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NACA 0010-65 (naca001065-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NACA 0010-65 (naca001065-il)
Reynolds number: 200,000
Max Cl/Cd: 40.59 at α=2.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca001065-il-200000.txt
Download as CSV file: xf-naca001065-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 0010-65                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.5137   0.09092   0.08732  -0.0346   1.0000   0.0742
 -10.250  -0.5373   0.08404   0.08049  -0.0384   1.0000   0.0754
 -10.000  -0.5637   0.07680   0.07328  -0.0422   1.0000   0.0753
  -9.750  -0.5907   0.07112   0.06759  -0.0433   1.0000   0.0751
  -9.500  -0.6207   0.06666   0.06309  -0.0418   1.0000   0.0750
  -9.250  -0.6508   0.06331   0.05970  -0.0380   1.0000   0.0749
  -9.000  -0.6812   0.06086   0.05721  -0.0322   1.0000   0.0749
  -8.750  -0.7190   0.05869   0.05486  -0.0252   1.0000   0.0761
  -8.500  -0.7552   0.05764   0.05348  -0.0172   1.0000   0.0771
  -8.250  -0.7712   0.05532   0.05091  -0.0116   1.0000   0.0773
  -8.000  -0.8333   0.05796   0.05306  -0.0052   1.0000   0.0783
  -7.750  -0.8491   0.04562   0.03989   0.0025   1.0000   0.0519
  -7.500  -0.8486   0.04144   0.03544   0.0064   1.0000   0.0512
  -7.250  -0.8453   0.03778   0.03145   0.0103   1.0000   0.0504
  -7.000  -0.8386   0.03444   0.02771   0.0140   1.0000   0.0499
  -6.750  -0.8278   0.03172   0.02457   0.0172   1.0000   0.0502
  -6.500  -0.8134   0.03014   0.02259   0.0200   1.0000   0.0517
  -6.250  -0.7977   0.02860   0.02068   0.0224   1.0000   0.0527
  -6.000  -0.7778   0.02568   0.01747   0.0238   1.0000   0.0537
  -5.750  -0.7568   0.02427   0.01597   0.0248   1.0000   0.0556
  -5.500  -0.7358   0.02343   0.01505   0.0260   1.0000   0.0581
  -5.250  -0.7132   0.02242   0.01389   0.0271   1.0000   0.0599
  -5.000  -0.6901   0.02146   0.01278   0.0281   1.0000   0.0615
  -4.750  -0.6678   0.02083   0.01200   0.0292   1.0000   0.0636
  -4.500  -0.6446   0.01964   0.01076   0.0301   1.0000   0.0662
  -4.250  -0.6230   0.01885   0.01000   0.0311   1.0000   0.0688
  -4.000  -0.6020   0.01825   0.00940   0.0324   1.0000   0.0718
  -3.750  -0.5811   0.01774   0.00884   0.0337   1.0000   0.0753
  -3.500  -0.5613   0.01707   0.00819   0.0351   1.0000   0.0805
  -3.250  -0.5412   0.01660   0.00776   0.0365   1.0000   0.0877
  -3.000  -0.5217   0.01601   0.00724   0.0380   1.0000   0.0996
  -2.750  -0.5024   0.01533   0.00675   0.0395   1.0000   0.1341
  -2.500  -0.4851   0.01435   0.00640   0.0410   1.0000   0.2417
  -2.250  -0.4807   0.01185   0.00620   0.0454   1.0000   0.7024
  -2.000  -0.4423   0.01265   0.00758   0.0457   1.0000   0.9003
  -1.750  -0.3959   0.01375   0.00857   0.0431   1.0000   0.9389
  -1.500  -0.2529   0.01605   0.01063   0.0213   1.0000   0.9712
  -1.250  -0.1723   0.01654   0.01100   0.0105   1.0000   0.9822
  -1.000  -0.0381   0.01675   0.01108  -0.0113   1.0000   1.0000
  -0.750  -0.0285   0.01668   0.01100  -0.0085   1.0000   1.0000
