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RAE 104 AIRFOIL (rae104-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: RAE 104 AIRFOIL (rae104-il)
Reynolds number: 500,000
Max Cl/Cd: 49.7 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rae104-il-500000-n5.txt
Download as CSV file: xf-rae104-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.8703   0.05332   0.05063  -0.0429   1.0000   0.0056
 -12.000  -0.8855   0.04915   0.04629  -0.0435   1.0000   0.0058
 -11.750  -0.9215   0.04317   0.03999  -0.0423   1.0000   0.0057
 -11.500  -0.9329   0.04036   0.03697  -0.0401   1.0000   0.0058
 -11.250  -0.9558   0.03651   0.03280  -0.0360   1.0000   0.0057
 -11.000  -0.9625   0.03443   0.03051  -0.0322   1.0000   0.0059
 -10.750  -0.9696   0.03204   0.02783  -0.0280   1.0000   0.0059
 -10.500  -0.9671   0.03003   0.02557  -0.0250   1.0000   0.0061
 -10.250  -0.9617   0.02808   0.02336  -0.0222   1.0000   0.0063
 -10.000  -0.9534   0.02632   0.02132  -0.0197   1.0000   0.0064
  -9.750  -0.9424   0.02481   0.01959  -0.0174   1.0000   0.0066
  -9.500  -0.9296   0.02347   0.01805  -0.0152   1.0000   0.0068
  -9.250  -0.9145   0.02247   0.01688  -0.0134   1.0000   0.0071
  -9.000  -0.8993   0.02144   0.01568  -0.0115   1.0000   0.0072
  -8.750  -0.8866   0.02007   0.01416  -0.0092   1.0000   0.0076
  -8.500  -0.8709   0.01925   0.01326  -0.0073   1.0000   0.0080
  -8.250  -0.8545   0.01856   0.01250  -0.0055   1.0000   0.0083
  -8.000  -0.8384   0.01789   0.01174  -0.0036   1.0000   0.0087
  -7.750  -0.8121   0.01707   0.01082  -0.0038   0.9973   0.0091
  -7.500  -0.7840   0.01627   0.00993  -0.0044   0.9920   0.0097
  -7.250  -0.7554   0.01554   0.00910  -0.0051   0.9866   0.0103
  -7.000  -0.7255   0.01492   0.00838  -0.0060   0.9818   0.0108
  -6.750  -0.6979   0.01404   0.00743  -0.0065   0.9753   0.0117
  -6.500  -0.6657   0.01353   0.00687  -0.0079   0.9705   0.0131
  -6.250  -0.6352   0.01310   0.00640  -0.0088   0.9632   0.0146
  -6.000  -0.6027   0.01266   0.00589  -0.0102   0.9568   0.0158
  -5.750  -0.5732   0.01206   0.00525  -0.0109   0.9481   0.0181
  -5.500  -0.5418   0.01167   0.00481  -0.0120   0.9400   0.0209
  -5.250  -0.5124   0.01133   0.00442  -0.0126   0.9300   0.0239
  -5.000  -0.4850   0.01097   0.00405  -0.0127   0.9194   0.0295
  -4.750  -0.4582   0.01069   0.00373  -0.0126   0.9091   0.0354
  -4.250  -0.4081   0.01011   0.00317  -0.0118   0.8885   0.0612
  -4.000  -0.3840   0.00981   0.00292  -0.0112   0.8791   0.0849
  -3.500  -0.3381   0.00905   0.00245  -0.0097   0.8622   0.1745
  -3.250  -0.3169   0.00853   0.00220  -0.0087   0.8550   0.2531
  -3.000  -0.2964   0.00799   0.00198  -0.0076   0.8476   0.3423
  -2.750  -0.2776   0.00735   0.00174  -0.0061   0.8412   0.4548
  -2.500  -0.2603   0.00673   0.00158  -0.0041   0.8345   0.5725
  -2.250  -0.2385   0.00649   0.00156  -0.0028   0.8287   0.6495
  -2.000  -0.2134   0.00642   0.00154  -0.0022   0.8233   0.6831
  -1.750  -0.1875   0.00638   0.00153  -0.0017   0.8182   0.7047
  -1.500  -0.1612   0.00636   0.00151  -0.0014   0.8138   0.7223
  -1.250  -0.1347   0.00634   0.00150  -0.0011   0.8087   0.7364
  -1.000  -0.1080   0.00633   0.00149  -0.0008   0.8038   0.7482
  -0.750  -0.0811   0.00633   0.00148  -0.0006   0.7994   0.7586
  -0.500  -0.0541   0.00632   0.00148  -0.0004   0.7942   0.7679
