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NACA-0009 9.0% smoothed (n0009sm-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NACA-0009 9.0% smoothed (n0009sm-il)
Reynolds number: 200,000
Max Cl/Cd: 45.65 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n0009sm-il-200000.txt
Download as CSV file: xf-n0009sm-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.6705   0.10051   0.09687  -0.0078   1.0000   0.0395
 -11.000  -0.8444   0.05643   0.05235  -0.0377   1.0000   0.0238
 -10.750  -0.8669   0.05254   0.04826  -0.0367   1.0000   0.0238
 -10.500  -0.8878   0.04930   0.04480  -0.0333   1.0000   0.0237
 -10.250  -0.9017   0.04588   0.04116  -0.0304   1.0000   0.0241
 -10.000  -0.9029   0.04358   0.03873  -0.0281   1.0000   0.0249
  -9.750  -0.8815   0.04456   0.03985  -0.0273   1.0000   0.0274
  -9.500  -0.8837   0.04164   0.03661  -0.0246   1.0000   0.0289
  -9.250  -0.8850   0.03833   0.03285  -0.0215   1.0000   0.0303
  -9.000  -0.8811   0.03557   0.02961  -0.0184   1.0000   0.0316
  -8.750  -0.8795   0.03141   0.02493  -0.0152   1.0000   0.0330
  -8.500  -0.8645   0.03018   0.02371  -0.0138   1.0000   0.0359
  -8.250  -0.8480   0.02934   0.02267  -0.0121   1.0000   0.0398
  -8.000  -0.8321   0.02811   0.02102  -0.0097   1.0000   0.0427
  -7.750  -0.8178   0.02512   0.01786  -0.0080   1.0000   0.0462
  -7.500  -0.7988   0.02453   0.01719  -0.0066   1.0000   0.0508
  -7.250  -0.7791   0.02385   0.01622  -0.0049   1.0000   0.0546
  -7.000  -0.7603   0.02185   0.01416  -0.0036   1.0000   0.0590
  -6.750  -0.7396   0.02103   0.01325  -0.0023   1.0000   0.0633
  -6.500  -0.7182   0.02027   0.01226  -0.0009   1.0000   0.0670
  -6.250  -0.6978   0.01882   0.01079   0.0004   1.0000   0.0714
  -6.000  -0.6767   0.01799   0.00994   0.0017   1.0000   0.0756
  -5.750  -0.6552   0.01729   0.00912   0.0031   1.0000   0.0799
  -5.500  -0.6358   0.01626   0.00814   0.0046   1.0000   0.0853
  -5.250  -0.6153   0.01568   0.00753   0.0061   1.0000   0.0920
  -5.000  -0.5963   0.01486   0.00673   0.0078   1.0000   0.0990
  -4.750  -0.5763   0.01429   0.00614   0.0093   1.0000   0.1085
  -4.500  -0.5576   0.01361   0.00555   0.0111   1.0000   0.1227
  -4.250  -0.5393   0.01291   0.00502   0.0128   1.0000   0.1497
  -4.000  -0.5231   0.01198   0.00454   0.0148   1.0000   0.2201
  -3.750  -0.5067   0.01124   0.00425   0.0167   1.0000   0.3124
  -3.500  -0.4890   0.01074   0.00404   0.0185   1.0000   0.3876
  -3.250  -0.4712   0.01032   0.00390   0.0205   1.0000   0.4564
  -3.000  -0.4536   0.00996   0.00382   0.0225   1.0000   0.5217
  -2.750  -0.4358   0.00967   0.00376   0.0246   1.0000   0.5819
  -2.500  -0.4180   0.00941   0.00374   0.0268   1.0000   0.6409
  -2.250  -0.4003   0.00918   0.00375   0.0291   1.0000   0.7016
  -2.000  -0.3815   0.00901   0.00382   0.0313   1.0000   0.7618
  -1.750  -0.3586   0.00893   0.00395   0.0328   1.0000   0.8258
  -1.500  -0.3136   0.00907   0.00426   0.0302   1.0000   0.8990
  -1.250  -0.2544   0.00939   0.00454   0.0243   1.0000   0.9372
  -1.000  -0.1999   0.00965   0.00474   0.0191   1.0000   0.9571
  -0.750  -0.1466   0.00990   0.00492   0.0140   1.0000   0.9716