  -0.500  -0.0190   0.01663   0.01094  -0.0057   1.0000   1.0000
  -0.250  -0.0095   0.01660   0.01090  -0.0028   1.0000   1.0000
   0.000   0.0000   0.01659   0.01089   0.0000   1.0000   1.0000
   0.250   0.0095   0.01660   0.01090   0.0028   1.0000   1.0000
   0.500   0.0190   0.01663   0.01094   0.0057   1.0000   1.0000
   0.750   0.0285   0.01668   0.01100   0.0085   1.0000   1.0000
   1.000   0.0381   0.01675   0.01108   0.0113   1.0000   1.0000
   1.250   0.1722   0.01654   0.01100  -0.0105   0.9823   1.0000
   1.500   0.2526   0.01605   0.01063  -0.0213   0.9712   1.0000
   1.750   0.3959   0.01374   0.00857  -0.0431   0.9389   1.0000
   2.000   0.4422   0.01265   0.00758  -0.0457   0.9004   1.0000
   2.250   0.4806   0.01184   0.00621  -0.0454   0.7056   1.0000
   2.500   0.4850   0.01435   0.00640  -0.0410   0.2415   1.0000
   2.750   0.5024   0.01533   0.00675  -0.0395   0.1346   1.0000
   3.000   0.5216   0.01601   0.00723  -0.0380   0.0996   1.0000
   3.250   0.5411   0.01660   0.00775  -0.0365   0.0878   1.0000
   3.500   0.5612   0.01707   0.00819  -0.0351   0.0805   1.0000
   3.750   0.5810   0.01774   0.00883  -0.0337   0.0753   1.0000
   4.000   0.6019   0.01825   0.00940  -0.0324   0.0717   1.0000
   4.250   0.6229   0.01884   0.01000  -0.0311   0.0688   1.0000
   4.500   0.6445   0.01963   0.01076  -0.0300   0.0662   1.0000
   4.750   0.6677   0.02083   0.01199  -0.0292   0.0636   1.0000
   5.000   0.6900   0.02146   0.01278  -0.0281   0.0616   1.0000
   5.250   0.7131   0.02242   0.01388  -0.0271   0.0599   1.0000
   5.500   0.7357   0.02343   0.01504  -0.0260   0.0581   1.0000
   5.750   0.7567   0.02426   0.01596  -0.0248   0.0556   1.0000
   6.000   0.7777   0.02566   0.01745  -0.0237   0.0538   1.0000
   6.250   0.7977   0.02858   0.02066  -0.0224   0.0527   1.0000
   6.500   0.8133   0.03016   0.02261  -0.0199   0.0517   1.0000
   6.750   0.8277   0.03172   0.02456  -0.0172   0.0502   1.0000
   7.000   0.8386   0.03443   0.02770  -0.0140   0.0499   1.0000
   7.250   0.8453   0.03777   0.03143  -0.0103   0.0505   1.0000
   7.500   0.8486   0.04142   0.03542  -0.0063   0.0511   1.0000
   7.750   0.7658   0.04405   0.03985   0.0087   0.0808   1.0000
   8.000   0.7739   0.04673   0.04246   0.0107   0.0791   1.0000
   8.500   0.7833   0.06400   0.05993   0.0186   0.0724   1.0000
   8.750   0.7701   0.06682   0.06287   0.0229   0.0706   1.0000
   9.000   0.7568   0.06951   0.06564   0.0269   0.0693   1.0000
   9.250   0.7431   0.07213   0.06831   0.0308   0.0683   1.0000
   9.500   0.7256   0.07451   0.07071   0.0352   0.0677   1.0000
   9.750   0.7056   0.07700   0.07322   0.0391   0.0672   1.0000
  10.000   0.6929   0.07980   0.07603   0.0415   0.0666   1.0000
  10.250   0.7292   0.08703   0.08307   0.0398   0.0642   1.0000
  10.500   0.7026   0.08959   0.08568   0.0435   0.0642   1.0000
  10.750   0.6771   0.09314   0.08929   0.0446   0.0641   1.0000
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