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RAE 5214 AIRFOIL (rae5214-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: RAE 5214 AIRFOIL (rae5214-il)
Reynolds number: 500,000
Max Cl/Cd: 66.58 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rae5214-il-500000.txt
Download as CSV file: xf-rae5214-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAE 5214 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.5427   0.08256   0.08009  -0.0300   1.0000   0.0241
  -9.500  -0.5499   0.07620   0.07376  -0.0343   1.0000   0.0242
  -9.250  -0.5797   0.06477   0.06227  -0.0447   1.0000   0.0242
  -9.000  -0.6138   0.05866   0.05606  -0.0482   1.0000   0.0241
  -8.750  -0.6248   0.05487   0.05216  -0.0488   1.0000   0.0242
  -8.500  -0.7089   0.03327   0.02908  -0.0469   1.0000   0.0168
  -8.250  -0.7032   0.02993   0.02545  -0.0451   1.0000   0.0167
  -8.000  -0.6964   0.02640   0.02147  -0.0430   1.0000   0.0167
  -7.750  -0.6854   0.02367   0.01824  -0.0411   1.0000   0.0170
  -7.500  -0.6703   0.02174   0.01619  -0.0395   1.0000   0.0173
  -7.250  -0.6526   0.02107   0.01553  -0.0382   1.0000   0.0178
  -7.000  -0.6349   0.02010   0.01446  -0.0367   1.0000   0.0183
  -6.750  -0.6058   0.01882   0.01297  -0.0374   0.9987   0.0192
  -6.500  -0.5715   0.01774   0.01155  -0.0388   0.9965   0.0201
  -6.250  -0.5388   0.01642   0.01027  -0.0404   0.9947   0.0211
  -6.000  -0.5055   0.01570   0.00952  -0.0417   0.9921   0.0223
  -5.750  -0.4717   0.01498   0.00865  -0.0431   0.9894   0.0237
  -5.500  -0.4377   0.01431   0.00804  -0.0447   0.9872   0.0254
  -5.250  -0.4014   0.01386   0.00750  -0.0464   0.9854   0.0271
  -5.000  -0.3694   0.01305   0.00676  -0.0476   0.9821   0.0289
  -4.750  -0.3356   0.01254   0.00623  -0.0489   0.9789   0.0306
  -4.500  -0.3005   0.01185   0.00554  -0.0506   0.9766   0.0322
  -4.250  -0.2636   0.01142   0.00514  -0.0526   0.9748   0.0344
  -4.000  -0.2308   0.01097   0.00468  -0.0537   0.9708   0.0365
  -3.750  -0.1962   0.01053   0.00427  -0.0551   0.9674   0.0388
  -3.500  -0.1601   0.01016   0.00390  -0.0568   0.9647   0.0419
  -3.250  -0.1239   0.00980   0.00357  -0.0585   0.9624   0.0462
  -3.000  -0.0946   0.00946   0.00326  -0.0587   0.9559   0.0536
  -2.750  -0.0628   0.00868   0.00284  -0.0598   0.9514   0.1267
  -2.500  -0.0367   0.00718   0.00241  -0.0605   0.9455   0.4135
  -2.250  -0.0089   0.00674   0.00238  -0.0604   0.9384   0.5357
  -2.000   0.0197   0.00664   0.00235  -0.0601   0.9295   0.5747
  -1.750   0.0478   0.00659   0.00228  -0.0595   0.9184   0.5981
  -1.500   0.0739   0.00657   0.00225  -0.0586   0.9048   0.6156
  -1.250   0.1004   0.00661   0.00228  -0.0577   0.8911   0.6357
  -1.000   0.1269   0.00670   0.00235  -0.0569   0.8778   0.6549
  -0.750   0.1534   0.00677   0.00242  -0.0560   0.8645   0.6698
  -0.500   0.1801   0.00679   0.00239  -0.0553   0.8490   0.6786
  -0.250   0.2069   0.00679   0.00234  -0.0546   0.8309   0.6834
   0.000   0.2341   0.00680   0.00230  -0.0541   0.8142   0.6881
   0.250   0.2618   0.00683   0.00226  -0.0538   0.7984   0.6925
   0.500   0.2888   0.00682   0.00223  -0.0533   0.7795   0.6967
   0.750   0.3156   0.00687   0.00221  -0.0527   0.7565   0.7010
   1.000   0.3424   0.00694   0.00220  -0.0522   0.7282   0.7057
   1.250   0.3684   0.00708   0.00218  -0.0515   0.6885   0.7102
   1.500   0.3925   0.00731   0.00218  -0.0504   0.6203   0.7144
   1.750   0.4130   0.00796   0.00229  -0.0489   0.4905   0.7189
   2.000   0.4333   0.00887   0.00253  -0.0477   0.3370   0.7236
   2.250   0.4558   0.00964   0.00278  -0.0469   0.2234   0.7281
