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RAE 100 AIRFOIL (rae100-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: RAE 100 AIRFOIL (rae100-il)
Reynolds number: 100,000
Max Cl/Cd: 35.27 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rae100-il-100000.txt
Download as CSV file: xf-rae100-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAE 100 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.8252   0.07540   0.07005  -0.0248   1.0000   0.0730
 -10.500  -0.8306   0.07025   0.06484  -0.0254   1.0000   0.0720
 -10.250  -0.8487   0.06565   0.06014  -0.0251   1.0000   0.0715
 -10.000  -0.8651   0.06098   0.05530  -0.0245   1.0000   0.0709
  -9.750  -0.8778   0.05632   0.05037  -0.0236   1.0000   0.0706
  -9.500  -0.8865   0.05184   0.04550  -0.0223   1.0000   0.0708
  -9.250  -0.8899   0.04769   0.04086  -0.0207   1.0000   0.0715
  -9.000  -0.8875   0.04396   0.03659  -0.0188   1.0000   0.0722
  -8.750  -0.8799   0.04063   0.03271  -0.0170   1.0000   0.0729
  -8.500  -0.8660   0.03669   0.02858  -0.0161   1.0000   0.0748
  -8.250  -0.8467   0.03486   0.02672  -0.0153   1.0000   0.0786
  -8.000  -0.8295   0.03272   0.02417  -0.0139   1.0000   0.0826
  -7.750  -0.8114   0.03048   0.02141  -0.0123   1.0000   0.0857
  -7.500  -0.7896   0.02844   0.01947  -0.0117   1.0000   0.0912
  -7.250  -0.7682   0.02701   0.01770  -0.0105   1.0000   0.0978
  -7.000  -0.7455   0.02517   0.01596  -0.0097   1.0000   0.1047
  -6.750  -0.7232   0.02377   0.01438  -0.0087   1.0000   0.1143
  -6.500  -0.7007   0.02259   0.01315  -0.0076   1.0000   0.1254
  -6.250  -0.6786   0.02138   0.01199  -0.0066   1.0000   0.1397
  -6.000  -0.6572   0.02015   0.01090  -0.0055   1.0000   0.1570
  -5.750  -0.6363   0.01912   0.01001  -0.0043   1.0000   0.1794
  -5.500  -0.6159   0.01813   0.00920  -0.0030   1.0000   0.2084
  -5.250  -0.5959   0.01723   0.00848  -0.0016   1.0000   0.2450
  -5.000  -0.5762   0.01644   0.00793  -0.0002   1.0000   0.2869
  -4.750  -0.5565   0.01577   0.00748   0.0013   1.0000   0.3316
  -4.500  -0.5365   0.01522   0.00713   0.0029   1.0000   0.3764
  -4.250  -0.5164   0.01476   0.00686   0.0045   1.0000   0.4203
  -4.000  -0.4961   0.01437   0.00662   0.0062   1.0000   0.4626
  -3.750  -0.4756   0.01404   0.00641   0.0078   1.0000   0.5044
  -3.500  -0.4551   0.01373   0.00628   0.0096   1.0000   0.5425
  -3.250  -0.4348   0.01347   0.00613   0.0114   1.0000   0.5816
  -3.000  -0.4146   0.01322   0.00603   0.0134   1.0000   0.6177
  -2.750  -0.3948   0.01300   0.00595   0.0154   1.0000   0.6540
  -2.500  -0.3754   0.01281   0.00587   0.0175   1.0000   0.6906
  -2.250  -0.3564   0.01264   0.00585   0.0198   1.0000   0.7254
  -2.000  -0.3378   0.01251   0.00584   0.0222   1.0000   0.7610
  -1.750  -0.3195   0.01242   0.00586   0.0246   1.0000   0.7984
  -1.500  -0.2991   0.01241   0.00595   0.0268   1.0000   0.8363
  -1.250  -0.2736   0.01250   0.00611   0.0279   1.0000   0.8768
  -1.000  -0.2321   0.01273   0.00636   0.0259   1.0000   0.9151
  -0.750  -0.1726   0.01302   0.00661   0.0201   1.0000   0.9459
