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RAE 101 AIRFOIL (rae101-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: RAE 101 AIRFOIL (rae101-il)
Reynolds number: 100,000
Max Cl/Cd: 36.4 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rae101-il-100000-n5.txt
Download as CSV file: xf-rae101-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAE 101 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.7471   0.08116   0.07601  -0.0150   1.0000   0.0254
 -11.000  -0.7755   0.07206   0.06680  -0.0221   1.0000   0.0250
 -10.750  -0.8008   0.06542   0.06001  -0.0265   1.0000   0.0248
 -10.500  -0.8235   0.06040   0.05480  -0.0283   1.0000   0.0245
 -10.250  -0.8434   0.05648   0.05067  -0.0277   1.0000   0.0245
 -10.000  -0.8588   0.05298   0.04691  -0.0258   1.0000   0.0246
  -9.750  -0.8672   0.04932   0.04292  -0.0241   1.0000   0.0247
  -9.500  -0.8696   0.04586   0.03909  -0.0223   1.0000   0.0251
  -9.250  -0.8668   0.04275   0.03557  -0.0205   1.0000   0.0261
  -9.000  -0.8602   0.03988   0.03220  -0.0187   1.0000   0.0273
  -8.750  -0.8497   0.03722   0.02906  -0.0170   1.0000   0.0283
  -8.500  -0.8353   0.03459   0.02627  -0.0159   1.0000   0.0293
  -8.250  -0.8183   0.03259   0.02405  -0.0148   1.0000   0.0303
  -8.000  -0.7999   0.03075   0.02201  -0.0137   1.0000   0.0316
  -7.750  -0.7804   0.02912   0.02016  -0.0126   1.0000   0.0337
  -7.500  -0.7597   0.02772   0.01847  -0.0115   1.0000   0.0364
  -7.250  -0.7400   0.02600   0.01668  -0.0104   1.0000   0.0387
  -7.000  -0.7203   0.02468   0.01531  -0.0093   1.0000   0.0411
  -6.750  -0.7000   0.02357   0.01410  -0.0082   1.0000   0.0447
  -6.500  -0.6803   0.02245   0.01289  -0.0069   1.0000   0.0491
  -6.250  -0.6616   0.02139   0.01184  -0.0055   1.0000   0.0537
  -6.000  -0.6416   0.02053   0.01085  -0.0042   1.0000   0.0598
  -5.750  -0.6231   0.01957   0.00990  -0.0028   1.0000   0.0686
  -5.500  -0.6041   0.01866   0.00901  -0.0014   1.0000   0.0796
  -5.250  -0.5847   0.01782   0.00821   0.0000   1.0000   0.0981
  -5.000  -0.5660   0.01690   0.00746   0.0013   1.0000   0.1280
  -4.750  -0.5484   0.01587   0.00677   0.0027   1.0000   0.1861
  -4.500  -0.5324   0.01478   0.00623   0.0044   1.0000   0.2851
  -4.250  -0.5145   0.01413   0.00596   0.0060   1.0000   0.3803
  -4.000  -0.4947   0.01374   0.00575   0.0075   1.0000   0.4413
  -3.750  -0.4743   0.01345   0.00558   0.0091   1.0000   0.4870
  -3.500  -0.4538   0.01322   0.00541   0.0106   1.0000   0.5253
  -3.250  -0.4331   0.01303   0.00528   0.0121   1.0000   0.5593
  -3.000  -0.4126   0.01286   0.00518   0.0136   1.0000   0.5901
  -2.750  -0.3923   0.01271   0.00510   0.0152   1.0000   0.6194
  -2.500  -0.3722   0.01259   0.00502   0.0167   1.0000   0.6471
  -2.250  -0.3445   0.01250   0.00498   0.0167   0.9953   0.6741
  -2.000  -0.3053   0.01243   0.00495   0.0144   0.9837   0.6994
  -1.500  -0.2279   0.01227   0.00480   0.0102   0.9589   0.7431
  -1.250  -0.1893   0.01219   0.00473   0.0082   0.9458   0.7643
  -1.000  -0.1511   0.01212   0.00468   0.0064   0.9316   0.7842
  -0.750  -0.1132   0.01206   0.00464   0.0047   0.9164   0.8051
  -0.500  -0.0754   0.01202   0.00461   0.0030   0.9003   0.8255
