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GOE 282 (DAIMLER XIII) AIRFOIL (goe282-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 282 (DAIMLER XIII) AIRFOIL (goe282-il)
Reynolds number: 200,000
Max Cl/Cd: 75.64 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe282-il-200000-n5.txt
Download as CSV file: xf-goe282-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 282 (DAIMLER XIII) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3283   0.09921   0.09583  -0.0308   1.0000   0.0168
  -8.500  -0.3353   0.09670   0.09339  -0.0296   1.0000   0.0167
  -8.250  -0.3450   0.09439   0.09114  -0.0279   1.0000   0.0167
  -8.000  -0.3464   0.09083   0.08762  -0.0293   0.9978   0.0168
  -7.750  -0.3367   0.08542   0.08223  -0.0351   0.9923   0.0169
  -7.500  -0.3205   0.07771   0.07451  -0.0450   0.9864   0.0174
  -7.250  -0.3003   0.07418   0.07098  -0.0504   0.9809   0.0183
  -7.000  -0.2741   0.07136   0.06813  -0.0555   0.9771   0.0195
  -6.750  -0.2512   0.06565   0.06237  -0.0636   0.9704   0.0202
  -6.500  -0.2196   0.05746   0.05407  -0.0757   0.9654   0.0211
  -6.250  -0.1815   0.02778   0.02291  -0.1038   0.9571   0.0251
  -6.000  -0.1465   0.02676   0.02178  -0.1062   0.9539   0.0269
  -5.750  -0.1103   0.02412   0.01865  -0.1093   0.9517   0.0296
  -5.500  -0.0813   0.02236   0.01635  -0.1102   0.9457   0.0324
  -5.250  -0.0492   0.02033   0.01399  -0.1118   0.9415   0.0347
  -5.000  -0.0151   0.01961   0.01317  -0.1134   0.9382   0.0374
  -4.750   0.0152   0.01864   0.01197  -0.1140   0.9326   0.0397
  -4.500   0.0467   0.01778   0.01086  -0.1148   0.9268   0.0420
  -4.250   0.0813   0.01704   0.00988  -0.1161   0.9226   0.0437
  -4.000   0.1100   0.01616   0.00883  -0.1162   0.9148   0.0447
  -3.750   0.1422   0.01515   0.00770  -0.1170   0.9090   0.0464
  -3.500   0.1718   0.01455   0.00704  -0.1173   0.9007   0.0485
  -3.250   0.2037   0.01404   0.00646  -0.1180   0.8932   0.0510
  -3.000   0.2325   0.01361   0.00595  -0.1180   0.8829   0.0529
  -2.750   0.2625   0.01321   0.00546  -0.1182   0.8729   0.0548
  -2.500   0.2925   0.01287   0.00502  -0.1184   0.8618   0.0571
  -2.250   0.3217   0.01252   0.00461  -0.1184   0.8486   0.0609
  -2.000   0.3505   0.01221   0.00428  -0.1183   0.8337   0.0677
  -1.750   0.3789   0.01192   0.00407  -0.1182   0.8152   0.0863
  -1.500   0.4076   0.01178   0.00394  -0.1181   0.7934   0.1228
  -1.250   0.4359   0.01177   0.00379  -0.1178   0.7687   0.1433
  -1.000   0.4636   0.01180   0.00365  -0.1174   0.7429   0.1562
  -0.750   0.4907   0.01186   0.00357  -0.1170   0.7176   0.1660
  -0.500   0.5173   0.01195   0.00354  -0.1166   0.6923   0.1780
  -0.250   0.5438   0.01206   0.00351  -0.1162   0.6673   0.1902
   0.000   0.5704   0.01214   0.00349  -0.1158   0.6445   0.2015
   0.250   0.5971   0.01218   0.00347  -0.1155   0.6254   0.2098
   0.750   0.6505   0.01230   0.00346  -0.1149   0.5895   0.2279
   1.000   0.6770   0.01237   0.00349  -0.1146   0.5736   0.2421
   1.500   0.7302   0.01244   0.00361  -0.1142   0.5471   0.3055
   2.000   0.7771   0.01131   0.00378  -0.1120   0.5244   1.0000
   2.250   0.8038   0.01152   0.00389  -0.1118   0.5135   1.0000
   2.500   0.8302   0.01174   0.00402  -0.1115   0.5024   1.0000
   2.750   0.8567   0.01196   0.00416  -0.1112   0.4905   1.0000
   3.000   0.8831   0.01216   0.00432  -0.1109   0.4779   1.0000
