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NACA 0010-35 (naca001035-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NACA 0010-35 (naca001035-il)
Reynolds number: 500,000
Max Cl/Cd: 36.85 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca001035-il-500000-n5.txt
Download as CSV file: xf-naca001035-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 0010-35                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.5761   0.10140   0.09909  -0.0300   1.0000   0.0040
 -10.500  -0.5833   0.09624   0.09396  -0.0319   1.0000   0.0039
 -10.250  -0.5914   0.09087   0.08862  -0.0343   1.0000   0.0038
 -10.000  -0.6018   0.08490   0.08269  -0.0380   1.0000   0.0038
  -9.750  -0.6181   0.07890   0.07667  -0.0419   1.0000   0.0038
  -9.500  -0.6378   0.07473   0.07247  -0.0418   1.0000   0.0038
  -9.250  -0.6602   0.07164   0.06934  -0.0390   1.0000   0.0038
  -9.000  -0.6847   0.06951   0.06717  -0.0340   1.0000   0.0037
  -8.750  -0.6999   0.06595   0.06352  -0.0313   0.9981   0.0037
  -8.500  -0.7019   0.06076   0.05816  -0.0313   0.9955   0.0036
  -8.250  -0.7025   0.05604   0.05324  -0.0302   0.9927   0.0036
  -8.000  -0.6999   0.05133   0.04830  -0.0288   0.9896   0.0035
  -7.750  -0.6936   0.04660   0.04331  -0.0273   0.9874   0.0034
  -7.500  -0.6858   0.04211   0.03853  -0.0252   0.9849   0.0034
  -7.250  -0.6781   0.03791   0.03401  -0.0224   0.9813   0.0033
  -7.000  -0.6656   0.03352   0.02925  -0.0200   0.9790   0.0032
  -6.750  -0.6493   0.02903   0.02431  -0.0179   0.9774   0.0031
  -6.500  -0.6293   0.02467   0.01944  -0.0161   0.9764   0.0030
  -6.250  -0.6143   0.02142   0.01571  -0.0129   0.9726   0.0029
  -6.000  -0.5899   0.01864   0.01252  -0.0119   0.9712   0.0029
  -5.750  -0.5641   0.01665   0.01023  -0.0114   0.9701   0.0029
  -5.500  -0.5392   0.01520   0.00857  -0.0110   0.9688   0.0030
  -5.250  -0.5142   0.01405   0.00725  -0.0106   0.9676   0.0031
  -5.000  -0.4875   0.01321   0.00624  -0.0106   0.9665   0.0034
  -4.750  -0.4591   0.01258   0.00548  -0.0110   0.9656   0.0041
  -4.500  -0.4398   0.01224   0.00515  -0.0094   0.9617   0.0082
  -4.250  -0.4141   0.01198   0.00488  -0.0093   0.9592   0.0124
  -4.000  -0.3857   0.01184   0.00474  -0.0099   0.9575   0.0201
  -3.750  -0.3576   0.01152   0.00436  -0.0103   0.9560   0.0222
  -3.500  -0.3284   0.01124   0.00402  -0.0109   0.9547   0.0237
  -3.250  -0.2988   0.01098   0.00371  -0.0116   0.9536   0.0263
  -3.000  -0.2753   0.01075   0.00350  -0.0109   0.9506   0.0342
  -2.750  -0.2563   0.01022   0.00326  -0.0094   0.9466   0.1089
  -2.500  -0.2386   0.00924   0.00294  -0.0079   0.9435   0.2868
  -2.250  -0.2268   0.00794   0.00257  -0.0052   0.9407   0.5245
  -2.000  -0.2288   0.00686   0.00245   0.0014   0.9344   0.7495
  -1.750  -0.2044   0.00669   0.00255   0.0024   0.9319   0.8345
  -1.500  -0.1750   0.00670   0.00259   0.0021   0.9301   0.8609
  -1.250  -0.1447   0.00679   0.00271   0.0017   0.9286   0.8843
  -1.000  -0.1135   0.00688   0.00280   0.0010   0.9273   0.8970
  -0.750  -0.0858   0.00691   0.00281   0.0009   0.9244   0.9021