  -0.250  -0.0371   0.01199   0.00460   0.0014   0.8835   0.8453
   0.000   0.0000   0.01198   0.00459   0.0000   0.8649   0.8648
   0.250   0.0371   0.01199   0.00460  -0.0014   0.8453   0.8835
   0.500   0.0754   0.01202   0.00461  -0.0030   0.8255   0.9003
   0.750   0.1132   0.01206   0.00464  -0.0047   0.8051   0.9164
   1.000   0.1510   0.01212   0.00468  -0.0064   0.7842   0.9316
   1.250   0.1892   0.01219   0.00472  -0.0082   0.7643   0.9458
   1.500   0.2279   0.01227   0.00479  -0.0102   0.7431   0.9590
   1.750   0.2665   0.01235   0.00486  -0.0123   0.7222   0.9715
   2.000   0.3053   0.01243   0.00494  -0.0144   0.6994   0.9838
   2.250   0.3445   0.01249   0.00498  -0.0167   0.6741   0.9954
   2.500   0.3720   0.01259   0.00502  -0.0167   0.6472   1.0000
   2.750   0.3922   0.01271   0.00510  -0.0151   0.6194   1.0000
   3.000   0.4125   0.01285   0.00518  -0.0136   0.5902   1.0000
   3.250   0.4330   0.01302   0.00528  -0.0120   0.5595   1.0000
   3.500   0.4536   0.01322   0.00541  -0.0105   0.5253   1.0000
   3.750   0.4742   0.01345   0.00558  -0.0090   0.4871   1.0000
   4.000   0.4945   0.01374   0.00575  -0.0075   0.4412   1.0000
   4.250   0.5143   0.01413   0.00596  -0.0060   0.3801   1.0000
   4.500   0.5322   0.01479   0.00623  -0.0043   0.2848   1.0000
   4.750   0.5483   0.01587   0.00677  -0.0027   0.1861   1.0000
   5.000   0.5660   0.01690   0.00746  -0.0013   0.1280   1.0000
   5.250   0.5847   0.01782   0.00821   0.0001   0.0981   1.0000
   5.500   0.6040   0.01866   0.00901   0.0014   0.0794   1.0000
   5.750   0.6230   0.01956   0.00990   0.0028   0.0686   1.0000
   6.000   0.6416   0.02052   0.01085   0.0042   0.0599   1.0000
   6.250   0.6616   0.02139   0.01184   0.0055   0.0536   1.0000
   6.500   0.6804   0.02244   0.01289   0.0069   0.0491   1.0000
   6.750   0.7001   0.02356   0.01410   0.0081   0.0447   1.0000
   7.000   0.7203   0.02467   0.01531   0.0093   0.0411   1.0000
   7.250   0.7401   0.02600   0.01669   0.0104   0.0387   1.0000
   7.500   0.7598   0.02771   0.01847   0.0115   0.0364   1.0000
   7.750   0.7805   0.02910   0.02014   0.0126   0.0336   1.0000
   8.000   0.8001   0.03074   0.02200   0.0137   0.0317   1.0000
   8.250   0.8185   0.03259   0.02405   0.0148   0.0304   1.0000
   8.500   0.8355   0.03460   0.02624   0.0159   0.0293   1.0000
   8.750   0.8501   0.03719   0.02904   0.0170   0.0284   1.0000
   9.000   0.8606   0.03991   0.03221   0.0186   0.0274   1.0000
   9.250   0.8671   0.04277   0.03559   0.0204   0.0262   1.0000
   9.500   0.8699   0.04591   0.03914   0.0222   0.0253   1.0000
   9.750   0.8676   0.04934   0.04295   0.0240   0.0248   1.0000
  10.000   0.8595   0.05296   0.04690   0.0257   0.0246   1.0000
  10.250   0.8436   0.05654   0.05073   0.0276   0.0245   1.0000
  10.500   0.8236   0.06049   0.05489   0.0282   0.0246   1.0000
  10.750   0.8016   0.06542   0.06000   0.0264   0.0247   1.0000
  11.000   0.7773   0.07193   0.06666   0.0221   0.0251   1.0000
  11.250   0.7491   0.08093   0.07578   0.0151   0.0255   1.0000
  11.500   0.7217   0.09229   0.08716   0.0069   0.0260   1.0000
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