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GOE 274 (DAIMLER V) AIRFOIL (goe274-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 274 (DAIMLER V) AIRFOIL (goe274-il)
Reynolds number: 200,000
Max Cl/Cd: 73.18 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe274-il-200000-n5.txt
Download as CSV file: xf-goe274-il-200000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3381   0.10593   0.10253  -0.0259   1.0000   0.0244
  -8.250  -0.3486   0.10437   0.10103  -0.0241   1.0000   0.0244
  -8.000  -0.3607   0.10290   0.09962  -0.0220   1.0000   0.0244
  -7.750  -0.3477   0.09868   0.09541  -0.0277   0.9969   0.0245
  -7.500  -0.3265   0.09369   0.09040  -0.0356   0.9933   0.0245
  -7.250  -0.3164   0.08937   0.08609  -0.0337   0.9914   0.0248
  -7.000  -0.2996   0.08584   0.08256  -0.0344   0.9887   0.0256
  -6.750  -0.2747   0.08184   0.07854  -0.0400   0.9853   0.0268
  -6.500  -0.2502   0.07760   0.07427  -0.0465   0.9793   0.0283
  -6.250  -0.2034   0.07195   0.06848  -0.0621   0.9747   0.0304
  -6.000  -0.1646   0.06687   0.06322  -0.0728   0.9678   0.0307
  -5.750  -0.1326   0.06118   0.05741  -0.0796   0.9644   0.0311
  -5.500  -0.1116   0.05727   0.05351  -0.0815   0.9619   0.0317
  -5.250  -0.0902   0.05420   0.05041  -0.0833   0.9554   0.0323
  -5.000  -0.0572   0.05070   0.04682  -0.0880   0.9519   0.0334
  -4.750  -0.0183   0.04700   0.04298  -0.0937   0.9494   0.0351
  -4.500   0.0323   0.04420   0.03958  -0.1001   0.9423   0.0392
  -4.250   0.0692   0.04118   0.03626  -0.1035   0.9375   0.0394
  -4.000   0.0984   0.03624   0.03138  -0.1070   0.9340   0.0403
  -3.750   0.1225   0.03398   0.02907  -0.1079   0.9250   0.0412
  -3.500   0.1557   0.03177   0.02672  -0.1102   0.9200   0.0429
  -3.250   0.1942   0.03140   0.02575  -0.1113   0.9121   0.0491
  -3.000   0.2257   0.02798   0.02221  -0.1134   0.9056   0.0500
  -2.750   0.2538   0.02585   0.02006  -0.1145   0.8967   0.0512
  -2.500   0.2866   0.02422   0.01829  -0.1160   0.8889   0.0532
  -2.250   0.3172   0.02291   0.01679  -0.1166   0.8777   0.0558
  -2.000   0.3495   0.02154   0.01513  -0.1175   0.8662   0.0622
  -1.500   0.4150   0.01861   0.01165  -0.1181   0.8379   0.0454
  -1.250   0.4481   0.01778   0.01031  -0.1179   0.8199   0.0398
  -1.000   0.4779   0.01695   0.00931  -0.1180   0.7960   0.0388
  -0.750   0.5069   0.01611   0.00823  -0.1179   0.7632   0.0385
  -0.500   0.5345   0.01557   0.00739  -0.1174   0.7220   0.0383
  -0.250   0.5606   0.01524   0.00672  -0.1167   0.6706   0.0384
   0.000   0.5854   0.01510   0.00622  -0.1158   0.6156   0.0386
   0.250   0.6102   0.01505   0.00585  -0.1150   0.5719   0.0399
   0.500   0.6354   0.01477   0.00541  -0.1145   0.5414   0.0412
   0.750   0.6612   0.01468   0.00516  -0.1141   0.5181   0.0413
   1.000   0.6876   0.01458   0.00497  -0.1138   0.4993   0.0414
   1.250   0.7141   0.01451   0.00483  -0.1136   0.4825   0.0417
   1.500   0.7408   0.01447   0.00472  -0.1134   0.4663   0.0421
   1.750   0.7677   0.01445   0.00466  -0.1133   0.4522   0.0428
   2.000   0.7946   0.01448   0.00463  -0.1132   0.4398   0.0438
   2.250   0.8215   0.01455   0.00462  -0.1131   0.4280   0.0452
