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NACA-0009 9.0% smoothed (n0009sm-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA-0009 9.0% smoothed (n0009sm-il)
Reynolds number: 100,000
Max Cl/Cd: 33.45 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n0009sm-il-100000-n5.txt
Download as CSV file: xf-n0009sm-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA-0009 9.0% smoothed                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.7125   0.09267   0.08756  -0.0119   1.0000   0.0297
 -11.250  -0.7440   0.07951   0.07448  -0.0205   1.0000   0.0288
 -11.000  -0.7809   0.06808   0.06296  -0.0297   1.0000   0.0275
 -10.750  -0.8254   0.05924   0.05387  -0.0344   1.0000   0.0259
 -10.500  -0.8507   0.05479   0.04921  -0.0336   1.0000   0.0257
 -10.250  -0.8652   0.05197   0.04621  -0.0310   1.0000   0.0263
 -10.000  -0.8747   0.04890   0.04288  -0.0287   1.0000   0.0272
  -9.750  -0.8815   0.04554   0.03916  -0.0263   1.0000   0.0283
  -9.500  -0.8849   0.04194   0.03511  -0.0236   1.0000   0.0295
  -9.250  -0.8832   0.03854   0.03117  -0.0210   1.0000   0.0310
  -9.000  -0.8757   0.03585   0.02809  -0.0188   1.0000   0.0329
  -8.750  -0.8615   0.03486   0.02708  -0.0174   1.0000   0.0355
  -8.500  -0.8476   0.03329   0.02519  -0.0156   1.0000   0.0387
  -8.250  -0.8326   0.03132   0.02277  -0.0137   1.0000   0.0418
  -8.000  -0.8166   0.02976   0.02108  -0.0122   1.0000   0.0453
  -7.750  -0.7986   0.02856   0.01975  -0.0109   1.0000   0.0486
  -7.500  -0.7796   0.02721   0.01813  -0.0094   1.0000   0.0524
  -7.250  -0.7603   0.02589   0.01658  -0.0080   1.0000   0.0564
  -7.000  -0.7408   0.02473   0.01541  -0.0067   1.0000   0.0598
  -6.750  -0.7206   0.02363   0.01418  -0.0054   1.0000   0.0633
  -6.500  -0.6996   0.02278   0.01305  -0.0040   1.0000   0.0678
  -6.250  -0.6809   0.02173   0.01208  -0.0026   1.0000   0.0727
  -6.000  -0.6609   0.02089   0.01115  -0.0012   1.0000   0.0775
  -5.750  -0.6414   0.02004   0.01022   0.0004   1.0000   0.0822
  -5.500  -0.6224   0.01926   0.00945   0.0019   1.0000   0.0884
  -5.250  -0.6028   0.01857   0.00875   0.0034   1.0000   0.0974
  -5.000  -0.5831   0.01793   0.00804   0.0049   1.0000   0.1082
  -4.750  -0.5637   0.01724   0.00740   0.0064   1.0000   0.1216
  -4.500  -0.5446   0.01655   0.00683   0.0079   1.0000   0.1423
  -4.250  -0.5255   0.01585   0.00634   0.0094   1.0000   0.1806
  -4.000  -0.5068   0.01517   0.00592   0.0109   1.0000   0.2358
  -3.750  -0.4878   0.01458   0.00556   0.0124   1.0000   0.2942
  -3.500  -0.4689   0.01405   0.00530   0.0140   1.0000   0.3585
  -3.250  -0.4500   0.01359   0.00509   0.0157   1.0000   0.4214
  -3.000  -0.4309   0.01318   0.00493   0.0175   1.0000   0.4836
  -2.750  -0.4117   0.01281   0.00482   0.0193   1.0000   0.5471
  -2.500  -0.3920   0.01248   0.00475   0.0212   1.0000   0.6170
  -2.250  -0.3704   0.01222   0.00477   0.0230   1.0000   0.6883
  -2.000  -0.3453   0.01208   0.00484   0.0241   1.0000   0.7529
  -1.750  -0.3157   0.01206   0.00494   0.0243   1.0000   0.8064
  -1.500  -0.2796   0.01213   0.00504   0.0231   1.0000   0.8537
  -1.250  -0.2360   0.01228   0.00518   0.0203   1.0000   0.8919
  -1.000  -0.1912   0.01243   0.00530   0.0171   1.0000   0.9223