  -0.500  -0.0922   0.01007   0.00505   0.0085   1.0000   0.9841
  -0.250  -0.0360   0.01017   0.00512   0.0025   1.0000   0.9945
   0.000   0.0000   0.01018   0.00512   0.0000   1.0000   1.0000
   0.250   0.0357   0.01017   0.00512  -0.0024   0.9945   1.0000
   0.500   0.0922   0.01007   0.00505  -0.0085   0.9841   1.0000
   0.750   0.1467   0.00989   0.00492  -0.0140   0.9716   1.0000
   1.000   0.2002   0.00965   0.00474  -0.0191   0.9570   1.0000
   1.250   0.2545   0.00939   0.00454  -0.0243   0.9371   1.0000
   1.500   0.3136   0.00907   0.00425  -0.0302   0.8990   1.0000
   1.750   0.3585   0.00892   0.00394  -0.0328   0.8256   1.0000
   2.000   0.3814   0.00901   0.00381  -0.0313   0.7621   1.0000
   2.250   0.4002   0.00918   0.00375  -0.0291   0.7016   1.0000
   2.500   0.4179   0.00941   0.00374  -0.0268   0.6412   1.0000
   2.750   0.4356   0.00966   0.00376  -0.0246   0.5820   1.0000
   3.000   0.4534   0.00996   0.00382  -0.0225   0.5215   1.0000
   3.250   0.4711   0.01032   0.00390  -0.0205   0.4570   1.0000
   3.500   0.4888   0.01074   0.00403  -0.0185   0.3872   1.0000
   3.750   0.5066   0.01123   0.00425  -0.0167   0.3126   1.0000
   4.000   0.5230   0.01198   0.00454  -0.0147   0.2199   1.0000
   4.250   0.5392   0.01290   0.00502  -0.0128   0.1500   1.0000
   4.500   0.5574   0.01361   0.00555  -0.0110   0.1225   1.0000
   4.750   0.5760   0.01431   0.00615  -0.0093   0.1082   1.0000
   5.000   0.5962   0.01486   0.00673  -0.0077   0.0989   1.0000
   5.250   0.6151   0.01568   0.00753  -0.0060   0.0920   1.0000
   5.500   0.6357   0.01626   0.00814  -0.0046   0.0853   1.0000
   5.750   0.6551   0.01729   0.00912  -0.0031   0.0799   1.0000
   6.000   0.6766   0.01799   0.00994  -0.0017   0.0756   1.0000
   6.250   0.6977   0.01881   0.01079  -0.0003   0.0715   1.0000
   6.500   0.7182   0.02029   0.01228   0.0009   0.0670   1.0000
   6.750   0.7396   0.02104   0.01325   0.0023   0.0633   1.0000
   7.000   0.7602   0.02187   0.01418   0.0036   0.0591   1.0000
   7.250   0.7791   0.02383   0.01620   0.0049   0.0545   1.0000
   7.500   0.7987   0.02456   0.01723   0.0066   0.0509   1.0000
   7.750   0.8178   0.02511   0.01785   0.0080   0.0462   1.0000
   8.000   0.8321   0.02810   0.02103   0.0098   0.0426   1.0000
   8.250   0.8480   0.02931   0.02264   0.0120   0.0398   1.0000
   8.500   0.8646   0.03016   0.02369   0.0138   0.0359   1.0000
   8.750   0.8795   0.03146   0.02498   0.0152   0.0330   1.0000
   9.000   0.8815   0.03543   0.02947   0.0184   0.0314   1.0000
   9.250   0.8856   0.03820   0.03273   0.0214   0.0301   1.0000
   9.500   0.8843   0.04155   0.03652   0.0245   0.0287   1.0000
   9.750   0.8810   0.04469   0.03999   0.0273   0.0274   1.0000
  10.000   0.9059   0.04314   0.03823   0.0278   0.0247   1.0000
  10.250   0.9028   0.04579   0.04105   0.0302   0.0240   1.0000
  10.500   0.8875   0.04935   0.04488   0.0334   0.0239   1.0000
  10.750   0.8670   0.05261   0.04832   0.0365   0.0237   1.0000
  11.000   0.8431   0.05666   0.05261   0.0375   0.0240   1.0000
  11.250   0.6691   0.10213   0.09850   0.0076   0.0455   1.0000
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