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RAE6-9CK AIRFOIL (rae69ck-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: RAE6-9CK AIRFOIL (rae69ck-il)
Reynolds number: 500,000
Max Cl/Cd: 70.64 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rae69ck-il-500000.txt
Download as CSV file: xf-rae69ck-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.750  -0.6745   0.09877   0.09631  -0.0380   1.0000   0.0153
 -13.500  -0.7207   0.08290   0.08032  -0.0480   1.0000   0.0142
 -13.250  -0.7656   0.07097   0.06819  -0.0555   1.0000   0.0139
 -13.000  -0.7981   0.06297   0.05999  -0.0597   1.0000   0.0136
 -12.750  -0.8409   0.05445   0.05115  -0.0630   1.0000   0.0133
 -12.500  -0.8719   0.04828   0.04468  -0.0641   1.0000   0.0131
 -12.250  -0.8853   0.04472   0.04093  -0.0640   1.0000   0.0131
 -12.000  -0.9028   0.04087   0.03683  -0.0631   1.0000   0.0131
 -11.750  -0.9053   0.03908   0.03496  -0.0619   1.0000   0.0134
 -11.500  -0.9109   0.03725   0.03300  -0.0599   1.0000   0.0136
 -11.250  -0.9205   0.03550   0.03112  -0.0568   1.0000   0.0138
 -11.000  -0.9298   0.03440   0.02992  -0.0526   1.0000   0.0140
 -10.750  -0.9333   0.03281   0.02818  -0.0492   1.0000   0.0143
 -10.500  -0.9348   0.03110   0.02626  -0.0458   1.0000   0.0146
 -10.250  -0.9334   0.02953   0.02450  -0.0425   1.0000   0.0149
 -10.000  -0.9291   0.02797   0.02275  -0.0396   1.0000   0.0151
  -9.750  -0.9219   0.02678   0.02140  -0.0369   1.0000   0.0154
  -9.500  -0.9127   0.02579   0.02025  -0.0344   1.0000   0.0157
  -9.250  -0.9051   0.02375   0.01802  -0.0319   1.0000   0.0161
  -9.000  -0.8855   0.02196   0.01614  -0.0316   0.9990   0.0168
  -8.750  -0.8553   0.02092   0.01505  -0.0333   0.9968   0.0176
  -8.500  -0.8234   0.02006   0.01411  -0.0351   0.9949   0.0187
  -8.250  -0.7926   0.01931   0.01329  -0.0365   0.9926   0.0200
  -8.000  -0.7609   0.01885   0.01273  -0.0379   0.9899   0.0210
  -7.750  -0.7344   0.01705   0.01086  -0.0391   0.9870   0.0227
  -7.500  -0.7014   0.01634   0.01012  -0.0410   0.9850   0.0246
  -7.250  -0.6670   0.01575   0.00947  -0.0431   0.9835   0.0266
  -7.000  -0.6407   0.01488   0.00854  -0.0436   0.9791   0.0290
  -6.750  -0.6097   0.01420   0.00786  -0.0450   0.9759   0.0325
  -6.500  -0.5758   0.01376   0.00734  -0.0468   0.9737   0.0358
  -6.250  -0.5418   0.01297   0.00657  -0.0488   0.9719   0.0430
  -6.000  -0.5062   0.01238   0.00599  -0.0511   0.9706   0.0526
  -5.750  -0.4801   0.01187   0.00551  -0.0512   0.9655   0.0667
  -5.500  -0.4484   0.01127   0.00504  -0.0526   0.9624   0.0963
  -5.250  -0.4152   0.01044   0.00452  -0.0547   0.9602   0.1618
  -5.000  -0.3832   0.00890   0.00373  -0.0573   0.9584   0.3318
  -4.750  -0.3486   0.00817   0.00349  -0.0595   0.9570   0.4668
  -4.500  -0.3185   0.00807   0.00341  -0.0601   0.9530   0.4989
  -4.250  -0.2872   0.00801   0.00333  -0.0608   0.9490   0.5181
  -4.000  -0.2532   0.00795   0.00323  -0.0621   0.9462   0.5327
  -3.750  -0.2183   0.00792   0.00315  -0.0636   0.9439   0.5455
  -3.500  -0.1835   0.00787   0.00311  -0.0651   0.9418   0.5564
  -3.250  -0.1577   0.00785   0.00307  -0.0646   0.9353   0.5652
  -3.000  -0.1258   0.00786   0.00302  -0.0654   0.9313   0.5752
  -2.750  -0.0935   0.00787   0.00307  -0.0662   0.9281   0.5872
  -2.500  -0.0661   0.00787   0.00307  -0.0661   0.9222   0.5948
  -2.250  -0.0363   0.00780   0.00298  -0.0665   0.9170   0.5984
  -2.000  -0.0048   0.00773   0.00286  -0.0672   0.9131   0.6017
  -1.750   0.0227   0.00770   0.00279  -0.0672   0.9065   0.6051
  -1.500   0.0520   0.00760   0.00270  -0.0675   0.9011   0.6081
  -1.250   0.0816   0.00755   0.00265  -0.0678   0.8961   0.6112
