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RAE 5214 AIRFOIL (rae5214-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: RAE 5214 AIRFOIL (rae5214-il)
Reynolds number: 100,000
Max Cl/Cd: 40.25 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rae5214-il-100000.txt
Download as CSV file: xf-rae5214-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4945   0.09542   0.09015  -0.0200   1.0000   0.1275
  -8.750  -0.5004   0.09192   0.08673  -0.0224   1.0000   0.1337
  -8.500  -0.5591   0.08628   0.08125  -0.0344   1.0000   0.1364
  -8.250  -0.5007   0.08449   0.07941  -0.0240   1.0000   0.1427
  -8.000  -0.5123   0.08089   0.07590  -0.0263   1.0000   0.1496
  -7.250  -0.5677   0.06730   0.06233  -0.0371   1.0000   0.1706
  -7.000  -0.5336   0.06571   0.06095  -0.0310   1.0000   0.1781
  -6.750  -0.5402   0.06211   0.05736  -0.0318   1.0000   0.1914
  -6.500  -0.5430   0.05907   0.05430  -0.0318   1.0000   0.2070
  -6.000  -0.5331   0.03940   0.03223  -0.0400   1.0000   0.0948
  -5.750  -0.5134   0.03497   0.02723  -0.0386   1.0000   0.0802
  -5.500  -0.4946   0.03179   0.02379  -0.0375   1.0000   0.0769
  -5.250  -0.4741   0.02914   0.02069  -0.0363   1.0000   0.0748
  -5.000  -0.4533   0.02741   0.01872  -0.0351   1.0000   0.0768
  -4.750  -0.4313   0.02568   0.01671  -0.0339   1.0000   0.0779
  -4.500  -0.4087   0.02408   0.01487  -0.0327   1.0000   0.0787
  -4.250  -0.3859   0.02304   0.01355  -0.0314   1.0000   0.0816
  -4.000  -0.3639   0.02147   0.01208  -0.0305   1.0000   0.0851
  -3.750  -0.3415   0.02045   0.01106  -0.0293   1.0000   0.0887
  -3.500  -0.3190   0.01967   0.01021  -0.0282   1.0000   0.0940
  -3.250  -0.2973   0.01861   0.00938  -0.0271   1.0000   0.1003
  -3.000  -0.2751   0.01784   0.00865  -0.0261   1.0000   0.1085
  -2.750  -0.2528   0.01704   0.00800  -0.0253   1.0000   0.1248
  -2.500  -0.2289   0.01418   0.00700  -0.0261   1.0000   0.4273
  -2.250  -0.2191   0.01476   0.00823  -0.0208   1.0000   0.6596
  -2.000  -0.2050   0.01518   0.00868  -0.0172   1.0000   0.7002
  -1.750  -0.1934   0.01553   0.00910  -0.0130   1.0000   0.7374
  -1.500  -0.1854   0.01578   0.00945  -0.0079   1.0000   0.7751
  -1.250  -0.1801   0.01589   0.00964  -0.0024   1.0000   0.8116
  -1.000  -0.1759   0.01582   0.00965   0.0032   1.0000   0.8436
  -0.750  -0.1673   0.01568   0.00953   0.0073   1.0000   0.8686
  -0.500  -0.1510   0.01557   0.00939   0.0092   1.0000   0.8860
  -0.250  -0.1295   0.01553   0.00930   0.0096   1.0000   0.8994
   0.000  -0.1072   0.01552   0.00926   0.0099   1.0000   0.9138
   0.250  -0.0660   0.01581   0.00953   0.0065   0.9932   0.9278
   0.500  -0.0154   0.01622   0.00992   0.0013   0.9850   0.9421
   0.750   0.0435   0.01661   0.01031  -0.0055   0.9744   0.9560
   1.000   0.1109   0.01683   0.01053  -0.0133   0.9562   0.9673
   1.250   0.1939   0.01672   0.01043  -0.0226   0.9327   0.9694
   1.500   0.2662   0.01608   0.00985  -0.0292   0.9072   0.9719
   1.750   0.3323   0.01544   0.00930  -0.0351   0.8897   0.9754
   2.000   0.3915   0.01470   0.00865  -0.0393   0.8698   0.9805
   2.250   0.4423   0.01395   0.00799  -0.0419   0.8415   0.9884
   2.500   0.4855   0.01323   0.00732  -0.0431   0.7988   1.0000
   2.750   0.5013   0.01281   0.00683  -0.0397   0.7424   1.0000
   3.000   0.5144   0.01278   0.00613  -0.0352   0.5671   1.0000
   3.250   0.5186   0.01478   0.00641  -0.0313   0.3124   1.0000
   3.500   0.5400   0.01600   0.00706  -0.0308   0.2568   1.0000
   3.750   0.5654   0.01699   0.00773  -0.0309   0.2298   1.0000
   4.000   0.5923   0.01797   0.00845  -0.0311   0.2111   1.0000
   4.250   0.6203   0.01886   0.00923  -0.0313   0.1960   1.0000
   4.500   0.6485   0.01984   0.01014  -0.0316   0.1835   1.0000
   4.750   0.6767   0.02101   0.01114  -0.0318   0.1729   1.0000
   5.000   0.7044   0.02193   0.01209  -0.0318   0.1627   1.0000
   5.250   0.7321   0.02319   0.01333  -0.0319   0.1537   1.0000
   5.500   0.7589   0.02423   0.01432  -0.0319   0.1447   1.0000
   5.750   0.7852   0.02554   0.01577  -0.0316   0.1365   1.0000
   6.000   0.8112   0.02668   0.01683  -0.0315   0.1288   1.0000
   6.250   0.8358   0.02816   0.01858  -0.0309   0.1216   1.0000
   6.500   0.8610   0.02941   0.01979  -0.0307   0.1153   1.0000
   6.750   0.8836   0.03136   0.02207  -0.0299   0.1097   1.0000
   7.000   0.9066   0.03305   0.02397  -0.0292   0.1047   1.0000
   7.250   0.9301   0.03527   0.02604  -0.0292   0.1005   1.0000
   7.500   0.9463   0.03770   0.02917  -0.0275   0.0971   1.0000
   7.750   0.9617   0.04082   0.03277  -0.0261   0.0951   1.0000
   8.000   0.9755   0.04405   0.03639  -0.0248   0.0935   1.0000
   8.250   0.9903   0.04678   0.03933  -0.0237   0.0916   1.0000
   8.500   1.0135   0.04909   0.04141  -0.0240   0.0890   1.0000
   8.750   1.0189   0.05341   0.04615  -0.0224   0.0885   1.0000
   9.000   1.0252   0.05768   0.05079  -0.0211   0.0890   1.0000
   9.250   0.9675   0.06937   0.06361  -0.0181   0.0986   1.0000
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