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GOE 280 (DAIMLER XI) AIRFOIL (goe280-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 280 (DAIMLER XI) AIRFOIL (goe280-il)
Reynolds number: 1,000,000
Max Cl/Cd: 87.25 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe280-il-1000000-n5.txt
Download as CSV file: xf-goe280-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 280 (DAIMLER XI) 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3579   0.11169   0.11013  -0.0147   1.0000   0.0034
  -9.250  -0.3521   0.10820   0.10665  -0.0162   1.0000   0.0034
  -8.750  -0.3415   0.10091   0.09939  -0.0194   1.0000   0.0036
  -8.250  -0.3237   0.09455   0.09305  -0.0240   0.9882   0.0040
  -7.750  -0.3087   0.08593   0.08442  -0.0303   0.9590   0.0037
  -7.500  -0.3022   0.08240   0.08086  -0.0330   0.9455   0.0036
  -7.250  -0.2915   0.07842   0.07685  -0.0371   0.9343   0.0036
  -6.750  -0.2621   0.06923   0.06758  -0.0475   0.9144   0.0036
  -6.500  -0.2429   0.06354   0.06182  -0.0541   0.9055   0.0037
  -6.250  -0.2208   0.05835   0.05654  -0.0601   0.8966   0.0039
  -6.000  -0.1967   0.05449   0.05260  -0.0644   0.8888   0.0040
  -5.750  -0.1714   0.05049   0.04849  -0.0685   0.8810   0.0042
  -5.500  -0.1436   0.04575   0.04362  -0.0729   0.8723   0.0045
  -5.250  -0.1122   0.03867   0.03629  -0.0781   0.8639   0.0052
  -5.000  -0.0787   0.03030   0.02748  -0.0825   0.8545   0.0062
  -4.750  -0.0504   0.02772   0.02470  -0.0836   0.8414   0.0067
  -4.250   0.0108   0.01864   0.01469  -0.0858   0.8057   0.0092
  -4.000   0.0384   0.01776   0.01359  -0.0859   0.7780   0.0103
  -3.750   0.0680   0.01492   0.01027  -0.0863   0.7554   0.0127
  -3.500   0.0958   0.01496   0.01021  -0.0864   0.7361   0.0134
  -3.250   0.1254   0.01270   0.00750  -0.0866   0.7203   0.0176
  -3.000   0.1535   0.01279   0.00746  -0.0866   0.6983   0.0182
  -2.750   0.1818   0.01217   0.00665  -0.0869   0.6785   0.0191
  -2.500   0.2100   0.01232   0.00674  -0.0871   0.6608   0.0197
  -2.250   0.2383   0.01229   0.00661  -0.0872   0.6393   0.0204
  -2.000   0.2665   0.01211   0.00628  -0.0874   0.6110   0.0211
  -1.750   0.2943   0.01201   0.00595  -0.0875   0.5695   0.0221
  -1.500   0.3222   0.01173   0.00541  -0.0876   0.5288   0.0226
  -1.250   0.3504   0.01136   0.00485  -0.0877   0.5020   0.0229
  -1.000   0.3789   0.01101   0.00438  -0.0879   0.4863   0.0232
  -0.750   0.4074   0.01066   0.00392  -0.0881   0.4715   0.0235
  -0.500   0.4359   0.01031   0.00347  -0.0882   0.4582   0.0235
  -0.250   0.4643   0.01004   0.00310  -0.0884   0.4428   0.0237
   0.000   0.4927   0.00986   0.00283  -0.0886   0.4236   0.0242
   0.250   0.5210   0.00979   0.00267  -0.0888   0.4052   0.0252
   0.500   0.5491   0.00983   0.00261  -0.0889   0.3849   0.0262
   0.750   0.5772   0.00991   0.00263  -0.0890   0.3669   0.0269
   1.000   0.6052   0.01002   0.00267  -0.0892   0.3493   0.0273
   1.250   0.6335   0.00990   0.00245  -0.0894   0.3293   0.0285
   1.500   0.6615   0.00993   0.00237  -0.0896   0.3079   0.0294
   1.750   0.6889   0.01010   0.00239  -0.0897   0.2764   0.0298
   2.000   0.7159   0.01036   0.00246  -0.0898   0.2392   0.0302
   2.250   0.7433   0.01054   0.00253  -0.0899   0.2145   0.0310
   2.500   0.7707   0.01073   0.00261  -0.0900   0.1936   0.0318
   2.750   0.7978   0.01097   0.00273  -0.0900   0.1688   0.0317
   3.000   0.8250   0.01117   0.00284  -0.0900   0.1511   0.0316
