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RAE 104 AIRFOIL (rae104-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: RAE 104 AIRFOIL (rae104-il)
Reynolds number: 200,000
Max Cl/Cd: 36.66 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rae104-il-200000-n5.txt
Download as CSV file: xf-rae104-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.6610   0.08810   0.08449  -0.0245   1.0000   0.0137
 -11.000  -0.6859   0.07511   0.07149  -0.0339   1.0000   0.0133
 -10.750  -0.7166   0.06623   0.06250  -0.0392   1.0000   0.0129
 -10.500  -0.7423   0.06042   0.05655  -0.0408   1.0000   0.0128
 -10.250  -0.7679   0.05555   0.05149  -0.0399   1.0000   0.0126
 -10.000  -0.7895   0.05176   0.04750  -0.0371   1.0000   0.0126
  -9.750  -0.8077   0.04840   0.04392  -0.0330   1.0000   0.0126
  -9.500  -0.8200   0.04467   0.03988  -0.0294   1.0000   0.0127
  -9.250  -0.8276   0.04097   0.03582  -0.0258   1.0000   0.0127
  -9.000  -0.8296   0.03761   0.03209  -0.0224   1.0000   0.0129
  -8.750  -0.8267   0.03462   0.02871  -0.0193   1.0000   0.0131
  -8.500  -0.8198   0.03196   0.02564  -0.0165   1.0000   0.0133
  -8.250  -0.8095   0.02963   0.02296  -0.0139   1.0000   0.0138
  -8.000  -0.7965   0.02756   0.02056  -0.0116   1.0000   0.0143
  -7.750  -0.7812   0.02580   0.01851  -0.0096   1.0000   0.0148
  -7.500  -0.7645   0.02442   0.01688  -0.0077   1.0000   0.0155
  -7.250  -0.7491   0.02292   0.01525  -0.0058   1.0000   0.0167
  -7.000  -0.7333   0.02209   0.01437  -0.0040   1.0000   0.0180
  -6.750  -0.7174   0.02114   0.01334  -0.0020   1.0000   0.0189
  -6.500  -0.7026   0.02019   0.01226   0.0003   1.0000   0.0200
  -6.250  -0.6817   0.01921   0.01116   0.0013   0.9982   0.0213
  -6.000  -0.6509   0.01829   0.01012   0.0002   0.9929   0.0230
  -5.750  -0.6223   0.01726   0.00908  -0.0007   0.9869   0.0264
  -5.500  -0.5915   0.01652   0.00825  -0.0018   0.9816   0.0299
  -5.250  -0.5625   0.01575   0.00737  -0.0025   0.9748   0.0335
  -5.000  -0.5303   0.01512   0.00672  -0.0039   0.9703   0.0416
  -4.750  -0.5019   0.01449   0.00609  -0.0044   0.9630   0.0513
  -4.500  -0.4710   0.01390   0.00554  -0.0055   0.9576   0.0708
  -4.250  -0.4432   0.01327   0.00505  -0.0060   0.9509   0.1071
  -4.000  -0.4165   0.01247   0.00460  -0.0065   0.9443   0.1824
  -3.750  -0.3935   0.01154   0.00417  -0.0063   0.9370   0.2990
  -3.500  -0.3745   0.01045   0.00378  -0.0052   0.9293   0.4572
  -3.250  -0.3573   0.00975   0.00379  -0.0029   0.9210   0.6144
  -3.000  -0.3302   0.00964   0.00379  -0.0025   0.9152   0.6825
  -2.750  -0.3032   0.00962   0.00377  -0.0021   0.9092   0.7174
  -2.500  -0.2763   0.00961   0.00376  -0.0016   0.9032   0.7432
  -2.250  -0.2469   0.00962   0.00374  -0.0017   0.8989   0.7644
  -2.000  -0.2216   0.00965   0.00375  -0.0009   0.8922   0.7822
  -1.750  -0.1937   0.00967   0.00374  -0.0007   0.8870   0.7968
  -1.500  -0.1657   0.00968   0.00373  -0.0005   0.8819   0.8083
  -1.250  -0.1388   0.00969   0.00371  -0.0002   0.8762   0.8178
  -1.000  -0.1109   0.00968   0.00365  -0.0002   0.8715   0.8265
  -0.750  -0.0830   0.00969   0.00365  -0.0001   0.8660   0.8327
