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RAE 104 AIRFOIL (rae104-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: RAE 104 AIRFOIL (rae104-il)
Reynolds number: 50,000
Max Cl/Cd: 26.21 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rae104-il-50000-n5.txt
Download as CSV file: xf-rae104-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAE 104 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.6355   0.10303   0.09577  -0.0242   1.0000   0.0432
 -11.000  -0.6393   0.09748   0.09025  -0.0269   1.0000   0.0429
 -10.750  -0.6478   0.09165   0.08443  -0.0301   1.0000   0.0426
 -10.500  -0.6590   0.08618   0.07897  -0.0330   1.0000   0.0423
 -10.250  -0.6732   0.08110   0.07386  -0.0353   1.0000   0.0420
 -10.000  -0.6889   0.07662   0.06932  -0.0364   1.0000   0.0417
  -9.750  -0.7055   0.07271   0.06534  -0.0361   1.0000   0.0415
  -9.500  -0.7218   0.06921   0.06174  -0.0345   1.0000   0.0413
  -9.250  -0.7346   0.06565   0.05802  -0.0326   1.0000   0.0412
  -9.000  -0.7443   0.06202   0.05416  -0.0306   1.0000   0.0412
  -8.750  -0.7507   0.05849   0.05034  -0.0283   1.0000   0.0414
  -8.500  -0.7544   0.05504   0.04652  -0.0257   1.0000   0.0419
  -8.250  -0.7559   0.05185   0.04281  -0.0229   1.0000   0.0430
  -8.000  -0.7514   0.04855   0.03928  -0.0207   1.0000   0.0444
  -7.750  -0.7420   0.04593   0.03648  -0.0189   1.0000   0.0460
  -7.500  -0.7312   0.04320   0.03343  -0.0168   1.0000   0.0473
  -7.250  -0.7179   0.04043   0.03028  -0.0148   1.0000   0.0486
  -7.000  -0.7015   0.03780   0.02721  -0.0129   1.0000   0.0503
  -6.750  -0.6829   0.03560   0.02456  -0.0112   1.0000   0.0537
  -6.500  -0.6629   0.03352   0.02229  -0.0100   1.0000   0.0581
  -6.250  -0.6396   0.03166   0.02027  -0.0090   1.0000   0.0625
  -6.000  -0.6128   0.02997   0.01826  -0.0082   1.0000   0.0680
  -5.750  -0.5916   0.02857   0.01691  -0.0071   1.0000   0.0772
  -5.500  -0.5702   0.02720   0.01542  -0.0057   1.0000   0.0862
  -5.250  -0.5536   0.02601   0.01421  -0.0037   1.0000   0.0995
  -5.000  -0.5401   0.02485   0.01310  -0.0014   1.0000   0.1196
  -4.750  -0.5295   0.02356   0.01202   0.0013   1.0000   0.1506
  -4.500  -0.5237   0.02197   0.01103   0.0045   1.0000   0.2218
  -4.250  -0.5253   0.02008   0.01027   0.0090   1.0000   0.3867
  -4.000  -0.5148   0.01965   0.01119   0.0150   1.0000   0.6543
  -3.750  -0.5042   0.02001   0.01146   0.0199   1.0000   0.7389
  -3.500  -0.4859   0.02066   0.01198   0.0241   1.0000   0.7993
  -3.250  -0.4378   0.02196   0.01296   0.0240   1.0000   0.8530
  -3.000  -0.3814   0.02273   0.01329   0.0206   1.0000   0.8855
  -2.750  -0.3226   0.02296   0.01314   0.0153   1.0000   0.9032
  -2.500  -0.2815   0.02289   0.01282   0.0125   1.0000   0.9170
  -2.250  -0.2472   0.02275   0.01246   0.0106   1.0000   0.9293
  -2.000  -0.2148   0.02260   0.01214   0.0089   1.0000   0.9406
  -1.750  -0.1785   0.02240   0.01180   0.0064   1.0000   0.9495
  -1.500  -0.1481   0.02224   0.01153   0.0048   1.0000   0.9592
  -1.250  -0.1186   0.02211   0.01128   0.0034   1.0000   0.9688
  -1.000  -0.0855   0.02193   0.01104   0.0011   1.0000   0.9769
  -0.750  -0.0551   0.02182   0.01087  -0.0007   1.0000   0.9856
