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NACA 0010-34 (naca001034-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 0010-34 (naca001034-il)
Reynolds number: 100,000
Max Cl/Cd: 34.83 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca001034-il-100000-n5.txt
Download as CSV file: xf-naca001034-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.6212   0.10454   0.09963  -0.0161   1.0000   0.0198
 -10.500  -0.6241   0.09935   0.09448  -0.0184   1.0000   0.0194
 -10.250  -0.6283   0.09334   0.08850  -0.0218   1.0000   0.0190
 -10.000  -0.6353   0.08637   0.08154  -0.0269   1.0000   0.0187
  -9.750  -0.6468   0.08021   0.07535  -0.0313   1.0000   0.0185
  -9.500  -0.6612   0.07509   0.07017  -0.0338   1.0000   0.0183
  -9.250  -0.6767   0.07087   0.06585  -0.0343   1.0000   0.0181
  -9.000  -0.6923   0.06730   0.06218  -0.0329   1.0000   0.0180
  -8.750  -0.7049   0.06380   0.05854  -0.0309   1.0000   0.0177
  -8.500  -0.7136   0.06019   0.05474  -0.0287   1.0000   0.0175
  -8.250  -0.7194   0.05660   0.05092  -0.0262   1.0000   0.0172
  -8.000  -0.7225   0.05305   0.04712  -0.0234   1.0000   0.0170
  -7.750  -0.7232   0.04961   0.04337  -0.0203   1.0000   0.0167
  -7.500  -0.7213   0.04630   0.03974  -0.0171   1.0000   0.0165
  -7.250  -0.7170   0.04313   0.03613  -0.0139   1.0000   0.0164
  -7.000  -0.7100   0.04021   0.03282  -0.0107   1.0000   0.0166
  -6.750  -0.7002   0.03756   0.02976  -0.0078   1.0000   0.0173
  -6.500  -0.6879   0.03508   0.02686  -0.0050   1.0000   0.0182
  -6.250  -0.6730   0.03269   0.02404  -0.0024   1.0000   0.0187
  -6.000  -0.6555   0.03032   0.02129  -0.0002   1.0000   0.0189
  -5.750  -0.6356   0.02817   0.01880   0.0017   1.0000   0.0193
  -5.500  -0.6144   0.02629   0.01665   0.0033   1.0000   0.0199
  -5.250  -0.5937   0.02457   0.01475   0.0048   1.0000   0.0210
  -5.000  -0.5765   0.02292   0.01311   0.0065   1.0000   0.0238
  -4.750  -0.5594   0.02171   0.01182   0.0085   1.0000   0.0260
  -4.500  -0.5434   0.02062   0.01055   0.0108   1.0000   0.0282
  -4.250  -0.5274   0.01965   0.00945   0.0130   1.0000   0.0323
  -4.000  -0.5100   0.01884   0.00850   0.0148   1.0000   0.0392
  -3.750  -0.4926   0.01785   0.00750   0.0167   1.0000   0.0544
  -3.500  -0.4818   0.01554   0.00652   0.0189   1.0000   0.2814
  -3.250  -0.4749   0.01364   0.00653   0.0232   1.0000   0.6422
  -3.000  -0.4554   0.01387   0.00729   0.0276   1.0000   0.8092
  -2.750  -0.4303   0.01420   0.00749   0.0293   1.0000   0.8534
  -2.500  -0.4030   0.01436   0.00744   0.0296   1.0000   0.8738
  -2.250  -0.3740   0.01452   0.00738   0.0295   1.0000   0.8917
  -2.000  -0.3442   0.01467   0.00735   0.0290   1.0000   0.9077
  -1.750  -0.3123   0.01482   0.00733   0.0280   1.0000   0.9218
  -1.500  -0.2756   0.01497   0.00733   0.0258   0.9991   0.9334
  -1.250  -0.2318   0.01512   0.00730   0.0221   0.9959   0.9428
  -1.000  -0.1887   0.01524   0.00730   0.0184   0.9920   0.9522
  -0.750  -0.1403   0.01535   0.00729   0.0136   0.9890   0.9580