   2.500   0.4809   0.01001   0.00298  -0.0464   0.1805   0.7326
   2.750   0.5069   0.01031   0.00317  -0.0461   0.1566   0.7374
   3.000   0.5334   0.01058   0.00336  -0.0457   0.1409   0.7425
   3.250   0.5599   0.01080   0.00353  -0.0454   0.1299   0.7475
   3.500   0.5864   0.01099   0.00373  -0.0450   0.1217   0.7527
   3.750   0.6123   0.01130   0.00398  -0.0446   0.1135   0.7583
   4.000   0.6393   0.01145   0.00415  -0.0444   0.1077   0.7640
   4.250   0.6646   0.01175   0.00442  -0.0439   0.1004   0.7702
   4.500   0.6915   0.01190   0.00461  -0.0436   0.0957   0.7773
   4.750   0.7169   0.01219   0.00489  -0.0431   0.0901   0.7841
   5.000   0.7430   0.01240   0.00516  -0.0427   0.0858   0.7922
   5.250   0.7689   0.01260   0.00538  -0.0423   0.0814   0.8014
   5.500   0.7937   0.01293   0.00574  -0.0417   0.0771   0.8128
   5.750   0.8194   0.01305   0.00595  -0.0412   0.0732   0.8269
   6.000   0.8430   0.01335   0.00627  -0.0404   0.0689   0.8469
   6.250   0.8655   0.01332   0.00646  -0.0391   0.0654   0.8911
   6.500   0.8960   0.01360   0.00677  -0.0397   0.0608   1.0000
   6.750   0.9228   0.01386   0.00704  -0.0396   0.0570   1.0000
   7.000   0.9477   0.01433   0.00748  -0.0391   0.0531   1.0000
   7.250   0.9733   0.01470   0.00784  -0.0388   0.0497   1.0000
   7.500   0.9971   0.01528   0.00841  -0.0382   0.0467   1.0000
   7.750   1.0219   0.01571   0.00886  -0.0377   0.0442   1.0000
   8.000   1.0445   0.01643   0.00953  -0.0369   0.0420   1.0000
   8.250   1.0689   0.01688   0.01005  -0.0364   0.0403   1.0000
   8.500   1.0925   0.01742   0.01061  -0.0357   0.0388   1.0000
   8.750   1.1146   0.01813   0.01131  -0.0349   0.0376   1.0000
   9.000   1.1363   0.01894   0.01216  -0.0341   0.0366   1.0000
   9.250   1.1590   0.01957   0.01288  -0.0333   0.0357   1.0000
   9.500   1.1811   0.02025   0.01362  -0.0325   0.0349   1.0000
   9.750   1.2028   0.02094   0.01435  -0.0317   0.0341   1.0000
  10.000   1.2238   0.02170   0.01512  -0.0308   0.0334   1.0000
  10.250   1.2422   0.02297   0.01640  -0.0297   0.0326   1.0000
  10.500   1.2627   0.02375   0.01731  -0.0287   0.0322   1.0000
  10.750   1.2823   0.02464   0.01831  -0.0277   0.0317   1.0000
  11.000   1.3010   0.02561   0.01940  -0.0265   0.0312   1.0000
  11.250   1.3188   0.02663   0.02053  -0.0253   0.0308   1.0000
  11.500   1.3357   0.02767   0.02168  -0.0241   0.0303   1.0000
  11.750   1.3517   0.02874   0.02285  -0.0227   0.0300   1.0000
  12.000   1.3665   0.02986   0.02405  -0.0213   0.0296   1.0000
  12.250   1.3800   0.03108   0.02535  -0.0197   0.0294   1.0000
  12.500   1.3908   0.03239   0.02673  -0.0178   0.0291   1.0000
  12.750   1.3984   0.03407   0.02851  -0.0157   0.0288   1.0000
  13.000   1.4010   0.03648   0.03106  -0.0134   0.0285   1.0000
  13.250   1.4015   0.03813   0.03289  -0.0107   0.0284   1.0000
  13.500   1.3994   0.04001   0.03498  -0.0082   0.0283   1.0000
  13.750   1.3951   0.04225   0.03741  -0.0060   0.0282   1.0000
  14.000   1.3881   0.04487   0.04024  -0.0043   0.0281   1.0000
  14.250   1.3786   0.04792   0.04350  -0.0031   0.0280   1.0000
  14.500   1.3658   0.05160   0.04739  -0.0027   0.0280   1.0000
  14.750   1.3500   0.05593   0.05194  -0.0031   0.0279   1.0000
  15.000   1.3301   0.06127   0.05750  -0.0047   0.0279   1.0000
  15.250   1.3066   0.06777   0.06422  -0.0078   0.0279   1.0000
  15.500   1.2768   0.07623   0.07292  -0.0130   0.0280   1.0000
  15.750   1.2404   0.08726   0.08418  -0.0207   0.0281   1.0000
  16.000   1.1821   0.10498   0.10219  -0.0337   0.0283   1.0000
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