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(Dicke 12.28%) (e171-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: (Dicke 12.28%) (e171-il)
Reynolds number: 200,000
Max Cl/Cd: 56.92 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e171-il-200000.txt
Download as CSV file: xf-e171-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: (Dicke 12.28%)                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.6716   0.11236   0.10883  -0.0066   1.0000   0.0351
 -12.500  -0.6810   0.10563   0.10214  -0.0092   1.0000   0.0330
 -11.750  -0.8152   0.06753   0.06337  -0.0347   1.0000   0.0264
 -11.500  -0.8337   0.06221   0.05793  -0.0361   1.0000   0.0258
 -11.250  -0.8546   0.05790   0.05343  -0.0364   1.0000   0.0257
 -11.000  -0.8701   0.05409   0.04947  -0.0357   1.0000   0.0251
 -10.750  -0.8878   0.05067   0.04582  -0.0336   1.0000   0.0250
 -10.500  -0.9019   0.04752   0.04244  -0.0305   1.0000   0.0246
 -10.250  -0.9103   0.04415   0.03878  -0.0276   1.0000   0.0242
 -10.000  -0.9130   0.04076   0.03504  -0.0250   1.0000   0.0241
  -9.750  -0.9097   0.03764   0.03157  -0.0226   1.0000   0.0239
  -9.500  -0.9015   0.03479   0.02836  -0.0205   1.0000   0.0241
  -9.250  -0.8889   0.03302   0.02631  -0.0187   1.0000   0.0255
  -9.000  -0.8741   0.03156   0.02452  -0.0170   1.0000   0.0265
  -8.750  -0.8575   0.02873   0.02140  -0.0156   1.0000   0.0274
  -8.500  -0.8375   0.02597   0.01853  -0.0147   1.0000   0.0287
  -8.250  -0.8186   0.02442   0.01695  -0.0135   1.0000   0.0304
  -8.000  -0.8001   0.02313   0.01558  -0.0121   1.0000   0.0328
  -7.750  -0.7806   0.02236   0.01467  -0.0107   1.0000   0.0360
  -7.500  -0.7677   0.02051   0.01288  -0.0086   1.0000   0.0398
  -7.250  -0.7516   0.01952   0.01184  -0.0068   1.0000   0.0443
  -7.000  -0.7383   0.01836   0.01068  -0.0045   1.0000   0.0506
  -6.750  -0.7226   0.01750   0.00978  -0.0025   1.0000   0.0593
  -6.500  -0.7119   0.01626   0.00869   0.0002   1.0000   0.0762
  -6.250  -0.7015   0.01500   0.00771   0.0029   1.0000   0.1165
  -6.000  -0.6905   0.01390   0.00699   0.0053   1.0000   0.1777
  -5.750  -0.6796   0.01296   0.00643   0.0077   1.0000   0.2465
  -5.500  -0.6700   0.01218   0.00599   0.0104   1.0000   0.3178
  -5.250  -0.6621   0.01163   0.00580   0.0135   1.0000   0.3879
  -5.000  -0.6302   0.01130   0.00578   0.0120   0.9934   0.4737
  -4.750  -0.5875   0.01127   0.00582   0.0088   0.9837   0.5278
  -4.500  -0.5462   0.01127   0.00576   0.0060   0.9730   0.5581
  -4.250  -0.5052   0.01128   0.00570   0.0034   0.9627   0.5823
  -4.000  -0.4635   0.01129   0.00567   0.0007   0.9536   0.6034
  -3.750  -0.4244   0.01127   0.00556  -0.0014   0.9425   0.6206
  -3.500  -0.3877   0.01124   0.00547  -0.0030   0.9298   0.6352
  -3.250  -0.3530   0.01121   0.00540  -0.0041   0.9166   0.6480
  -3.000  -0.3210   0.01118   0.00531  -0.0047   0.9026   0.6595
  -2.750  -0.2918   0.01117   0.00523  -0.0047   0.8883   0.6705
  -2.500  -0.2647   0.01118   0.00514  -0.0043   0.8743   0.6817
  -2.250  -0.2379   0.01118   0.00511  -0.0038   0.8612   0.6913
  -2.000  -0.2114   0.01118   0.00505  -0.0033   0.8490   0.7003
  -1.750  -0.1854   0.01119   0.00496  -0.0027   0.8377   0.7102
  -1.500  -0.1588   0.01119   0.00495  -0.0022   0.8268   0.7187
  -1.250  -0.1327   0.01118   0.00490  -0.0018   0.8158   0.7276
  -1.000  -0.1065   0.01119   0.00486  -0.0014   0.8061   0.7370