  -0.500  -0.0950   0.01544   0.00731   0.0094   0.9852   0.9658
  -0.250  -0.0466   0.01547   0.00730   0.0045   0.9809   0.9706
   0.000   0.0000   0.01551   0.00732   0.0000   0.9769   0.9769
   0.250   0.0467   0.01547   0.00730  -0.0046   0.9706   0.9809
   0.500   0.0951   0.01544   0.00731  -0.0094   0.9658   0.9853
   0.750   0.1403   0.01535   0.00729  -0.0136   0.9580   0.9890
   1.000   0.1888   0.01524   0.00729  -0.0185   0.9522   0.9921
   1.250   0.2318   0.01512   0.00730  -0.0221   0.9429   0.9959
   1.500   0.2757   0.01497   0.00732  -0.0259   0.9335   0.9991
   1.750   0.3123   0.01482   0.00733  -0.0280   0.9218   1.0000
   2.000   0.3441   0.01467   0.00735  -0.0290   0.9077   1.0000
   2.250   0.3739   0.01452   0.00738  -0.0295   0.8917   1.0000
   2.500   0.4030   0.01436   0.00744  -0.0296   0.8738   1.0000
   2.750   0.4302   0.01420   0.00749  -0.0292   0.8534   1.0000
   3.000   0.4553   0.01386   0.00728  -0.0276   0.8094   1.0000
   3.250   0.4748   0.01363   0.00652  -0.0232   0.6437   1.0000
   3.500   0.4817   0.01553   0.00652  -0.0189   0.2833   1.0000
   3.750   0.4925   0.01784   0.00749  -0.0167   0.0545   1.0000
   4.000   0.5099   0.01884   0.00850  -0.0148   0.0393   1.0000
   4.250   0.5273   0.01965   0.00944  -0.0129   0.0324   1.0000
   4.500   0.5433   0.02061   0.01054  -0.0108   0.0282   1.0000
   4.750   0.5593   0.02170   0.01181  -0.0085   0.0260   1.0000
   5.000   0.5763   0.02292   0.01311  -0.0065   0.0238   1.0000
   5.250   0.5936   0.02456   0.01475  -0.0048   0.0210   1.0000
   5.500   0.6143   0.02629   0.01664  -0.0033   0.0199   1.0000
   5.750   0.6355   0.02817   0.01880  -0.0016   0.0193   1.0000
   6.000   0.6554   0.03032   0.02128   0.0002   0.0189   1.0000
   6.250   0.6729   0.03268   0.02403   0.0024   0.0187   1.0000
   6.500   0.6878   0.03508   0.02685   0.0050   0.0182   1.0000
   6.750   0.7002   0.03755   0.02975   0.0078   0.0173   1.0000
   7.000   0.7100   0.04021   0.03282   0.0108   0.0166   1.0000
   7.250   0.7170   0.04313   0.03613   0.0139   0.0164   1.0000
   7.500   0.7213   0.04630   0.03974   0.0171   0.0165   1.0000
   7.750   0.7232   0.04962   0.04338   0.0203   0.0167   1.0000
   8.000   0.7226   0.05307   0.04713   0.0233   0.0170   1.0000
   8.250   0.7195   0.05661   0.05094   0.0261   0.0172   1.0000
   8.500   0.7137   0.06021   0.05477   0.0286   0.0175   1.0000
   8.750   0.7051   0.06384   0.05858   0.0308   0.0177   1.0000
   9.000   0.6926   0.06733   0.06222   0.0328   0.0180   1.0000
   9.250   0.6770   0.07091   0.06590   0.0342   0.0181   1.0000
   9.500   0.6616   0.07515   0.07022   0.0337   0.0183   1.0000
   9.750   0.6473   0.08029   0.07543   0.0311   0.0185   1.0000
  10.000   0.6358   0.08647   0.08165   0.0267   0.0187   1.0000
  10.250   0.6290   0.09343   0.08859   0.0216   0.0190   1.0000
  10.500   0.6249   0.09944   0.09456   0.0182   0.0194   1.0000
  10.750   0.6221   0.10462   0.09971   0.0159   0.0198   1.0000
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