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RAE 103 AIRFOIL (rae103-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: RAE 103 AIRFOIL (rae103-il)
Reynolds number: 200,000
Max Cl/Cd: 39.19 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rae103-il-200000-n5.txt
Download as CSV file: xf-rae103-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAE 103 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.7014   0.08641   0.08283  -0.0177   1.0000   0.0134
 -11.250  -0.7328   0.07253   0.06887  -0.0276   1.0000   0.0130
 -11.000  -0.7602   0.06456   0.06075  -0.0329   1.0000   0.0129
 -10.750  -0.7827   0.05906   0.05509  -0.0352   1.0000   0.0128
 -10.500  -0.8058   0.05439   0.05022  -0.0353   1.0000   0.0127
 -10.250  -0.8266   0.05054   0.04617  -0.0334   1.0000   0.0127
 -10.000  -0.8454   0.04708   0.04246  -0.0299   1.0000   0.0127
  -9.750  -0.8571   0.04333   0.03837  -0.0268   1.0000   0.0128
  -9.500  -0.8625   0.03968   0.03433  -0.0238   1.0000   0.0129
  -9.250  -0.8620   0.03634   0.03057  -0.0211   1.0000   0.0131
  -9.000  -0.8563   0.03333   0.02713  -0.0186   1.0000   0.0134
  -8.750  -0.8458   0.03081   0.02420  -0.0165   1.0000   0.0138
  -8.500  -0.8318   0.02870   0.02174  -0.0146   1.0000   0.0142
  -8.250  -0.8170   0.02660   0.01938  -0.0130   1.0000   0.0149
  -8.000  -0.7999   0.02540   0.01810  -0.0117   1.0000   0.0157
  -7.750  -0.7815   0.02454   0.01712  -0.0105   1.0000   0.0168
  -7.500  -0.7626   0.02334   0.01576  -0.0091   1.0000   0.0179
  -7.250  -0.7436   0.02205   0.01430  -0.0077   1.0000   0.0188
  -7.000  -0.7247   0.02091   0.01301  -0.0061   1.0000   0.0197
  -6.750  -0.7064   0.01987   0.01186  -0.0045   1.0000   0.0206
  -6.500  -0.6902   0.01878   0.01076  -0.0027   1.0000   0.0225
  -6.250  -0.6715   0.01815   0.01007  -0.0012   1.0000   0.0246
  -6.000  -0.6535   0.01746   0.00931   0.0004   1.0000   0.0268
  -5.750  -0.6357   0.01681   0.00856   0.0022   1.0000   0.0285
  -5.500  -0.6206   0.01597   0.00774   0.0043   1.0000   0.0316
  -5.250  -0.6030   0.01550   0.00723   0.0061   1.0000   0.0361
  -5.000  -0.5762   0.01485   0.00655   0.0058   0.9961   0.0421
  -4.750  -0.5434   0.01428   0.00592   0.0044   0.9889   0.0519
  -4.500  -0.5106   0.01366   0.00538   0.0028   0.9821   0.0711
  -4.250  -0.4797   0.01301   0.00489   0.0016   0.9738   0.1064
  -4.000  -0.4495   0.01222   0.00441   0.0004   0.9657   0.1775
  -3.750  -0.4213   0.01122   0.00395  -0.0005   0.9567   0.2979
  -3.500  -0.3982   0.01016   0.00360  -0.0003   0.9453   0.4551
  -3.250  -0.3713   0.00971   0.00356  -0.0001   0.9353   0.5702
  -3.000  -0.3396   0.00954   0.00346  -0.0008   0.9270   0.6205
  -2.750  -0.3100   0.00944   0.00338  -0.0010   0.9160   0.6536
  -2.500  -0.2802   0.00936   0.00332  -0.0012   0.9055   0.6804
  -2.250  -0.2503   0.00929   0.00326  -0.0014   0.8955   0.7026
  -2.000  -0.2212   0.00925   0.00318  -0.0014   0.8852   0.7222
  -1.750  -0.1933   0.00921   0.00313  -0.0013   0.8745   0.7386
  -1.500  -0.1652   0.00917   0.00307  -0.0011   0.8642   0.7520
  -1.250  -0.1370   0.00914   0.00300  -0.0010   0.8545   0.7631