  -0.750  -0.0796   0.01119   0.00484  -0.0010   0.7972   0.7447
  -0.500  -0.0534   0.01118   0.00481  -0.0007   0.7873   0.7538
  -0.250  -0.0266   0.01118   0.00481  -0.0003   0.7790   0.7615
   0.000   0.0000   0.01117   0.00478   0.0000   0.7702   0.7702
   0.250   0.0266   0.01118   0.00481   0.0003   0.7615   0.7789
   0.500   0.0534   0.01118   0.00481   0.0007   0.7538   0.7873
   0.750   0.0796   0.01119   0.00484   0.0010   0.7447   0.7972
   1.000   0.1064   0.01119   0.00486   0.0014   0.7370   0.8061
   1.250   0.1327   0.01118   0.00490   0.0018   0.7276   0.8158
   1.500   0.1588   0.01119   0.00495   0.0022   0.7187   0.8268
   1.750   0.1853   0.01119   0.00496   0.0027   0.7103   0.8377
   2.000   0.2114   0.01118   0.00505   0.0033   0.7003   0.8490
   2.250   0.2378   0.01118   0.00511   0.0038   0.6913   0.8612
   2.500   0.2646   0.01118   0.00514   0.0043   0.6817   0.8743
   2.750   0.2918   0.01117   0.00523   0.0047   0.6705   0.8884
   3.000   0.3209   0.01118   0.00531   0.0047   0.6595   0.9026
   3.250   0.3530   0.01121   0.00540   0.0041   0.6480   0.9165
   3.500   0.3877   0.01124   0.00547   0.0030   0.6351   0.9298
   3.750   0.4244   0.01127   0.00556   0.0014   0.6206   0.9425
   4.000   0.4635   0.01129   0.00567  -0.0007   0.6034   0.9536
   4.250   0.5052   0.01128   0.00571  -0.0034   0.5824   0.9627
   4.500   0.5462   0.01127   0.00576  -0.0060   0.5581   0.9730
   4.750   0.5876   0.01127   0.00582  -0.0088   0.5280   0.9837
   5.000   0.6303   0.01130   0.00578  -0.0120   0.4738   0.9934
   5.250   0.6620   0.01163   0.00580  -0.0135   0.3888   1.0000
   5.500   0.6699   0.01217   0.00599  -0.0104   0.3183   1.0000
   5.750   0.6795   0.01296   0.00643  -0.0077   0.2469   1.0000
   6.000   0.6905   0.01390   0.00699  -0.0053   0.1781   1.0000
   6.250   0.7015   0.01499   0.00771  -0.0029   0.1167   1.0000
   6.500   0.7119   0.01626   0.00867  -0.0002   0.0760   1.0000
   6.750   0.7224   0.01752   0.00980   0.0025   0.0591   1.0000
   7.000   0.7383   0.01836   0.01067   0.0045   0.0504   1.0000
   7.250   0.7517   0.01951   0.01183   0.0068   0.0443   1.0000
   7.500   0.7677   0.02052   0.01289   0.0086   0.0399   1.0000
   7.750   0.7807   0.02235   0.01467   0.0107   0.0359   1.0000
   8.000   0.8001   0.02313   0.01558   0.0121   0.0328   1.0000
   8.250   0.8189   0.02443   0.01696   0.0135   0.0306   1.0000
   8.500   0.8376   0.02596   0.01852   0.0147   0.0287   1.0000
   8.750   0.8576   0.02872   0.02138   0.0156   0.0274   1.0000
   9.000   0.8744   0.03168   0.02464   0.0169   0.0266   1.0000
   9.250   0.8890   0.03292   0.02620   0.0187   0.0254   1.0000
   9.500   0.9016   0.03479   0.02836   0.0205   0.0241   1.0000
   9.750   0.9100   0.03764   0.03156   0.0226   0.0240   1.0000
  10.000   0.9132   0.04072   0.03500   0.0250   0.0239   1.0000
  10.250   0.9111   0.04408   0.03869   0.0275   0.0242   1.0000
  10.500   0.9014   0.04753   0.04246   0.0306   0.0244   1.0000
  10.750   0.8878   0.05071   0.04587   0.0336   0.0249   1.0000
  11.000   0.8704   0.05416   0.04954   0.0357   0.0252   1.0000
  11.250   0.8526   0.05796   0.05353   0.0364   0.0255   1.0000
  11.500   0.8349   0.06228   0.05799   0.0360   0.0259   1.0000
  11.750   0.8136   0.06744   0.06331   0.0345   0.0262   1.0000
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