  -1.000   0.1092   0.00752   0.00262  -0.0678   0.8894   0.6145
  -0.750   0.1390   0.00749   0.00255  -0.0681   0.8842   0.6181
  -0.500   0.1667   0.00746   0.00253  -0.0681   0.8774   0.6215
  -0.250   0.1953   0.00742   0.00251  -0.0682   0.8713   0.6248
   0.000   0.2236   0.00741   0.00251  -0.0683   0.8648   0.6284
   0.250   0.2517   0.00739   0.00249  -0.0683   0.8571   0.6322
   0.500   0.2797   0.00738   0.00246  -0.0683   0.8491   0.6359
   0.750   0.3076   0.00733   0.00245  -0.0682   0.8402   0.6394
   1.000   0.3345   0.00731   0.00246  -0.0678   0.8292   0.6435
   1.250   0.3619   0.00731   0.00244  -0.0676   0.8174   0.6478
   1.500   0.3882   0.00727   0.00240  -0.0670   0.8004   0.6517
   1.750   0.4138   0.00726   0.00235  -0.0663   0.7780   0.6555
   2.000   0.4400   0.00729   0.00237  -0.0658   0.7592   0.6600
   2.250   0.4665   0.00734   0.00240  -0.0654   0.7405   0.6649
   2.500   0.4922   0.00738   0.00245  -0.0648   0.7186   0.6691
   2.750   0.5173   0.00748   0.00251  -0.0641   0.6900   0.6739
   3.000   0.5411   0.00766   0.00257  -0.0632   0.6481   0.6791
   3.250   0.5615   0.00799   0.00269  -0.0616   0.5753   0.6836
   3.500   0.5734   0.00897   0.00300  -0.0586   0.4227   0.6886
   3.750   0.5871   0.01012   0.00346  -0.0564   0.2693   0.6944
   4.000   0.6036   0.01110   0.00392  -0.0547   0.1488   0.6995
   4.250   0.6235   0.01185   0.00434  -0.0535   0.0823   0.7055
   4.500   0.6464   0.01233   0.00475  -0.0526   0.0605   0.7115
   4.750   0.6694   0.01277   0.00520  -0.0518   0.0499   0.7174
   5.000   0.6933   0.01318   0.00560  -0.0511   0.0431   0.7243
   5.250   0.7158   0.01365   0.00616  -0.0501   0.0387   0.7306
   5.500   0.7396   0.01404   0.00660  -0.0495   0.0352   0.7383
   5.750   0.7581   0.01492   0.00754  -0.0478   0.0312   0.7452
   6.000   0.7827   0.01521   0.00789  -0.0473   0.0295   0.7534
   6.250   0.8053   0.01565   0.00842  -0.0464   0.0274   0.7609
   6.500   0.8275   0.01620   0.00901  -0.0455   0.0257   0.7698
   6.750   0.8439   0.01762   0.01054  -0.0436   0.0237   0.7784
   7.000   0.8676   0.01794   0.01097  -0.0429   0.0227   0.7881
   7.250   0.8903   0.01849   0.01160  -0.0421   0.0214   0.7989
   7.500   0.9120   0.01911   0.01233  -0.0411   0.0204   0.8098
   7.750   0.9333   0.01979   0.01310  -0.0401   0.0194   0.8215
   8.000   0.9532   0.02122   0.01464  -0.0390   0.0184   0.8344
   8.250   0.9744   0.02312   0.01676  -0.0380   0.0178   0.8487
   8.500   0.9944   0.02397   0.01783  -0.0366   0.0173   0.8671
   8.750   1.0122   0.02491   0.01901  -0.0348   0.0166   0.8913
   9.000   1.0272   0.02558   0.01993  -0.0325   0.0159   0.9467
   9.250   1.0503   0.02670   0.02118  -0.0323   0.0152   1.0000
   9.500   1.0688   0.02812   0.02275  -0.0313   0.0148   1.0000
   9.750   1.0858   0.02937   0.02410  -0.0302   0.0144   1.0000
  10.000   1.0997   0.03136   0.02624  -0.0287   0.0140   1.0000
  10.250   1.1057   0.03472   0.02990  -0.0264   0.0137   1.0000
  10.500   1.1015   0.03891   0.03449  -0.0230   0.0136   1.0000
  10.750   1.0888   0.04285   0.03879  -0.0186   0.0135   1.0000
  11.000   1.0792   0.04545   0.04162  -0.0146   0.0135   1.0000
  11.250   1.0652   0.04842   0.04482  -0.0108   0.0136   1.0000
  11.500   1.0526   0.05126   0.04785  -0.0079   0.0136   1.0000
  11.750   1.0257   0.05582   0.05267  -0.0053   0.0136   1.0000
  12.000   1.0166   0.05864   0.05563  -0.0043   0.0136   1.0000
  12.250   0.9917   0.06372   0.06092  -0.0042   0.0136   1.0000
  12.500   0.9760   0.06819   0.06557  -0.0052   0.0138   1.0000
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