  -0.250  -0.0271   0.00631   0.00148  -0.0002   0.7886   0.7756
   0.000   0.0000   0.00632   0.00147   0.0000   0.7829   0.7829
   0.250   0.0271   0.00631   0.00148   0.0002   0.7756   0.7886
   0.500   0.0541   0.00632   0.00148   0.0004   0.7679   0.7942
   0.750   0.0811   0.00633   0.00148   0.0006   0.7585   0.7994
   1.000   0.1080   0.00633   0.00149   0.0008   0.7482   0.8038
   1.250   0.1347   0.00634   0.00150   0.0011   0.7364   0.8088
   1.500   0.1612   0.00636   0.00151   0.0014   0.7221   0.8138
   1.750   0.1875   0.00638   0.00153   0.0017   0.7046   0.8182
   2.000   0.2134   0.00642   0.00154   0.0022   0.6834   0.8233
   2.250   0.2385   0.00649   0.00156   0.0028   0.6486   0.8287
   2.500   0.2603   0.00672   0.00158   0.0041   0.5731   0.8345
   2.750   0.2777   0.00734   0.00174   0.0061   0.4550   0.8412
   3.000   0.2964   0.00798   0.00198   0.0076   0.3429   0.8476
   3.250   0.3168   0.00854   0.00220   0.0087   0.2518   0.8550
   3.500   0.3381   0.00905   0.00245   0.0097   0.1746   0.8622
   3.750   0.3607   0.00945   0.00268   0.0105   0.1230   0.8705
   4.000   0.3840   0.00981   0.00292   0.0112   0.0844   0.8791
   4.250   0.4081   0.01011   0.00317   0.0118   0.0613   0.8886
   4.750   0.4582   0.01069   0.00373   0.0126   0.0355   0.9092
   5.000   0.4850   0.01097   0.00405   0.0127   0.0295   0.9194
   5.250   0.5125   0.01132   0.00441   0.0125   0.0243   0.9300
   5.500   0.5418   0.01167   0.00481   0.0120   0.0210   0.9401
   5.750   0.5732   0.01205   0.00524   0.0109   0.0182   0.9481
   6.000   0.6026   0.01266   0.00589   0.0102   0.0158   0.9569
   6.250   0.6351   0.01309   0.00639   0.0089   0.0146   0.9632
   6.500   0.6656   0.01353   0.00687   0.0079   0.0131   0.9705
   6.750   0.6978   0.01404   0.00742   0.0065   0.0117   0.9753
   7.000   0.7255   0.01491   0.00836   0.0060   0.0108   0.9818
   7.250   0.7554   0.01553   0.00908   0.0051   0.0103   0.9866
   7.500   0.7839   0.01627   0.00992   0.0045   0.0097   0.9920
   7.750   0.8121   0.01704   0.01079   0.0038   0.0091   0.9972
   8.000   0.8386   0.01787   0.01174   0.0035   0.0087   1.0000
   8.250   0.8549   0.01851   0.01245   0.0054   0.0082   1.0000
   8.500   0.8708   0.01927   0.01329   0.0073   0.0080   1.0000
   8.750   0.8862   0.02014   0.01424   0.0093   0.0077   1.0000
   9.000   0.8986   0.02157   0.01583   0.0116   0.0072   1.0000
   9.250   0.9140   0.02256   0.01698   0.0134   0.0071   1.0000
   9.500   0.9293   0.02353   0.01811   0.0153   0.0069   1.0000
   9.750   0.9418   0.02492   0.01972   0.0175   0.0067   1.0000
  10.000   0.9532   0.02636   0.02137   0.0197   0.0065   1.0000
  10.250   0.9602   0.02831   0.02362   0.0224   0.0064   1.0000
  10.500   0.9666   0.03010   0.02565   0.0250   0.0061   1.0000
  10.750   0.9680   0.03226   0.02808   0.0282   0.0060   1.0000
  11.000   0.9602   0.03470   0.03079   0.0325   0.0059   1.0000
  11.250   0.9515   0.03698   0.03332   0.0364   0.0058   1.0000
  11.500   0.9409   0.03955   0.03611   0.0396   0.0057   1.0000
  11.750   0.9247   0.04287   0.03967   0.0421   0.0056   1.0000
  12.000   0.8969   0.04784   0.04492   0.0435   0.0056   1.0000
  12.250   0.8783   0.05233   0.04960   0.0430   0.0056   1.0000
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