  -0.500  -0.0236   0.02172   0.01074  -0.0029   1.0000   0.9941
  -0.250   0.0001   0.02167   0.01066  -0.0036   1.0000   1.0000
   0.000   0.0000   0.02167   0.01067   0.0000   1.0000   1.0000
   0.250  -0.0001   0.02167   0.01066   0.0036   1.0000   1.0000
   0.500   0.0235   0.02172   0.01074   0.0029   0.9941   1.0000
   0.750   0.0550   0.02182   0.01087   0.0007   0.9856   1.0000
   1.000   0.0854   0.02193   0.01103  -0.0011   0.9769   1.0000
   1.250   0.1185   0.02211   0.01128  -0.0033   0.9689   1.0000
   1.500   0.1479   0.02224   0.01153  -0.0048   0.9592   1.0000
   1.750   0.1784   0.02240   0.01180  -0.0064   0.9495   1.0000
   2.000   0.2148   0.02260   0.01214  -0.0089   0.9406   1.0000
   2.250   0.2471   0.02275   0.01245  -0.0106   0.9293   1.0000
   2.500   0.2814   0.02289   0.01282  -0.0124   0.9170   1.0000
   2.750   0.3224   0.02295   0.01314  -0.0153   0.9032   1.0000
   3.000   0.3808   0.02273   0.01329  -0.0205   0.8856   1.0000
   3.250   0.4377   0.02195   0.01296  -0.0240   0.8529   1.0000
   3.500   0.4846   0.02071   0.01203  -0.0240   0.8004   1.0000
   3.750   0.5042   0.02001   0.01146  -0.0199   0.7389   1.0000
   4.000   0.5147   0.01964   0.01118  -0.0149   0.6537   1.0000
   4.250   0.5251   0.02009   0.01027  -0.0090   0.3854   1.0000
   4.500   0.5236   0.02197   0.01103  -0.0045   0.2216   1.0000
   4.750   0.5295   0.02356   0.01202  -0.0013   0.1507   1.0000
   5.000   0.5401   0.02485   0.01309   0.0014   0.1198   1.0000
   5.250   0.5537   0.02601   0.01421   0.0037   0.1000   1.0000
   5.500   0.5702   0.02719   0.01541   0.0057   0.0863   1.0000
   5.750   0.5916   0.02856   0.01690   0.0071   0.0774   1.0000
   6.000   0.6128   0.02997   0.01825   0.0082   0.0681   1.0000
   6.250   0.6396   0.03166   0.02028   0.0090   0.0624   1.0000
   6.500   0.6629   0.03352   0.02228   0.0100   0.0581   1.0000
   6.750   0.6829   0.03559   0.02455   0.0112   0.0537   1.0000
   7.000   0.7015   0.03782   0.02722   0.0129   0.0502   1.0000
   7.250   0.7180   0.04043   0.03028   0.0148   0.0486   1.0000
   7.500   0.7313   0.04318   0.03341   0.0168   0.0474   1.0000
   7.750   0.7420   0.04594   0.03650   0.0189   0.0461   1.0000
   8.000   0.7514   0.04855   0.03928   0.0207   0.0444   1.0000
   8.250   0.7554   0.05183   0.04281   0.0229   0.0428   1.0000
   8.500   0.7546   0.05502   0.04649   0.0257   0.0420   1.0000
   8.750   0.7508   0.05849   0.05033   0.0283   0.0414   1.0000
   9.000   0.7442   0.06205   0.05419   0.0306   0.0412   1.0000
   9.250   0.7348   0.06566   0.05802   0.0326   0.0412   1.0000
   9.500   0.7226   0.06917   0.06169   0.0344   0.0414   1.0000
   9.750   0.7057   0.07270   0.06533   0.0361   0.0415   1.0000
  10.000   0.6900   0.07656   0.06926   0.0364   0.0417   1.0000
  10.250   0.6739   0.08107   0.07383   0.0352   0.0420   1.0000
  10.500   0.6601   0.08607   0.07886   0.0331   0.0423   1.0000
  10.750   0.6481   0.09169   0.08447   0.0300   0.0426   1.0000
  11.000   0.6406   0.09733   0.09009   0.0270   0.0429   1.0000
  11.250   0.6368   0.10285   0.09559   0.0244   0.0432   1.0000
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