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NACA-0009 9.0% smoothed (n0009sm-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA-0009 9.0% smoothed (n0009sm-il)
Reynolds number: 200,000
Max Cl/Cd: 42.19 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n0009sm-il-200000-n5.txt
Download as CSV file: xf-n0009sm-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.250  -0.8683   0.08119   0.07741  -0.0163   1.0000   0.0108
 -13.000  -0.8961   0.07048   0.06658  -0.0237   1.0000   0.0104
 -12.750  -0.9234   0.06071   0.05661  -0.0312   1.0000   0.0104
 -12.500  -0.9444   0.05377   0.04947  -0.0361   1.0000   0.0103
 -12.250  -0.9627   0.04855   0.04402  -0.0386   1.0000   0.0103
 -12.000  -0.9796   0.04441   0.03962  -0.0389   1.0000   0.0104
 -11.750  -0.9928   0.04121   0.03618  -0.0374   1.0000   0.0106
 -11.500  -1.0025   0.03860   0.03331  -0.0348   1.0000   0.0107
 -11.250  -1.0091   0.03638   0.03083  -0.0315   1.0000   0.0110
 -11.000  -1.0133   0.03413   0.02839  -0.0283   1.0000   0.0113
 -10.750  -1.0086   0.03249   0.02660  -0.0259   1.0000   0.0119
 -10.500  -0.9987   0.03124   0.02522  -0.0240   1.0000   0.0126
 -10.250  -0.9853   0.03030   0.02410  -0.0223   1.0000   0.0138
 -10.000  -0.9732   0.02889   0.02245  -0.0204   1.0000   0.0152
  -9.750  -0.9609   0.02734   0.02065  -0.0184   1.0000   0.0164
  -9.500  -0.9475   0.02615   0.01937  -0.0166   1.0000   0.0178
  -9.250  -0.9308   0.02528   0.01838  -0.0150   1.0000   0.0193
  -9.000  -0.9129   0.02446   0.01739  -0.0136   1.0000   0.0217
  -8.750  -0.8963   0.02334   0.01610  -0.0119   1.0000   0.0239
  -8.500  -0.8783   0.02264   0.01534  -0.0105   1.0000   0.0262
  -8.250  -0.8593   0.02190   0.01449  -0.0091   1.0000   0.0286
  -8.000  -0.8392   0.02128   0.01364  -0.0077   1.0000   0.0314
  -7.750  -0.8212   0.02038   0.01269  -0.0062   1.0000   0.0342
  -7.500  -0.8009   0.01989   0.01214  -0.0050   1.0000   0.0372
  -7.250  -0.7803   0.01935   0.01149  -0.0037   1.0000   0.0406
  -7.000  -0.7593   0.01881   0.01079  -0.0024   1.0000   0.0428
  -6.750  -0.7413   0.01792   0.00991  -0.0008   1.0000   0.0461
  -6.500  -0.7209   0.01738   0.00932   0.0005   1.0000   0.0493
  -6.250  -0.7005   0.01682   0.00865   0.0019   1.0000   0.0522
  -6.000  -0.6798   0.01632   0.00804   0.0033   1.0000   0.0547
  -5.750  -0.6608   0.01566   0.00740   0.0048   1.0000   0.0589
  -5.500  -0.6401   0.01522   0.00692   0.0062   1.0000   0.0635
  -5.250  -0.6191   0.01482   0.00643   0.0075   1.0000   0.0677
  -5.000  -0.5992   0.01429   0.00593   0.0090   1.0000   0.0733
  -4.750  -0.5782   0.01392   0.00549   0.0103   1.0000   0.0802
  -4.500  -0.5577   0.01349   0.00511   0.0116   1.0000   0.0902
  -4.250  -0.5371   0.01309   0.00476   0.0130   1.0000   0.1048
  -4.000  -0.5168   0.01267   0.00444   0.0143   1.0000   0.1273
  -3.750  -0.4966   0.01226   0.00417   0.0157   1.0000   0.1592
  -3.500  -0.4767   0.01185   0.00391   0.0170   1.0000   0.2008
  -3.250  -0.4571   0.01143   0.00372   0.0184   1.0000   0.2512
  -3.000  -0.4375   0.01107   0.00358   0.0199   1.0000   0.3042
  -2.750  -0.4035   0.01071   0.00345   0.0182   0.9952   0.3638
  -2.500  -0.3702   0.01033   0.00332   0.0168   0.9893   0.4283
  -2.250  -0.3362   0.01000   0.00324   0.0153   0.9832   0.4910
  -2.000  -0.3050   0.00964   0.00317   0.0146   0.9760   0.5579
  -1.750  -0.2727   0.00927   0.00313   0.0137   0.9693   0.6371
  -1.500  -0.2427   0.00898   0.00310   0.0136   0.9608   0.6983
  -1.250  -0.2066   0.00878   0.00307   0.0122   0.9547   0.7463
  -1.000  -0.1741   0.00861   0.00306   0.0116   0.9452   0.7892
  -0.750  -0.1346   0.00852   0.00306   0.0096   0.9377   0.8287