  -0.500  -0.1033   0.01323   0.00676   0.0121   1.0000   0.9689
  -0.250  -0.0301   0.01326   0.00675   0.0030   1.0000   0.9876
   0.000   0.0000   0.01318   0.00667   0.0000   1.0000   1.0000
   0.250   0.0301   0.01326   0.00675  -0.0030   0.9876   1.0000
   0.500   0.1033   0.01323   0.00676  -0.0121   0.9689   1.0000
   0.750   0.1725   0.01302   0.00661  -0.0201   0.9460   1.0000
   1.000   0.2321   0.01273   0.00636  -0.0259   0.9151   1.0000
   1.250   0.2737   0.01250   0.00611  -0.0279   0.8769   1.0000
   1.500   0.2992   0.01241   0.00595  -0.0268   0.8363   1.0000
   1.750   0.3196   0.01242   0.00586  -0.0246   0.7983   1.0000
   2.000   0.3379   0.01251   0.00584  -0.0222   0.7611   1.0000
   2.250   0.3565   0.01264   0.00585  -0.0198   0.7255   1.0000
   2.500   0.3756   0.01281   0.00587  -0.0175   0.6906   1.0000
   2.750   0.3949   0.01300   0.00595  -0.0154   0.6539   1.0000
   3.000   0.4148   0.01322   0.00603  -0.0134   0.6177   1.0000
   3.250   0.4349   0.01347   0.00613  -0.0115   0.5816   1.0000
   3.500   0.4553   0.01373   0.00628  -0.0097   0.5424   1.0000
   3.750   0.4757   0.01404   0.00641  -0.0079   0.5044   1.0000
   4.000   0.4962   0.01437   0.00662  -0.0062   0.4626   1.0000
   4.250   0.5166   0.01476   0.00686  -0.0046   0.4202   1.0000
   4.500   0.5367   0.01522   0.00714  -0.0029   0.3764   1.0000
   4.750   0.5566   0.01578   0.00748  -0.0014   0.3315   1.0000
   5.000   0.5763   0.01644   0.00793   0.0002   0.2868   1.0000
   5.250   0.5960   0.01723   0.00848   0.0016   0.2450   1.0000
   5.500   0.6160   0.01813   0.00920   0.0030   0.2083   1.0000
   5.750   0.6364   0.01912   0.01001   0.0043   0.1794   1.0000
   6.000   0.6572   0.02015   0.01090   0.0055   0.1569   1.0000
   6.250   0.6787   0.02138   0.01199   0.0066   0.1397   1.0000
   6.500   0.7007   0.02259   0.01314   0.0076   0.1255   1.0000
   6.750   0.7232   0.02376   0.01438   0.0087   0.1142   1.0000
   7.000   0.7454   0.02516   0.01595   0.0097   0.1047   1.0000
   7.250   0.7682   0.02700   0.01769   0.0105   0.0978   1.0000
   7.500   0.7895   0.02845   0.01948   0.0117   0.0912   1.0000
   7.750   0.8113   0.03049   0.02142   0.0123   0.0857   1.0000
   8.000   0.8294   0.03272   0.02418   0.0139   0.0826   1.0000
   8.250   0.8465   0.03489   0.02675   0.0153   0.0787   1.0000
   8.500   0.8657   0.03672   0.02863   0.0162   0.0749   1.0000
   8.750   0.8800   0.04048   0.03256   0.0171   0.0730   1.0000
   9.000   0.8874   0.04395   0.03657   0.0189   0.0722   1.0000
   9.250   0.8902   0.04767   0.04082   0.0207   0.0716   1.0000
   9.500   0.8865   0.05180   0.04545   0.0223   0.0708   1.0000
   9.750   0.8786   0.05629   0.05032   0.0236   0.0708   1.0000
  10.000   0.8658   0.06095   0.05525   0.0245   0.0710   1.0000
  10.250   0.8477   0.06563   0.06013   0.0252   0.0714   1.0000
  10.500   0.8341   0.07016   0.06474   0.0255   0.0722   1.0000
  10.750   0.8251   0.07524   0.06989   0.0248   0.0731   1.0000
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