   3.250   0.8522   0.01138   0.00296  -0.0901   0.1355   0.0315
   3.500   0.8792   0.01161   0.00312  -0.0901   0.1210   0.0316
   3.750   0.9064   0.01179   0.00325  -0.0901   0.1138   0.0318
   4.000   0.9336   0.01195   0.00338  -0.0902   0.1071   0.0323
   4.250   0.9605   0.01217   0.00356  -0.0902   0.0982   0.0339
   4.750   1.0060   0.01153   0.00447  -0.0892   0.0397   1.0000
   5.000   1.0313   0.01202   0.00487  -0.0889   0.0141   1.0000
   5.250   1.0577   0.01231   0.00519  -0.0888   0.0110   1.0000
   5.500   1.0842   0.01257   0.00547  -0.0887   0.0095   1.0000
   5.750   1.1104   0.01285   0.00577  -0.0886   0.0080   1.0000
   6.000   1.1361   0.01322   0.00619  -0.0883   0.0068   1.0000
   6.250   1.1620   0.01352   0.00652  -0.0882   0.0063   1.0000
   6.500   1.1876   0.01384   0.00686  -0.0880   0.0055   1.0000
   6.750   1.2127   0.01422   0.00726  -0.0877   0.0048   1.0000
   7.000   1.2372   0.01467   0.00776  -0.0873   0.0044   1.0000
   7.250   1.2616   0.01511   0.00827  -0.0869   0.0041   1.0000
   7.500   1.2854   0.01560   0.00880  -0.0864   0.0037   1.0000
   7.750   1.3090   0.01610   0.00935  -0.0859   0.0034   1.0000
   8.000   1.3321   0.01662   0.00991  -0.0854   0.0032   1.0000
   8.250   1.3533   0.01736   0.01073  -0.0845   0.0029   1.0000
   8.500   1.3756   0.01792   0.01137  -0.0838   0.0027   1.0000
   8.750   1.3961   0.01866   0.01219  -0.0828   0.0025   1.0000
   9.000   1.4156   0.01946   0.01308  -0.0817   0.0024   1.0000
   9.250   1.4342   0.02028   0.01398  -0.0805   0.0022   1.0000
   9.500   1.4522   0.02110   0.01487  -0.0792   0.0021   1.0000
   9.750   1.4695   0.02190   0.01575  -0.0778   0.0020   1.0000
  10.000   1.4858   0.02273   0.01665  -0.0764   0.0019   1.0000
  10.250   1.4993   0.02370   0.01770  -0.0744   0.0019   1.0000
  10.500   1.5037   0.02519   0.01932  -0.0711   0.0018   1.0000
  10.750   1.5029   0.02666   0.02094  -0.0670   0.0017   1.0000
  11.000   1.5021   0.02824   0.02263  -0.0632   0.0017   1.0000
  11.250   1.4993   0.03016   0.02467  -0.0597   0.0016   1.0000
  11.500   1.4932   0.03255   0.02718  -0.0563   0.0016   1.0000
  11.750   1.4851   0.03537   0.03012  -0.0534   0.0015   1.0000
  12.000   1.4749   0.03869   0.03355  -0.0507   0.0015   1.0000
  12.250   1.4690   0.04187   0.03682  -0.0486   0.0014   1.0000
  12.500   1.4662   0.04487   0.03992  -0.0470   0.0014   1.0000
  12.750   1.4655   0.04776   0.04291  -0.0459   0.0013   1.0000
  13.000   1.4645   0.05076   0.04601  -0.0451   0.0012   1.0000
  13.250   1.4627   0.05392   0.04929  -0.0446   0.0012   1.0000
  13.500   1.4596   0.05736   0.05285  -0.0442   0.0012   1.0000
  13.750   1.4552   0.06104   0.05666  -0.0441   0.0012   1.0000
  14.000   1.4493   0.06501   0.06075  -0.0443   0.0011   1.0000
  14.250   1.4422   0.06929   0.06517  -0.0448   0.0011   1.0000
  14.500   1.4343   0.07386   0.06988  -0.0457   0.0011   1.0000
  14.750   1.4255   0.07872   0.07488  -0.0471   0.0011   1.0000
  15.000   1.4162   0.08386   0.08015  -0.0488   0.0011   1.0000
  15.250   1.4063   0.08929   0.08571  -0.0509   0.0011   1.0000
  15.500   1.3946   0.09513   0.09169  -0.0531   0.0011   1.0000
  15.750   1.3830   0.10112   0.09782  -0.0557   0.0011   1.0000
  16.000   1.3710   0.10742   0.10426  -0.0587   0.0010   1.0000
  16.250   1.3587   0.11396   0.11093  -0.0619   0.0010   1.0000
  16.500   1.3463   0.12070   0.11780  -0.0654   0.0010   1.0000
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