  -0.750  -0.1454   0.01257   0.00537   0.0134   1.0000   0.9457
  -0.500  -0.1009   0.01269   0.00546   0.0099   1.0000   0.9657
  -0.250  -0.0562   0.01279   0.00553   0.0061   1.0000   0.9828
   0.000   0.0000   0.01279   0.00552   0.0000   0.9912   0.9912
   0.250   0.0560   0.01279   0.00553  -0.0061   0.9828   1.0000
   0.500   0.1010   0.01269   0.00546  -0.0099   0.9656   1.0000
   0.750   0.1454   0.01257   0.00537  -0.0134   0.9457   1.0000
   1.000   0.1912   0.01243   0.00529  -0.0171   0.9222   1.0000
   1.250   0.2360   0.01228   0.00518  -0.0203   0.8919   1.0000
   1.500   0.2796   0.01213   0.00504  -0.0231   0.8536   1.0000
   1.750   0.3156   0.01206   0.00494  -0.0243   0.8063   1.0000
   2.000   0.3452   0.01208   0.00484  -0.0241   0.7528   1.0000
   2.250   0.3703   0.01222   0.00477  -0.0229   0.6882   1.0000
   2.500   0.3919   0.01248   0.00475  -0.0212   0.6171   1.0000
   2.750   0.4115   0.01281   0.00481  -0.0193   0.5466   1.0000
   3.000   0.4308   0.01318   0.00492  -0.0175   0.4835   1.0000
   3.250   0.4499   0.01359   0.00508  -0.0157   0.4208   1.0000
   3.500   0.4688   0.01405   0.00529  -0.0140   0.3584   1.0000
   3.750   0.4877   0.01458   0.00556  -0.0124   0.2947   1.0000
   4.000   0.5067   0.01517   0.00592  -0.0109   0.2354   1.0000
   4.250   0.5254   0.01585   0.00633  -0.0094   0.1806   1.0000
   4.500   0.5444   0.01655   0.00682  -0.0079   0.1422   1.0000
   4.750   0.5636   0.01724   0.00739  -0.0064   0.1214   1.0000
   5.000   0.5830   0.01793   0.00804  -0.0048   0.1081   1.0000
   5.250   0.6028   0.01857   0.00874  -0.0034   0.0973   1.0000
   5.500   0.6223   0.01926   0.00945  -0.0019   0.0884   1.0000
   5.750   0.6413   0.02004   0.01022  -0.0003   0.0822   1.0000
   6.000   0.6609   0.02089   0.01115   0.0012   0.0774   1.0000
   6.250   0.6809   0.02174   0.01208   0.0027   0.0727   1.0000
   6.500   0.6996   0.02279   0.01305   0.0041   0.0678   1.0000
   6.750   0.7205   0.02363   0.01418   0.0054   0.0633   1.0000
   7.000   0.7408   0.02473   0.01541   0.0067   0.0598   1.0000
   7.250   0.7603   0.02590   0.01659   0.0080   0.0564   1.0000
   7.500   0.7796   0.02722   0.01813   0.0094   0.0525   1.0000
   7.750   0.7987   0.02857   0.01976   0.0109   0.0487   1.0000
   8.000   0.8166   0.02973   0.02103   0.0122   0.0452   1.0000
   8.250   0.8327   0.03132   0.02276   0.0137   0.0419   1.0000
   8.500   0.8477   0.03329   0.02519   0.0156   0.0387   1.0000
   8.750   0.8616   0.03483   0.02705   0.0173   0.0355   1.0000
   9.000   0.8759   0.03580   0.02803   0.0187   0.0328   1.0000
   9.250   0.8834   0.03854   0.03116   0.0209   0.0310   1.0000
   9.500   0.8850   0.04198   0.03515   0.0236   0.0295   1.0000
   9.750   0.8815   0.04556   0.03919   0.0262   0.0283   1.0000
  10.000   0.8746   0.04899   0.04297   0.0287   0.0273   1.0000
  10.250   0.8654   0.05203   0.04626   0.0310   0.0264   1.0000
  10.500   0.8509   0.05484   0.04925   0.0335   0.0257   1.0000
  10.750   0.8258   0.05927   0.05390   0.0343   0.0258   1.0000
  11.000   0.7829   0.06785   0.06273   0.0297   0.0273   1.0000
  11.250   0.7449   0.07951   0.07449   0.0203   0.0288   1.0000
  11.500   0.7128   0.09289   0.08778   0.0116   0.0297   1.0000
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