  -0.500  -0.0920   0.00849   0.00311   0.0069   0.9290   0.8619
  -0.250  -0.0473   0.00849   0.00314   0.0037   0.9187   0.8872
   0.000   0.0000   0.00850   0.00316   0.0000   0.9055   0.9055
   0.250   0.0472   0.00850   0.00315  -0.0037   0.8874   0.9187
   0.500   0.0920   0.00849   0.00311  -0.0069   0.8619   0.9290
   0.750   0.1347   0.00852   0.00306  -0.0096   0.8286   0.9378
   1.000   0.1741   0.00861   0.00306  -0.0116   0.7890   0.9452
   1.250   0.2066   0.00878   0.00307  -0.0122   0.7458   0.9547
   1.500   0.2427   0.00898   0.00310  -0.0136   0.6986   0.9608
   1.750   0.2727   0.00926   0.00313  -0.0137   0.6371   0.9693
   2.000   0.3049   0.00964   0.00316  -0.0145   0.5577   0.9760
   2.250   0.3361   0.01000   0.00324  -0.0153   0.4906   0.9833
   2.500   0.3703   0.01033   0.00332  -0.0168   0.4285   0.9894
   2.750   0.4037   0.01070   0.00345  -0.0182   0.3647   0.9953
   3.000   0.4374   0.01107   0.00358  -0.0198   0.3041   1.0000
   3.250   0.4570   0.01143   0.00372  -0.0184   0.2518   1.0000
   3.500   0.4766   0.01185   0.00391  -0.0170   0.2001   1.0000
   3.750   0.4965   0.01226   0.00416  -0.0156   0.1592   1.0000
   4.000   0.5167   0.01267   0.00444  -0.0143   0.1270   1.0000
   4.250   0.5370   0.01309   0.00476  -0.0129   0.1048   1.0000
   4.500   0.5576   0.01349   0.00511  -0.0116   0.0900   1.0000
   4.750   0.5781   0.01392   0.00549  -0.0103   0.0799   1.0000
   5.000   0.5991   0.01429   0.00591  -0.0089   0.0732   1.0000
   5.250   0.6189   0.01482   0.00643  -0.0075   0.0677   1.0000
   5.500   0.6400   0.01522   0.00692  -0.0061   0.0636   1.0000
   5.750   0.6607   0.01566   0.00740  -0.0048   0.0589   1.0000
   6.000   0.6797   0.01633   0.00804  -0.0033   0.0547   1.0000
   6.250   0.7004   0.01682   0.00865  -0.0019   0.0523   1.0000
   6.500   0.7208   0.01738   0.00932  -0.0005   0.0493   1.0000
   6.750   0.7412   0.01792   0.00992   0.0008   0.0461   1.0000
   7.000   0.7593   0.01882   0.01080   0.0024   0.0428   1.0000
   7.250   0.7803   0.01935   0.01149   0.0037   0.0405   1.0000
   7.500   0.8009   0.01989   0.01215   0.0050   0.0373   1.0000
   7.750   0.8212   0.02038   0.01269   0.0062   0.0342   1.0000
   8.000   0.8391   0.02130   0.01367   0.0078   0.0314   1.0000
   8.250   0.8593   0.02192   0.01450   0.0091   0.0287   1.0000
   8.500   0.8784   0.02263   0.01534   0.0105   0.0262   1.0000
   8.750   0.8963   0.02337   0.01613   0.0119   0.0239   1.0000
   9.000   0.9134   0.02439   0.01732   0.0135   0.0216   1.0000
   9.250   0.9310   0.02527   0.01837   0.0150   0.0193   1.0000
   9.500   0.9476   0.02616   0.01938   0.0166   0.0178   1.0000
   9.750   0.9610   0.02736   0.02066   0.0184   0.0164   1.0000
  10.000   0.9737   0.02884   0.02240   0.0203   0.0151   1.0000
  10.250   0.9860   0.03024   0.02403   0.0222   0.0138   1.0000
  10.500   0.9974   0.03150   0.02550   0.0241   0.0128   1.0000
  10.750   1.0093   0.03244   0.02654   0.0258   0.0118   1.0000
  11.000   1.0136   0.03415   0.02841   0.0282   0.0113   1.0000
  11.250   1.0101   0.03635   0.03079   0.0314   0.0110   1.0000
  11.500   1.0030   0.03862   0.03333   0.0347   0.0107   1.0000
  11.750   0.9925   0.04132   0.03630   0.0374   0.0105   1.0000
  12.000   0.9801   0.04445   0.03968   0.0388   0.0103   1.0000
  12.250   0.9643   0.04846   0.04392   0.0385   0.0103   1.0000
  12.500   0.9459   0.05369   0.04938   0.0360   0.0103   1.0000
  12.750   0.9253   0.06053   0.05641   0.0312   0.0104   1.0000
  13.000   0.9002   0.06982   0.06590   0.0240   0.0105   1.0000
  13.250   0.8717   0.08063   0.07683   0.0165   0.0108   1.0000
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