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NACA 0010-35 (naca001035-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 0010-35 (naca001035-il)
Reynolds number: 100,000
Max Cl/Cd: 27.13 at α=2.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca001035-il-100000-n5.txt
Download as CSV file: xf-naca001035-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.4781   0.09346   0.08872  -0.0380   1.0000   0.0211
 -10.250  -0.4855   0.08885   0.08415  -0.0389   1.0000   0.0207
 -10.000  -0.4952   0.08377   0.07911  -0.0404   1.0000   0.0203
  -9.750  -0.5081   0.07808   0.07344  -0.0429   1.0000   0.0201
  -9.250  -0.6367   0.07904   0.07399  -0.0413   1.0000   0.0210
  -9.000  -0.6541   0.07618   0.07111  -0.0384   1.0000   0.0207
  -8.750  -0.6730   0.07373   0.06863  -0.0342   1.0000   0.0205
  -8.500  -0.6883   0.07093   0.06577  -0.0302   1.0000   0.0202
  -8.250  -0.7015   0.06803   0.06279  -0.0262   1.0000   0.0198
  -8.000  -0.7127   0.06504   0.05968  -0.0221   1.0000   0.0194
  -7.750  -0.7217   0.06199   0.05648  -0.0179   1.0000   0.0190
  -7.500  -0.7285   0.05887   0.05318  -0.0137   1.0000   0.0186
  -7.250  -0.7331   0.05570   0.04979  -0.0094   1.0000   0.0182
  -7.000  -0.7353   0.05250   0.04634  -0.0052   1.0000   0.0177
  -6.750  -0.7352   0.04930   0.04284  -0.0010   1.0000   0.0173
  -6.500  -0.7326   0.04611   0.03933   0.0032   1.0000   0.0170
  -6.250  -0.7275   0.04299   0.03583   0.0071   1.0000   0.0167
  -6.000  -0.7194   0.04002   0.03247   0.0108   1.0000   0.0166
  -5.750  -0.7085   0.03743   0.02947   0.0141   1.0000   0.0173
  -5.500  -0.6948   0.03501   0.02661   0.0170   1.0000   0.0184
  -5.250  -0.6781   0.03260   0.02374   0.0196   1.0000   0.0192
  -5.000  -0.6582   0.03020   0.02090   0.0218   1.0000   0.0195
  -4.750  -0.6351   0.02801   0.01826   0.0233   1.0000   0.0200
  -4.500  -0.6103   0.02612   0.01604   0.0245   1.0000   0.0208
  -4.250  -0.5868   0.02444   0.01418   0.0255   1.0000   0.0232
  -4.000  -0.5665   0.02314   0.01284   0.0269   1.0000   0.0263
  -3.750  -0.5477   0.02195   0.01153   0.0288   1.0000   0.0289
  -3.500  -0.5305   0.02096   0.01041   0.0308   1.0000   0.0337
  -3.250  -0.5127   0.02015   0.00948   0.0328   1.0000   0.0410
  -3.000  -0.4948   0.01926   0.00854   0.0346   1.0000   0.0573
  -2.750  -0.4789   0.01766   0.00773   0.0365   1.0000   0.1956
  -2.500  -0.3079   0.01938   0.01180   0.0143   1.0000   0.9494
  -2.250  -0.2746   0.01938   0.01156   0.0126   1.0000   0.9572
  -2.000  -0.2412   0.01936   0.01134   0.0108   1.0000   0.9644
  -1.750  -0.2049   0.01933   0.01111   0.0084   1.0000   0.9706
  -1.500  -0.1714   0.01933   0.01096   0.0065   1.0000   0.9778
  -1.250  -0.1355   0.01925   0.01075   0.0040   1.0000   0.9827
  -1.000  -0.1032   0.01921   0.01062   0.0021   1.0000   0.9880
  -0.750  -0.0700   0.01915   0.01050   0.0001   1.0000   0.9925
