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RAE6-9CK AIRFOIL (rae69ck-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: RAE6-9CK AIRFOIL (rae69ck-il)
Reynolds number: 100,000
Max Cl/Cd: 37.2 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rae69ck-il-100000.txt
Download as CSV file: xf-rae69ck-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAE6-9CK 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  -0.4490   0.09853   0.09362  -0.0362   1.0000   0.1700
 -10.500  -0.5973   0.06491   0.05992  -0.0585   1.0000   0.0811
 -10.250  -0.6171   0.05952   0.05451  -0.0589   1.0000   0.0789
 -10.000  -0.6511   0.05456   0.04947  -0.0585   1.0000   0.0760
  -9.750  -0.7465   0.06409   0.05868  -0.0537   1.0000   0.0796
  -9.500  -0.7942   0.05950   0.05341  -0.0493   1.0000   0.0694
  -9.250  -0.7919   0.05471   0.04858  -0.0478   1.0000   0.0672
  -9.000  -0.7962   0.05092   0.04456  -0.0454   1.0000   0.0653
  -8.750  -0.7987   0.04754   0.04087  -0.0428   1.0000   0.0646
  -8.500  -0.7972   0.04452   0.03751  -0.0402   1.0000   0.0652
  -8.250  -0.7920   0.04155   0.03417  -0.0378   1.0000   0.0655
  -8.000  -0.7833   0.03856   0.03078  -0.0356   1.0000   0.0654
  -7.750  -0.7709   0.03578   0.02759  -0.0336   1.0000   0.0655
  -7.500  -0.7560   0.03336   0.02480  -0.0317   1.0000   0.0667
  -7.250  -0.7399   0.03175   0.02277  -0.0298   1.0000   0.0694
  -7.000  -0.7218   0.02932   0.02028  -0.0285   1.0000   0.0730
  -6.750  -0.7027   0.02771   0.01860  -0.0271   1.0000   0.0768
  -6.500  -0.6831   0.02639   0.01710  -0.0255   1.0000   0.0818
  -6.250  -0.6649   0.02487   0.01565  -0.0241   1.0000   0.0888
  -6.000  -0.6459   0.02380   0.01448  -0.0225   1.0000   0.0964
  -5.750  -0.6290   0.02252   0.01338  -0.0209   1.0000   0.1079
  -5.500  -0.6123   0.02138   0.01235  -0.0193   1.0000   0.1239
  -5.250  -0.5962   0.02002   0.01125  -0.0180   1.0000   0.1521
  -5.000  -0.5825   0.01658   0.00940  -0.0185   1.0000   0.3411
  -4.750  -0.5689   0.01736   0.01086  -0.0145   1.0000   0.5572
  -4.500  -0.5527   0.01833   0.01178  -0.0111   1.0000   0.5933
  -4.250  -0.5365   0.01914   0.01253  -0.0079   1.0000   0.6184
  -4.000  -0.5211   0.01987   0.01322  -0.0045   1.0000   0.6374
  -3.750  -0.5061   0.02051   0.01381  -0.0011   1.0000   0.6539
  -3.500  -0.4910   0.02102   0.01427   0.0020   1.0000   0.6692
  -3.250  -0.4763   0.02146   0.01467   0.0052   1.0000   0.6841
  -3.000  -0.4648   0.02205   0.01526   0.0094   1.0000   0.7008
  -2.750  -0.4550   0.02262   0.01583   0.0140   1.0000   0.7191
  -2.500  -0.4433   0.02294   0.01611   0.0178   1.0000   0.7356
  -2.250  -0.4263   0.02285   0.01595   0.0195   1.0000   0.7448
  -2.000  -0.4035   0.02256   0.01553   0.0192   1.0000   0.7506
  -1.750  -0.3794   0.02224   0.01510   0.0184   1.0000   0.7559
  -1.500  -0.3596   0.02208   0.01486   0.0191   1.0000   0.7604
  -1.250  -0.3359   0.02188   0.01457   0.0185   1.0000   0.7658
  -1.000  -0.3116   0.02171   0.01431   0.0178   0.9999   0.7708
  -0.750  -0.2756   0.02196   0.01450   0.0153   0.9944   0.7753
  -0.500  -0.2394   0.02207   0.01454   0.0123   0.9885   0.7805
   0.000  -0.1703   0.02241   0.01481   0.0076   0.9765   0.7906
   0.250  -0.1306   0.02270   0.01506   0.0041   0.9708   0.7961
   0.500  -0.1009   0.02275   0.01511   0.0027   0.9637   0.8012
   0.750  -0.0645   0.02303   0.01540   0.0003   0.9575   0.8069
   1.000  -0.0328   0.02314   0.01551  -0.0016   0.9499   0.8135
   1.250   0.0028   0.02339   0.01582  -0.0037   0.9431   0.8186
   1.500   0.0320   0.02351   0.01598  -0.0049   0.9347   0.8254
   1.750   0.0712   0.02376   0.01631  -0.0076   0.9279   0.8318
   2.000   0.0978   0.02385   0.01647  -0.0082   0.9183   0.8390
   2.250   0.1367   0.02406   0.01677  -0.0108   0.9108   0.8457
   2.500   0.1672   0.02414   0.01695  -0.0118   0.9007   0.8537
   2.750   0.1973   0.02421   0.01714  -0.0126   0.8901   0.8618
   3.000   0.2380   0.02424   0.01732  -0.0151   0.8804   0.8708
   3.250   0.2779   0.02408   0.01733  -0.0170   0.8694   0.8790
   3.500   0.3144   0.02383   0.01724  -0.0182   0.8559   0.8887
   3.750   0.3656   0.02298   0.01663  -0.0208   0.8404   0.8978
   4.000   0.4396   0.02052   0.01446  -0.0247   0.8142   0.9037
   4.250   0.4992   0.01829   0.01249  -0.0263   0.7878   0.9110
   4.500   0.5435   0.01662   0.01102  -0.0260   0.7531   0.9201
   4.750   0.5739   0.01548   0.00997  -0.0238   0.6926   0.9323
   5.000   0.5862   0.01576   0.00889  -0.0182   0.3942   0.9466
   5.250   0.5894   0.01884   0.01019  -0.0153   0.1553   0.9654
   5.500   0.6225   0.02062   0.01164  -0.0173   0.1192   0.9834
   5.750   0.6527   0.02211   0.01297  -0.0187   0.1027   1.0000
   6.000   0.6786   0.02340   0.01420  -0.0193   0.0924   1.0000
   6.250   0.7116   0.02507   0.01592  -0.0207   0.0838   1.0000
   6.500   0.7477   0.02735   0.01809  -0.0228   0.0778   1.0000
   6.750   0.7791   0.02927   0.02031  -0.0236   0.0725   1.0000
   7.000   0.8099   0.03161   0.02294  -0.0242   0.0697   1.0000
   7.250   0.8377   0.03432   0.02599  -0.0243   0.0684   1.0000
   7.500   0.8632   0.03698   0.02876  -0.0246   0.0657   1.0000
   7.750   0.8827   0.04184   0.03387  -0.0244   0.0638   1.0000
   8.000   0.9017   0.04416   0.03662  -0.0229   0.0646   1.0000
   8.250   0.9024   0.04913   0.04270  -0.0185   0.0721   1.0000
  10.000   0.7625   0.09613   0.09200  -0.0160   0.1594   1.0000
  10.250   0.7248   0.10380   0.09955  -0.0244   0.1528   1.0000
  10.500   0.6114   0.10749   0.10359  -0.0212   0.1593   1.0000
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