  -0.500  -0.0583   0.00699   0.00288   0.0009   0.9209   0.9076
  -0.250  -0.0328   0.00698   0.00286   0.0013   0.9177   0.9138
   0.000   0.0000   0.00700   0.00287   0.0000   0.9158   0.9158
   0.250   0.0328   0.00698   0.00286  -0.0013   0.9138   0.9177
   0.500   0.0583   0.00699   0.00288  -0.0009   0.9076   0.9209
   0.750   0.0858   0.00691   0.00281  -0.0009   0.9021   0.9244
   1.000   0.1135   0.00688   0.00280  -0.0010   0.8970   0.9273
   1.250   0.1444   0.00679   0.00271  -0.0016   0.8836   0.9286
   1.500   0.1749   0.00670   0.00260  -0.0021   0.8611   0.9301
   1.750   0.2042   0.00669   0.00255  -0.0024   0.8353   0.9320
   2.000   0.2286   0.00686   0.00245  -0.0014   0.7483   0.9344
   2.250   0.2269   0.00793   0.00257   0.0052   0.5256   0.9407
   2.500   0.2386   0.00924   0.00294   0.0079   0.2872   0.9435
   2.750   0.2562   0.01022   0.00326   0.0094   0.1088   0.9465
   3.000   0.2753   0.01075   0.00350   0.0109   0.0342   0.9506
   3.250   0.2989   0.01098   0.00371   0.0115   0.0263   0.9536
   3.500   0.3284   0.01124   0.00402   0.0109   0.0237   0.9547
   3.750   0.3576   0.01152   0.00435   0.0103   0.0222   0.9560
   4.000   0.3857   0.01184   0.00474   0.0099   0.0202   0.9575
   4.250   0.4142   0.01198   0.00489   0.0093   0.0126   0.9593
   4.500   0.4398   0.01224   0.00515   0.0094   0.0081   0.9617
   4.750   0.4591   0.01258   0.00549   0.0110   0.0041   0.9656
   5.000   0.4872   0.01322   0.00626   0.0107   0.0034   0.9665
   5.250   0.5141   0.01406   0.00725   0.0106   0.0031   0.9676
   5.500   0.5392   0.01518   0.00855   0.0109   0.0030   0.9688
   5.750   0.5642   0.01666   0.01025   0.0114   0.0029   0.9701
   6.000   0.5900   0.01863   0.01251   0.0119   0.0029   0.9712
   6.250   0.6144   0.02141   0.01570   0.0129   0.0029   0.9727
   6.500   0.6294   0.02463   0.01940   0.0161   0.0030   0.9764
   6.750   0.6494   0.02903   0.02431   0.0179   0.0031   0.9774
   7.000   0.6657   0.03351   0.02923   0.0200   0.0032   0.9790
   7.250   0.6781   0.03791   0.03401   0.0224   0.0033   0.9813
   7.500   0.6858   0.04211   0.03852   0.0252   0.0033   0.9850
   7.750   0.6937   0.04664   0.04335   0.0273   0.0034   0.9874
   8.000   0.7001   0.05135   0.04833   0.0287   0.0035   0.9897
   8.250   0.7027   0.05607   0.05327   0.0302   0.0036   0.9927
   8.500   0.7021   0.06081   0.05821   0.0312   0.0036   0.9955
   8.750   0.7002   0.06599   0.06356   0.0312   0.0037   0.9982
   9.000   0.6849   0.06950   0.06716   0.0340   0.0037   1.0000
   9.250   0.6604   0.07164   0.06934   0.0390   0.0038   1.0000
   9.500   0.6381   0.07472   0.07246   0.0418   0.0038   1.0000
   9.750   0.6183   0.07891   0.07668   0.0419   0.0038   1.0000
  10.000   0.6021   0.08494   0.08273   0.0380   0.0038   1.0000
  10.250   0.5916   0.09095   0.08870   0.0342   0.0038   1.0000
  10.500   0.5837   0.09629   0.09400   0.0319   0.0039   1.0000
  10.750   0.5764   0.10148   0.09917   0.0298   0.0040   1.0000
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