  -0.500  -0.0372   0.01912   0.01041  -0.0019   1.0000   0.9969
  -0.250  -0.0101   0.01909   0.01037  -0.0027   1.0000   1.0000
   0.000   0.0000   0.01908   0.01035   0.0000   1.0000   1.0000
   0.250   0.0101   0.01909   0.01037   0.0027   1.0000   1.0000
   0.500   0.0372   0.01911   0.01041   0.0019   0.9969   1.0000
   0.750   0.0699   0.01915   0.01050  -0.0001   0.9926   1.0000
   1.000   0.1031   0.01921   0.01062  -0.0021   0.9880   1.0000
   1.250   0.1355   0.01925   0.01075  -0.0039   0.9827   1.0000
   1.500   0.1713   0.01932   0.01095  -0.0064   0.9779   1.0000
   1.750   0.2048   0.01933   0.01110  -0.0084   0.9706   1.0000
   2.000   0.2412   0.01936   0.01134  -0.0108   0.9645   1.0000
   2.250   0.2746   0.01937   0.01156  -0.0126   0.9572   1.0000
   2.500   0.3079   0.01937   0.01180  -0.0143   0.9494   1.0000
   2.750   0.4788   0.01765   0.00773  -0.0365   0.1959   1.0000
   3.000   0.4947   0.01925   0.00854  -0.0346   0.0574   1.0000
   3.250   0.5126   0.02015   0.00947  -0.0327   0.0410   1.0000
   3.500   0.5304   0.02096   0.01041  -0.0308   0.0337   1.0000
   3.750   0.5476   0.02195   0.01153  -0.0288   0.0289   1.0000
   4.000   0.5664   0.02313   0.01283  -0.0269   0.0263   1.0000
   4.250   0.5867   0.02444   0.01418  -0.0255   0.0232   1.0000
   4.500   0.6102   0.02612   0.01604  -0.0245   0.0208   1.0000
   4.750   0.6350   0.02801   0.01826  -0.0233   0.0200   1.0000
   5.000   0.6581   0.03020   0.02089  -0.0217   0.0195   1.0000
   5.250   0.6780   0.03259   0.02374  -0.0196   0.0192   1.0000
   5.500   0.6948   0.03500   0.02660  -0.0170   0.0184   1.0000
   5.750   0.7085   0.03742   0.02945  -0.0141   0.0173   1.0000
   6.000   0.7194   0.04002   0.03246  -0.0108   0.0166   1.0000
   6.250   0.7274   0.04298   0.03582  -0.0071   0.0167   1.0000
   6.500   0.7326   0.04611   0.03932  -0.0032   0.0170   1.0000
   6.750   0.7352   0.04929   0.04283   0.0010   0.0173   1.0000
   7.000   0.7353   0.05250   0.04633   0.0052   0.0177   1.0000
   7.250   0.7331   0.05569   0.04978   0.0095   0.0182   1.0000
   7.500   0.7285   0.05887   0.05317   0.0137   0.0186   1.0000
   7.750   0.7217   0.06199   0.05648   0.0180   0.0190   1.0000
   8.000   0.7127   0.06504   0.05968   0.0221   0.0194   1.0000
   8.250   0.7016   0.06802   0.06278   0.0262   0.0198   1.0000
   8.500   0.6885   0.07092   0.06577   0.0302   0.0202   1.0000
   8.750   0.6732   0.07373   0.06863   0.0341   0.0205   1.0000
   9.000   0.6543   0.07619   0.07112   0.0383   0.0207   1.0000
   9.250   0.6370   0.07905   0.07400   0.0413   0.0210   1.0000
   9.500   0.5249   0.07259   0.06794   0.0448   0.0199   1.0000
   9.750   0.5077   0.07792   0.07328   0.0429   0.0201   1.0000
  10.000   0.4948   0.08361   0.07894   0.0404   0.0203   1.0000
  10.250   0.4851   0.08870   0.08400   0.0389   0.0207   1.0000
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