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GOE 274 (DAIMLER V) AIRFOIL (goe274-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 274 (DAIMLER V) AIRFOIL (goe274-il)
Reynolds number: 200,000
Max Cl/Cd: 73.2 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe274-il-200000.txt
Download as CSV file: xf-goe274-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 274 (DAIMLER V) 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3392   0.10409   0.10068  -0.0244   1.0000   0.0305
  -8.000  -0.3546   0.10327   0.09994  -0.0223   1.0000   0.0305
  -7.750  -0.3655   0.10189   0.09863  -0.0224   1.0000   0.0306
  -7.500  -0.3695   0.09979   0.09657  -0.0246   1.0000   0.0307
  -7.000  -0.3694   0.09301   0.08987  -0.0236   1.0000   0.0310
  -6.750  -0.3687   0.08991   0.08681  -0.0200   1.0000   0.0313
  -6.500  -0.3674   0.08723   0.08415  -0.0184   1.0000   0.0317
  -6.250  -0.3653   0.08463   0.08156  -0.0180   1.0000   0.0321
  -6.000  -0.3614   0.08200   0.07896  -0.0183   1.0000   0.0328
  -5.750  -0.3525   0.07905   0.07601  -0.0201   0.9997   0.0338
  -5.500  -0.3115   0.07389   0.07076  -0.0303   0.9953   0.0357
  -5.250  -0.2306   0.06715   0.06355  -0.0533   0.9890   0.0377
  -5.000  -0.2123   0.06198   0.05850  -0.0544   0.9856   0.0383
  -4.750  -0.1831   0.05831   0.05481  -0.0578   0.9819   0.0394
  -4.500  -0.1491   0.05480   0.05121  -0.0626   0.9767   0.0416
  -4.250  -0.0749   0.05156   0.04726  -0.0752   0.9728   0.0460
  -4.000  -0.0440   0.04571   0.04151  -0.0796   0.9707   0.0470
  -3.750  -0.0174   0.04283   0.03863  -0.0816   0.9642   0.0484
  -3.500   0.0233   0.03997   0.03564  -0.0861   0.9604   0.0513
  -3.250   0.0781   0.03680   0.03195  -0.0924   0.9579   0.0575
  -3.000   0.1093   0.03419   0.02936  -0.0948   0.9521   0.0597
  -2.750   0.1583   0.03437   0.02897  -0.0980   0.9469   0.0682
  -2.500   0.1969   0.02950   0.02421  -0.1027   0.9444   0.0718
  -2.250   0.2461   0.02779   0.02214  -0.1073   0.9423   0.0839
  -2.000   0.2763   0.02594   0.02036  -0.1086   0.9339   0.0907
  -1.750   0.3227   0.02432   0.01850  -0.1128   0.9306   0.1146
  -1.500   0.3666   0.02241   0.01658  -0.1167   0.9277   0.1351
  -0.750   0.4675   0.01791   0.01208  -0.1211   0.9001   0.2538
  -0.500   0.5005   0.01687   0.01095  -0.1214   0.8857   0.2811
  -0.250   0.5449   0.01634   0.00950  -0.1196   0.8701   0.1251
   0.000   0.5775   0.01529   0.00818  -0.1187   0.8492   0.0946
   0.250   0.6087   0.01459   0.00725  -0.1180   0.8234   0.0812
   0.500   0.6373   0.01366   0.00621  -0.1173   0.7889   0.0757
   0.750   0.6650   0.01328   0.00557  -0.1164   0.7441   0.0712
   1.000   0.6907   0.01323   0.00522  -0.1153   0.6895   0.0694
   1.250   0.7152   0.01328   0.00497  -0.1142   0.6346   0.0688
   1.500   0.7399   0.01327   0.00471  -0.1134   0.5926   0.0700
   1.750   0.7655   0.01335   0.00460  -0.1130   0.5632   0.0738
   2.000   0.7918   0.01352   0.00459  -0.1126   0.5402   0.0752
   2.250   0.8181   0.01373   0.00462  -0.1122   0.5215   0.0775
   2.500   0.8446   0.01394   0.00469  -0.1119   0.5052   0.0816
   2.750   0.8715   0.01408   0.00486  -0.1117   0.4906   0.1103
   3.000   0.8879   0.01261   0.00504  -0.1092   0.4789   1.0000
   3.250   0.9144   0.01293   0.00520  -0.1089   0.4663   1.0000
   3.500   0.9407   0.01326   0.00537  -0.1085   0.4543   1.0000
   3.750   0.9670   0.01353   0.00558  -0.1083   0.4416   1.0000
   4.000   0.9930   0.01380   0.00579  -0.1080   0.4287   1.0000
   4.250   1.0189   0.01409   0.00601  -0.1076   0.4157   1.0000
   4.500   1.0445   0.01438   0.00626  -0.1072   0.4029   1.0000
   4.750   1.0698   0.01469   0.00650  -0.1068   0.3900   1.0000
   5.000   1.0949   0.01502   0.00676  -0.1064   0.3773   1.0000
