0.01547  -0.0996   0.4667   1.0000
   5.250   1.0915   0.02551   0.01638  -0.0972   0.4591   1.0000
   5.500   1.1175   0.02594   0.01671  -0.0968   0.4532   1.0000
   5.750   1.1462   0.02646   0.01712  -0.0970   0.4483   1.0000
   6.000   1.1563   0.02739   0.01820  -0.0944   0.4418   1.0000
   6.250   1.1798   0.02791   0.01867  -0.0937   0.4363   1.0000
   6.500   1.2159   0.02826   0.01882  -0.0949   0.4318   1.0000
   6.750   1.2193   0.02943   0.02022  -0.0915   0.4260   1.0000
   7.000   1.2360   0.03026   0.02111  -0.0900   0.4210   1.0000
   7.250   1.2639   0.03077   0.02155  -0.0900   0.4167   1.0000
   7.500   1.2892   0.03153   0.02227  -0.0898   0.4125   1.0000
   7.750   1.2890   0.03291   0.02386  -0.0861   0.4072   1.0000
   8.000   1.3046   0.03380   0.02481  -0.0845   0.4025   1.0000
   8.250   1.3337   0.03434   0.02528  -0.0848   0.3987   1.0000
   8.500   1.3571   0.03528   0.02621  -0.0844   0.3950   1.0000
   8.750   1.3414   0.03729   0.02849  -0.0790   0.3903   1.0000
   9.000   1.3465   0.03859   0.02990  -0.0763   0.3858   1.0000
   9.250   1.3750   0.03912   0.03039  -0.0764   0.3819   1.0000
   9.500   1.4203   0.03942   0.03057  -0.0789   0.3784   1.0000
   9.750   1.3591   0.04304   0.03456  -0.0683   0.3745   1.0000
  10.000   1.0706   0.06861   0.06070  -0.0534   0.3621   1.0000
  10.250   1.2307   0.05448   0.04643  -0.0542   0.3647   1.0000
  10.500   1.3973   0.04640   0.03804  -0.0637   0.3625   1.0000
  10.750   0.8021   0.11982   0.11226  -0.0660   0.3416   1.0000
  11.000   0.7989   0.12501   0.11749  -0.0673   0.3420   1.0000
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