   2.500   0.8485   0.01463   0.00465  -0.1130   0.4166   0.0482
   2.750   0.8753   0.01472   0.00468  -0.1128   0.4062   0.0515
   3.250   0.9286   0.01499   0.00486  -0.1124   0.3855   0.0581
   3.500   0.9536   0.01395   0.00521  -0.1124   0.3748   0.7305
   3.750   0.9713   0.01370   0.00523  -0.1098   0.3642   1.0000
   4.000   0.9973   0.01395   0.00540  -0.1095   0.3518   1.0000
   4.250   1.0232   0.01421   0.00560  -0.1092   0.3395   1.0000
   4.500   1.0489   0.01449   0.00583  -0.1089   0.3277   1.0000
   4.750   1.0742   0.01479   0.00607  -0.1085   0.3166   1.0000
   5.000   1.0996   0.01509   0.00633  -0.1082   0.3052   1.0000
   5.250   1.1249   0.01539   0.00662  -0.1078   0.2939   1.0000
   5.500   1.1497   0.01571   0.00693  -0.1074   0.2826   1.0000
   5.750   1.1742   0.01607   0.00725  -0.1069   0.2702   1.0000
   6.000   1.1982   0.01646   0.00760  -0.1064   0.2573   1.0000
   6.250   1.2220   0.01686   0.00799  -0.1058   0.2453   1.0000
   6.500   1.2459   0.01725   0.00838  -0.1052   0.2347   1.0000
   6.750   1.2689   0.01769   0.00880  -0.1046   0.2227   1.0000
   7.000   1.2913   0.01819   0.00926  -0.1038   0.2092   1.0000
   7.250   1.3133   0.01870   0.00974  -0.1030   0.1971   1.0000
   7.500   1.3348   0.01925   0.01026  -0.1021   0.1875   1.0000
   7.750   1.3571   0.01971   0.01077  -0.1014   0.1791   1.0000
   8.000   1.3780   0.02026   0.01135  -0.1004   0.1697   1.0000
   8.250   1.3979   0.02089   0.01195  -0.0993   0.1566   1.0000
   8.500   1.4183   0.02146   0.01254  -0.0983   0.1437   1.0000
   8.750   1.4377   0.02210   0.01314  -0.0971   0.1150   1.0000
   9.000   1.4436   0.02394   0.01454  -0.0942   0.0685   1.0000
   9.250   1.4461   0.02595   0.01629  -0.0906   0.0252   1.0000
   9.500   1.4569   0.02708   0.01751  -0.0881   0.0217   1.0000
   9.750   1.4664   0.02812   0.01869  -0.0853   0.0200   1.0000
  10.000   1.4764   0.02917   0.01989  -0.0827   0.0188   1.0000
  10.250   1.4848   0.03036   0.02124  -0.0801   0.0176   1.0000
  10.500   1.4909   0.03175   0.02281  -0.0774   0.0165   1.0000
  10.750   1.4937   0.03341   0.02464  -0.0745   0.0157   1.0000
  11.000   1.4928   0.03543   0.02686  -0.0714   0.0151   1.0000
  11.250   1.4954   0.03723   0.02882  -0.0690   0.0147   1.0000
  11.500   1.4963   0.03926   0.03102  -0.0667   0.0144   1.0000
  11.750   1.4951   0.04159   0.03353  -0.0647   0.0141   1.0000
  12.000   1.4920   0.04427   0.03639  -0.0629   0.0138   1.0000
  12.250   1.4871   0.04732   0.03960  -0.0616   0.0135   1.0000
  12.500   1.4811   0.05074   0.04320  -0.0608   0.0132   1.0000
  12.750   1.4736   0.05461   0.04724  -0.0604   0.0129   1.0000
  13.000   1.4649   0.05892   0.05172  -0.0607   0.0127   1.0000
  13.250   1.4554   0.06367   0.05663  -0.0615   0.0124   1.0000
  13.500   1.4450   0.06880   0.06191  -0.0627   0.0122   1.0000
  13.750   1.4341   0.07423   0.06748  -0.0642   0.0120   1.0000
  14.000   1.4227   0.07983   0.07322  -0.0659   0.0119   1.0000
  14.250   1.4113   0.08544   0.07895  -0.0677   0.0117   1.0000
  14.500   1.4000   0.09101   0.08463  -0.0693   0.0115   1.0000
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