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NACA 0008-34 (naca000834-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NACA 0008-34 (naca000834-il)
Reynolds number: 500,000
Max Cl/Cd: 57.23 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca000834-il-500000.txt
Download as CSV file: xf-naca000834-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 0008-34                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.6413   0.10628   0.10403   0.0013   1.0000   0.0098
 -10.000  -0.6477   0.09988   0.09766  -0.0017   1.0000   0.0099
  -9.750  -0.6515   0.09397   0.09177  -0.0051   1.0000   0.0100
  -9.500  -0.6547   0.08767   0.08550  -0.0095   1.0000   0.0101
  -9.250  -0.6553   0.08009   0.07793  -0.0175   1.0000   0.0100
  -9.000  -0.6627   0.07452   0.07229  -0.0219   1.0000   0.0100
  -8.750  -0.6739   0.07013   0.06783  -0.0232   1.0000   0.0100
  -8.500  -0.6858   0.06562   0.06321  -0.0230   1.0000   0.0100
  -8.250  -0.6938   0.06090   0.05835  -0.0226   1.0000   0.0102
  -8.000  -0.6977   0.05651   0.05381  -0.0218   1.0000   0.0104
  -7.750  -0.6973   0.05265   0.04979  -0.0207   1.0000   0.0106
  -7.500  -0.6930   0.04936   0.04634  -0.0194   1.0000   0.0109
  -7.250  -0.6870   0.04623   0.04304  -0.0179   1.0000   0.0113
  -7.000  -0.6796   0.04322   0.03986  -0.0161   1.0000   0.0117
  -6.750  -0.6713   0.04034   0.03679  -0.0139   1.0000   0.0123
  -6.500  -0.6617   0.03753   0.03376  -0.0114   1.0000   0.0131
  -6.250  -0.6504   0.03485   0.03084  -0.0087   1.0000   0.0144
  -6.000  -0.6240   0.03599   0.03174  -0.0065   1.0000   0.0175
  -4.250  -0.5181   0.01625   0.01005   0.0105   1.0000   0.0150
  -4.000  -0.4954   0.01447   0.00810   0.0119   1.0000   0.0144
  -3.750  -0.4737   0.01323   0.00677   0.0134   1.0000   0.0150
  -3.500  -0.4521   0.01243   0.00590   0.0146   1.0000   0.0164
  -3.250  -0.4218   0.01199   0.00540   0.0139   0.9987   0.0178
  -3.000  -0.3906   0.01065   0.00394   0.0130   0.9968   0.0218
  -2.750  -0.3554   0.01017   0.00335   0.0112   0.9948   0.0270
  -2.500  -0.3254   0.00877   0.00263   0.0101   0.9928   0.2093
  -2.250  -0.3015   0.00682   0.00231   0.0096   0.9904   0.6093
  -2.000  -0.2718   0.00623   0.00231   0.0091   0.9871   0.7613
  -1.750  -0.2413   0.00603   0.00246   0.0091   0.9841   0.8612
  -1.500  -0.2066   0.00606   0.00252   0.0079   0.9815   0.8943
  -1.250  -0.1770   0.00608   0.00254   0.0078   0.9758   0.9153
  -1.000  -0.1411   0.00610   0.00253   0.0061   0.9723   0.9273
  -0.750  -0.1025   0.00613   0.00254   0.0039   0.9699   0.9352
  -0.500  -0.0695   0.00614   0.00253   0.0028   0.9650   0.9436
  -0.250  -0.0348   0.00615   0.00253   0.0014   0.9602   0.9498
   0.000   0.0000   0.00614   0.00251   0.0000   0.9560   0.9560
   0.250   0.0348   0.00615   0.00253  -0.0014   0.9498   0.9601
   0.500   0.0695   0.00614   0.00253  -0.0028   0.9436   0.9650
   0.750   0.1025   0.00613   0.00254  -0.0038   0.9352   0.9699
   1.000   0.1410   0.00610   0.00253  -0.0061   0.9273   0.9723
   1.250   0.1770   0.00608   0.00254  -0.0078   0.9155   0.9758
   1.500   0.2065   0.00606   0.00252  -0.0079   0.8941   0.9816
   1.750   0.2412   0.00603   0.00246  -0.0090   0.8612   0.9841
   2.000   0.2718   0.00623   0.00232  -0.0091   0.7623   0.9871
   2.250   0.3014   0.00682   0.00231  -0.0095   0.6087   0.9904
   2.500   0.3254   0.00875   0.00263  -0.0101   0.2121   0.9928
   2.750   0.3554   0.01017   0.00335  -0.0112   0.0271   0.9949
   3.000   0.3907   0.01065   0.00394  -0.0130   0.0218   0.9968
   3.250   0.4218   0.01199   0.00541  -0.0139   0.0178   0.9988
   3.500   0.4520   0.01243   0.00590  -0.0146   0.0164   1.0000
   3.750   0.4736   0.01323   0.00676  -0.0133   0.0150   1.0000
   4.000   0.4953   0.01446   0.00810  -0.0119   0.0144   1.0000
   4.250   0.5180   0.01625   0.01004  -0.0105   0.0150   1.0000
   4.500   0.5380   0.00940   0.00404  -0.0084   0.0276   1.0000
   4.750   0.5567   0.01010   0.00497  -0.0064   0.0257   1.0000
   5.000   0.5735   0.01107   0.00613  -0.0044   0.0225   1.0000
   5.250   0.5883   0.01214   0.00722  -0.0029   0.0199   1.0000
   5.500   0.5970   0.01529   0.01058  -0.0004   0.0184   1.0000
   6.000   0.6009   0.02331   0.01938   0.0074   0.0175   1.0000
   6.250   0.6239   0.02231   0.01861   0.0100   0.0150   1.0000
   6.500   0.6320   0.02493   0.02147   0.0131   0.0135   1.0000
   6.750   0.6377   0.02796   0.02470   0.0159   0.0127   1.0000
   7.000   0.6421   0.03117   0.02810   0.0186   0.0121   1.0000
   7.250   0.6452   0.03456   0.03166   0.0209   0.0116   1.0000
   7.500   0.6468   0.03820   0.03545   0.0229   0.0113   1.0000
   7.750   0.6462   0.04201   0.03939   0.0246   0.0110   1.0000
   8.000   0.6429   0.04598   0.04350   0.0262   0.0109   1.0000
   8.250   0.6359   0.05010   0.04773   0.0275   0.0107   1.0000
   8.500   0.6225   0.05402   0.05175   0.0291   0.0107   1.0000
   8.750   0.6024   0.05848   0.05631   0.0292   0.0108   1.0000
   9.000   0.5774   0.06555   0.06348   0.0248   0.0111   1.0000
   9.250   0.5575   0.07498   0.07291   0.0172   0.0115   1.0000
   9.500   0.5475   0.08123   0.07914   0.0142   0.0115   1.0000
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