   3.250   0.9093   0.01238   0.00449  -0.1106   0.4647   1.0000
   3.500   0.9353   0.01260   0.00467  -0.1102   0.4511   1.0000
   3.750   0.9612   0.01283   0.00486  -0.1099   0.4367   1.0000
   4.000   0.9867   0.01308   0.00507  -0.1094   0.4204   1.0000
   4.250   1.0113   0.01337   0.00528  -0.1089   0.3996   1.0000
   4.500   1.0352   0.01371   0.00552  -0.1082   0.3744   1.0000
   4.750   1.0584   0.01412   0.00579  -0.1074   0.3493   1.0000
   5.000   1.0817   0.01453   0.00612  -0.1067   0.3282   1.0000
   5.500   1.1273   0.01544   0.00684  -0.1052   0.2900   1.0000
   5.750   1.1488   0.01599   0.00728  -0.1042   0.2672   1.0000
   6.000   1.1705   0.01652   0.00770  -0.1033   0.2484   1.0000
   6.250   1.1927   0.01700   0.00813  -0.1025   0.2327   1.0000
   6.500   1.2146   0.01749   0.00857  -0.1016   0.2166   1.0000
   6.750   1.2365   0.01798   0.00903  -0.1008   0.1995   1.0000
   7.000   1.2551   0.01872   0.00955  -0.0995   0.1559   1.0000
   7.250   1.2619   0.02057   0.01075  -0.0967   0.0799   1.0000
   7.500   1.2791   0.02142   0.01152  -0.0951   0.0631   1.0000
   7.750   1.2953   0.02232   0.01231  -0.0935   0.0444   1.0000
   8.000   1.3061   0.02363   0.01346  -0.0910   0.0180   1.0000
   8.250   1.3229   0.02434   0.01431  -0.0893   0.0161   1.0000
   8.500   1.3383   0.02508   0.01519  -0.0873   0.0153   1.0000
   8.750   1.3502   0.02593   0.01619  -0.0849   0.0143   1.0000
   9.000   1.3600   0.02696   0.01738  -0.0822   0.0133   1.0000
   9.250   1.3677   0.02817   0.01877  -0.0794   0.0125   1.0000
   9.500   1.3740   0.02953   0.02030  -0.0765   0.0120   1.0000
   9.750   1.3790   0.03103   0.02197  -0.0737   0.0116   1.0000
  10.000   1.3868   0.03234   0.02343  -0.0715   0.0114   1.0000
  10.250   1.3931   0.03384   0.02510  -0.0693   0.0111   1.0000
  10.500   1.3979   0.03550   0.02692  -0.0671   0.0108   1.0000
  10.750   1.4012   0.03736   0.02892  -0.0650   0.0105   1.0000
  11.000   1.4025   0.03948   0.03120  -0.0631   0.0100   1.0000
  11.250   1.4023   0.04187   0.03373  -0.0615   0.0097   1.0000
  11.500   1.3999   0.04462   0.03662  -0.0601   0.0093   1.0000
  11.750   1.3959   0.04771   0.03985  -0.0590   0.0091   1.0000
  12.000   1.3901   0.05121   0.04350  -0.0583   0.0090   1.0000
  12.250   1.3830   0.05505   0.04747  -0.0580   0.0088   1.0000
  12.500   1.3748   0.05918   0.05172  -0.0580   0.0087   1.0000
  12.750   1.3664   0.06349   0.05615  -0.0583   0.0086   1.0000
  13.000   1.3574   0.06795   0.06069  -0.0586   0.0086   1.0000
  13.250   1.3498   0.07226   0.06508  -0.0590   0.0085   1.0000
  13.500   1.3434   0.07623   0.06905  -0.0589   0.0084   1.0000
  13.750   1.3421   0.07982   0.07274  -0.0592   0.0083   1.0000
  14.000   1.3412   0.08333   0.07635  -0.0595   0.0082   1.0000
  14.250   1.3410   0.08676   0.07991  -0.0598   0.0081   1.0000
  14.500   1.3414   0.09009   0.08333  -0.0600   0.0081   1.0000
  14.750   1.3420   0.09339   0.08672  -0.0603   0.0080   1.0000
  15.000   1.3430   0.09663   0.09005  -0.0605   0.0079   1.0000
  15.250   1.3435   0.10004   0.09358  -0.0610   0.0078   1.0000
  15.500   1.3438   0.10356   0.09722  -0.0616   0.0076   1.0000
  15.750   1.3426   0.10747   0.10126  -0.0627   0.0075   1.0000
  16.000   1.3415   0.11138   0.10530  -0.0638   0.0073   1.0000
  16.250   1.3400   0.11540   0.10944  -0.0651   0.0071   1.0000
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