  -0.500  -0.0560   0.00968   0.00363   0.0001   0.8606   0.8395
  -0.250  -0.0269   0.00967   0.00359  -0.0002   0.8563   0.8447
   0.000   0.0000   0.00968   0.00362   0.0000   0.8502   0.8502
   0.250   0.0269   0.00967   0.00359   0.0002   0.8447   0.8563
   0.500   0.0560   0.00968   0.00363  -0.0001   0.8395   0.8606
   0.750   0.0830   0.00969   0.00365   0.0001   0.8326   0.8660
   1.000   0.1109   0.00968   0.00365   0.0002   0.8265   0.8715
   1.250   0.1388   0.00969   0.00371   0.0002   0.8178   0.8762
   1.500   0.1657   0.00968   0.00373   0.0005   0.8082   0.8819
   1.750   0.1937   0.00967   0.00373   0.0007   0.7969   0.8869
   2.000   0.2216   0.00965   0.00375   0.0009   0.7823   0.8922
   2.250   0.2469   0.00962   0.00374   0.0017   0.7644   0.8989
   2.500   0.2763   0.00961   0.00376   0.0016   0.7431   0.9032
   2.750   0.3032   0.00962   0.00377   0.0021   0.7172   0.9092
   3.000   0.3302   0.00964   0.00378   0.0025   0.6824   0.9152
   3.250   0.3574   0.00975   0.00380   0.0029   0.6154   0.9210
   3.500   0.3745   0.01045   0.00378   0.0052   0.4576   0.9293
   3.750   0.3936   0.01153   0.00417   0.0063   0.3002   0.9370
   4.000   0.4166   0.01247   0.00460   0.0065   0.1834   0.9443
   4.250   0.4431   0.01328   0.00505   0.0060   0.1071   0.9509
   4.500   0.4710   0.01390   0.00554   0.0055   0.0709   0.9576
   4.750   0.5019   0.01449   0.00609   0.0044   0.0514   0.9630
   5.000   0.5302   0.01512   0.00672   0.0039   0.0418   0.9703
   5.250   0.5627   0.01573   0.00736   0.0025   0.0339   0.9748
   5.500   0.5915   0.01651   0.00825   0.0018   0.0300   0.9815
   5.750   0.6223   0.01725   0.00908   0.0007   0.0265   0.9868
   6.000   0.6510   0.01827   0.01010  -0.0002   0.0230   0.9929
   6.250   0.6817   0.01923   0.01118  -0.0012   0.0213   0.9982
   6.500   0.7026   0.02019   0.01226  -0.0003   0.0200   1.0000
   6.750   0.7175   0.02114   0.01333   0.0020   0.0189   1.0000
   7.000   0.7333   0.02207   0.01436   0.0040   0.0179   1.0000
   7.250   0.7490   0.02289   0.01520   0.0058   0.0166   1.0000
   7.500   0.7645   0.02442   0.01688   0.0077   0.0156   1.0000
   7.750   0.7813   0.02577   0.01848   0.0096   0.0148   1.0000
   8.000   0.7966   0.02755   0.02054   0.0116   0.0143   1.0000
   8.250   0.8096   0.02962   0.02294   0.0139   0.0137   1.0000
   8.500   0.8199   0.03195   0.02563   0.0165   0.0134   1.0000
   8.750   0.8268   0.03459   0.02867   0.0193   0.0130   1.0000
   9.000   0.8297   0.03757   0.03204   0.0224   0.0128   1.0000
   9.250   0.8279   0.04092   0.03577   0.0258   0.0127   1.0000
   9.500   0.8207   0.04458   0.03978   0.0294   0.0127   1.0000
   9.750   0.8072   0.04852   0.04404   0.0331   0.0127   1.0000
  10.000   0.7886   0.05192   0.04766   0.0371   0.0127   1.0000
  10.250   0.7652   0.05600   0.05195   0.0400   0.0128   1.0000
  10.500   0.7419   0.06054   0.05667   0.0407   0.0129   1.0000
  10.750   0.7150   0.06660   0.06289   0.0390   0.0130   1.0000
  11.000   0.6876   0.07481   0.07118   0.0341   0.0133   1.0000
  11.250   0.6625   0.08783   0.08422   0.0245   0.0138   1.0000
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