  -1.000  -0.1096   0.00912   0.00295  -0.0008   0.8442   0.7732
  -0.750  -0.0824   0.00910   0.00290  -0.0006   0.8349   0.7831
  -0.250  -0.0274   0.00907   0.00285  -0.0002   0.8169   0.8000
   0.000   0.0000   0.00907   0.00285   0.0000   0.8086   0.8086
   0.250   0.0275   0.00907   0.00285   0.0002   0.7999   0.8170
   0.750   0.0824   0.00910   0.00290   0.0006   0.7831   0.8349
   1.000   0.1097   0.00912   0.00295   0.0008   0.7732   0.8442
   1.250   0.1370   0.00914   0.00300   0.0010   0.7632   0.8544
   1.500   0.1652   0.00917   0.00307   0.0011   0.7519   0.8642
   1.750   0.1933   0.00921   0.00313   0.0013   0.7386   0.8745
   2.000   0.2213   0.00925   0.00318   0.0014   0.7223   0.8852
   2.250   0.2503   0.00929   0.00326   0.0014   0.7027   0.8955
   2.500   0.2802   0.00936   0.00332   0.0012   0.6802   0.9055
   2.750   0.3100   0.00944   0.00338   0.0010   0.6537   0.9160
   3.250   0.3713   0.00971   0.00356   0.0001   0.5700   0.9353
   3.500   0.3982   0.01016   0.00360   0.0003   0.4555   0.9453
   3.750   0.4212   0.01122   0.00395   0.0006   0.2974   0.9567
   4.000   0.4494   0.01223   0.00441  -0.0004   0.1765   0.9657
   4.250   0.4797   0.01302   0.00489  -0.0016   0.1059   0.9738
   4.500   0.5105   0.01366   0.00538  -0.0028   0.0711   0.9821
   4.750   0.5434   0.01428   0.00592  -0.0043   0.0521   0.9889
   5.000   0.5761   0.01486   0.00653  -0.0058   0.0421   0.9960
   5.250   0.6031   0.01550   0.00723  -0.0061   0.0359   1.0000
   5.500   0.6206   0.01597   0.00773  -0.0043   0.0316   1.0000
   5.750   0.6357   0.01681   0.00856  -0.0022   0.0285   1.0000
   6.000   0.6535   0.01746   0.00931  -0.0004   0.0268   1.0000
   6.250   0.6715   0.01816   0.01009   0.0013   0.0247   1.0000
   6.500   0.6902   0.01877   0.01075   0.0027   0.0224   1.0000
   6.750   0.7065   0.01985   0.01184   0.0045   0.0206   1.0000
   7.000   0.7247   0.02091   0.01302   0.0061   0.0197   1.0000
   7.250   0.7436   0.02205   0.01430   0.0077   0.0189   1.0000
   7.500   0.7626   0.02336   0.01578   0.0091   0.0180   1.0000
   7.750   0.7815   0.02448   0.01705   0.0105   0.0167   1.0000
   8.000   0.7999   0.02554   0.01826   0.0117   0.0158   1.0000
   8.250   0.8170   0.02659   0.01936   0.0130   0.0148   1.0000
   8.500   0.8318   0.02874   0.02177   0.0146   0.0143   1.0000
   8.750   0.8459   0.03080   0.02419   0.0165   0.0139   1.0000
   9.000   0.8564   0.03334   0.02714   0.0186   0.0135   1.0000
   9.250   0.8620   0.03636   0.03059   0.0211   0.0131   1.0000
   9.500   0.8624   0.03974   0.03439   0.0238   0.0129   1.0000
   9.750   0.8561   0.04350   0.03856   0.0269   0.0127   1.0000
  10.000   0.8451   0.04716   0.04254   0.0299   0.0127   1.0000
  10.250   0.8271   0.05053   0.04615   0.0333   0.0127   1.0000
  10.500   0.8052   0.05452   0.05036   0.0353   0.0127   1.0000
  10.750   0.7846   0.05889   0.05491   0.0351   0.0128   1.0000
  11.000   0.7597   0.06476   0.06095   0.0327   0.0129   1.0000
  11.250   0.7355   0.07209   0.06841   0.0279   0.0131   1.0000
  11.500   0.7050   0.08527   0.08169   0.0182   0.0134   1.0000
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