   5.250   1.1200   0.01531   0.00705  -0.1059   0.3638   1.0000
   5.500   1.1448   0.01564   0.00737  -0.1054   0.3496   1.0000
   5.750   1.1690   0.01599   0.00769  -0.1049   0.3347   1.0000
   6.000   1.1929   0.01637   0.00804  -0.1042   0.3195   1.0000
   6.250   1.2167   0.01678   0.00842  -0.1036   0.3054   1.0000
   6.500   1.2404   0.01721   0.00885  -0.1030   0.2922   1.0000
   6.750   1.2636   0.01763   0.00925  -0.1023   0.2790   1.0000
   7.000   1.2865   0.01804   0.00965  -0.1016   0.2664   1.0000
   7.250   1.3090   0.01849   0.01008  -0.1008   0.2552   1.0000
   7.500   1.3317   0.01892   0.01053  -0.1000   0.2448   1.0000
   7.750   1.3544   0.01933   0.01100  -0.0993   0.2348   1.0000
   8.000   1.3761   0.01980   0.01147  -0.0984   0.2245   1.0000
   8.250   1.3966   0.02030   0.01197  -0.0974   0.2137   1.0000
   8.500   1.4178   0.02073   0.01247  -0.0965   0.2016   1.0000
   8.750   1.4376   0.02124   0.01299  -0.0953   0.1875   1.0000
   9.000   1.4564   0.02182   0.01358  -0.0941   0.1724   1.0000
   9.250   1.4756   0.02239   0.01417  -0.0928   0.1541   1.0000
   9.500   1.4937   0.02309   0.01480  -0.0914   0.1180   1.0000
   9.750   1.4956   0.02513   0.01634  -0.0878   0.0615   1.0000
  10.000   1.4957   0.02712   0.01810  -0.0838   0.0365   1.0000
  10.250   1.5016   0.02846   0.01952  -0.0805   0.0329   1.0000
  10.500   1.5089   0.02973   0.02097  -0.0776   0.0312   1.0000
  10.750   1.5140   0.03118   0.02260  -0.0745   0.0300   1.0000
  11.000   1.5161   0.03287   0.02448  -0.0714   0.0289   1.0000
  11.250   1.5144   0.03489   0.02667  -0.0681   0.0280   1.0000
  11.500   1.5086   0.03733   0.02927  -0.0650   0.0272   1.0000
  11.750   1.4990   0.04027   0.03237  -0.0620   0.0265   1.0000
  12.000   1.4969   0.04277   0.03502  -0.0601   0.0260   1.0000
  12.250   1.4928   0.04565   0.03806  -0.0584   0.0256   1.0000
  12.500   1.4872   0.04889   0.04145  -0.0572   0.0252   1.0000
  12.750   1.4809   0.05243   0.04513  -0.0564   0.0250   1.0000
  13.000   1.4743   0.05620   0.04904  -0.0560   0.0247   1.0000
  13.250   1.4679   0.06011   0.05309  -0.0558   0.0245   1.0000
  13.500   1.4623   0.06404   0.05714  -0.0558   0.0242   1.0000
  13.750   1.4574   0.06791   0.06113  -0.0559   0.0240   1.0000
  14.000   1.4540   0.07162   0.06494  -0.0558   0.0238   1.0000
  14.250   1.4519   0.07514   0.06856  -0.0557   0.0236   1.0000
  14.500   1.4512   0.07844   0.07195  -0.0555   0.0234   1.0000
  14.750   1.4517   0.08155   0.07515  -0.0551   0.0232   1.0000
  15.000   1.4530   0.08458   0.07828  -0.0547   0.0229   1.0000
  15.250   1.4541   0.08769   0.08148  -0.0544   0.0226   1.0000
  15.500   1.4553   0.09078   0.08466  -0.0541   0.0222   1.0000
  15.750   1.4576   0.09367   0.08762  -0.0536   0.0217   1.0000
  16.000   1.4614   0.09641   0.09044  -0.0526   0.0214   1.0000
  16.250   1.4602   0.10020   0.09439  -0.0530   0.0213   1.0000
  16.500   1.4559   0.10464   0.09902  -0.0543   0.0214   1.0000
  16.750   1.4492   0.10954   0.10412  -0.0561   0.0214   1.0000
  17.000   1.4404   0.11496   0.10975  -0.0587   0.0215   1.0000
  17.250   1.4298   0.12091   0.11593  -0.0618   0.0217   1.0000
  17.500   1.4175   0.12743   0.12268  -0.0656   0.0219   1.0000
  17.750   1.4037   0.13453   0.13003  -0.0700   0.0221   1.0000
  18.000   1.3852   0.14306   0.13884  -0.0758   0.0225   1.0000
  18.250   1.3648   0.15247   0.14850  -0.0825   0.0228   1.0000
  18.500   1.3432   0.16275   0.15903  -0.0900   0.0232   1.0000
  18.750   1.3197   0.17427   0.17078  -0.0985   0.0237   1.0000
  19.000   1.2924   0.18790   0.18462  -0.1085   0.0243   1.0000
  19.250   1.2571   0.20580   0.20268  -0.1212   0.0253   1.0000
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