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NACA 0010-34 (naca001034-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NACA 0010-34 (naca001034-il)
Reynolds number: 500,000
Max Cl/Cd: 46.49 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca001034-il-500000.txt
Download as CSV file: xf-naca001034-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 0010-34                                    
  
 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  -0.6495   0.08696   0.08477  -0.0216   1.0000   0.0149
 -10.000  -0.6651   0.07735   0.07513  -0.0305   1.0000   0.0142
  -9.750  -0.6848   0.07091   0.06860  -0.0348   1.0000   0.0138
  -9.500  -0.7038   0.06625   0.06384  -0.0357   1.0000   0.0138
  -9.250  -0.7216   0.06262   0.06011  -0.0339   1.0000   0.0138
  -9.000  -0.7338   0.05911   0.05646  -0.0316   1.0000   0.0141
  -8.750  -0.7407   0.05556   0.05274  -0.0292   1.0000   0.0147
  -8.500  -0.7282   0.05446   0.05138  -0.0265   1.0000   0.0167
  -8.250  -0.7297   0.05240   0.04911  -0.0230   1.0000   0.0169
  -8.000  -0.7324   0.04985   0.04634  -0.0193   1.0000   0.0170
  -7.750  -0.7342   0.04727   0.04354  -0.0154   1.0000   0.0170
  -5.750  -0.6847   0.02116   0.01526   0.0116   0.9991   0.0143
  -5.500  -0.6549   0.01858   0.01237   0.0116   0.9978   0.0140
  -5.250  -0.6236   0.01702   0.01065   0.0109   0.9964   0.0147
  -5.000  -0.5919   0.01580   0.00933   0.0100   0.9949   0.0155
  -4.750  -0.5583   0.01549   0.00892   0.0086   0.9930   0.0169
  -4.500  -0.5318   0.01374   0.00707   0.0086   0.9904   0.0180
  -4.250  -0.5026   0.01259   0.00583   0.0080   0.9876   0.0202
  -4.000  -0.4693   0.01200   0.00519   0.0065   0.9854   0.0231
  -3.750  -0.4342   0.01160   0.00473   0.0047   0.9836   0.0271
  -3.500  -0.4022   0.01088   0.00396   0.0036   0.9812   0.0443
  -3.250  -0.3838   0.00883   0.00328   0.0041   0.9762   0.3526
  -3.000  -0.3575   0.00769   0.00300   0.0036   0.9729   0.5575
  -2.750  -0.3260   0.00714   0.00288   0.0026   0.9707   0.6698
  -2.500  -0.2927   0.00681   0.00288   0.0015   0.9691   0.7588
  -2.250  -0.2669   0.00669   0.00286   0.0021   0.9631   0.8013
  -2.000  -0.2343   0.00662   0.00283   0.0012   0.9597   0.8291
  -1.750  -0.1999   0.00655   0.00275  -0.0001   0.9569   0.8450
  -1.500  -0.1701   0.00650   0.00269  -0.0004   0.9519   0.8582
  -1.250  -0.1407   0.00644   0.00264  -0.0006   0.9463   0.8702
  -1.000  -0.1088   0.00638   0.00258  -0.0013   0.9423   0.8801
  -0.750  -0.0830   0.00636   0.00256  -0.0007   0.9348   0.8901
  -0.500  -0.0544   0.00632   0.00251  -0.0007   0.9293   0.8996
  -0.250  -0.0273   0.00632   0.00252  -0.0003   0.9219   0.9070
   0.000   0.0000   0.00630   0.00248   0.0000   0.9153   0.9153
   0.250   0.0274   0.00632   0.00252   0.0003   0.9070   0.9219
   0.500   0.0544   0.00632   0.00251   0.0007   0.8996   0.9293
   0.750   0.0830   0.00636   0.00256   0.0007   0.8901   0.9348
   1.000   0.1088   0.00638   0.00258   0.0013   0.8802   0.9423
   1.250   0.1407   0.00644   0.00264   0.0006   0.8702   0.9463
   1.500   0.1701   0.00650   0.00269   0.0004   0.8581   0.9519
   1.750   0.1999   0.00655   0.00275   0.0001   0.8450   0.9569
   2.000   0.2343   0.00662   0.00283  -0.0012   0.8291   0.9597
   2.250   0.2669   0.00669   0.00286  -0.0021   0.8012   0.9631
   2.500   0.2927   0.00681   0.00286  -0.0015   0.7589   0.9691
   2.750   0.3260   0.00714   0.00288  -0.0026   0.6702   0.9707
   3.000   0.3575   0.00769   0.00300  -0.0036   0.5577   0.9729
   3.250   0.3837   0.00884   0.00328  -0.0041   0.3519   0.9762
   3.500   0.4021   0.01088   0.00396  -0.0036   0.0442   0.9812
   3.750   0.4341   0.01161   0.00474  -0.0046   0.0271   0.9836
   4.000   0.4693   0.01200   0.00519  -0.0065   0.0231   0.9854
   4.250   0.5026   0.01258   0.00583  -0.0080   0.0203   0.9876
   4.500   0.5319   0.01373   0.00706  -0.0086   0.0180   0.9904
   4.750   0.5580   0.01556   0.00899  -0.0085   0.0170   0.9930
   5.000   0.5919   0.01580   0.00933  -0.0100   0.0155   0.9949
   5.250   0.6237   0.01702   0.01065  -0.0109   0.0147   0.9964
   5.500   0.6548   0.01858   0.01237  -0.0116   0.0141   0.9978
   5.750   0.6846   0.02115   0.01525  -0.0116   0.0143   0.9991
   6.000   0.6661   0.01439   0.00947  -0.0026   0.0242   0.9962
   6.250   0.6932   0.01659   0.01198  -0.0027   0.0225   0.9983
   6.500   0.7148   0.01902   0.01469  -0.0023   0.0210   1.0000
   6.750   0.7214   0.02076   0.01662   0.0009   0.0201   1.0000
   7.000   0.7274   0.02239   0.01834   0.0038   0.0192   1.0000
   7.250   0.7325   0.02436   0.02035   0.0066   0.0184   1.0000
   7.500   0.7182   0.02993   0.02616   0.0114   0.0174   1.0000
   7.750   0.7342   0.04726   0.04354   0.0155   0.0170   1.0000
   8.000   0.7324   0.04984   0.04633   0.0193   0.0170   1.0000
   8.250   0.7297   0.05239   0.04909   0.0230   0.0169   1.0000
   8.500   0.7280   0.05451   0.05143   0.0264   0.0167   1.0000
   8.750   0.7410   0.05556   0.05274   0.0291   0.0147   1.0000
   9.000   0.7341   0.05912   0.05647   0.0315   0.0141   1.0000
   9.250   0.7219   0.06264   0.06013   0.0338   0.0138   1.0000
   9.500   0.7042   0.06628   0.06387   0.0356   0.0137   1.0000
   9.750   0.6852   0.07096   0.06866   0.0347   0.0138   1.0000
  10.000   0.6656   0.07744   0.07522   0.0303   0.0142   1.0000
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