Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

NACA 0010-65 (naca001065-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA 0010-65 (naca001065-il)
Reynolds number: 200,000
Max Cl/Cd: 35.69 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca001065-il-200000-n5.txt
Download as CSV file: xf-naca001065-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 0010-65                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.8122   0.06173   0.05773  -0.0521   1.0000   0.0189
 -11.500  -0.8483   0.05615   0.05197  -0.0502   1.0000   0.0187
 -11.250  -0.8827   0.05181   0.04740  -0.0455   1.0000   0.0187
 -11.000  -0.9144   0.04846   0.04381  -0.0388   1.0000   0.0188
 -10.750  -0.9433   0.04536   0.04042  -0.0313   1.0000   0.0191
 -10.500  -0.9656   0.04184   0.03649  -0.0245   1.0000   0.0195
 -10.250  -0.9797   0.03868   0.03285  -0.0184   1.0000   0.0200
 -10.000  -0.9843   0.03632   0.03017  -0.0136   1.0000   0.0205
  -9.750  -0.9793   0.03515   0.02888  -0.0102   1.0000   0.0211
  -9.500  -0.9706   0.03447   0.02814  -0.0073   1.0000   0.0217
  -9.250  -0.9612   0.03374   0.02730  -0.0044   1.0000   0.0227
  -9.000  -0.9525   0.03261   0.02597  -0.0013   1.0000   0.0239
  -8.750  -0.9434   0.03112   0.02418   0.0018   1.0000   0.0252
  -8.500  -0.9324   0.02961   0.02232   0.0047   1.0000   0.0265
  -8.250  -0.9196   0.02830   0.02071   0.0072   1.0000   0.0275
  -8.000  -0.9060   0.02703   0.01936   0.0094   1.0000   0.0289
  -7.750  -0.8905   0.02637   0.01861   0.0114   1.0000   0.0302
  -7.500  -0.8741   0.02556   0.01766   0.0133   1.0000   0.0317
  -7.250  -0.8559   0.02468   0.01659   0.0149   0.9999   0.0332
  -7.000  -0.8294   0.02387   0.01557   0.0148   0.9985   0.0351
  -6.750  -0.8026   0.02287   0.01438   0.0147   0.9971   0.0364
  -6.500  -0.7762   0.02175   0.01321   0.0145   0.9958   0.0382
  -6.250  -0.7483   0.02114   0.01252   0.0140   0.9945   0.0401
  -6.000  -0.7222   0.02047   0.01178   0.0140   0.9929   0.0417
  -5.750  -0.6958   0.01979   0.01101   0.0140   0.9911   0.0430
  -5.500  -0.6685   0.01921   0.01034   0.0138   0.9893   0.0446
  -5.250  -0.6403   0.01874   0.00976   0.0135   0.9875   0.0462
  -5.000  -0.6138   0.01802   0.00904   0.0133   0.9860   0.0483
  -4.750  -0.5867   0.01753   0.00854   0.0131   0.9843   0.0503
  -4.500  -0.5618   0.01712   0.00808   0.0135   0.9816   0.0526
  -4.250  -0.5351   0.01675   0.00766   0.0134   0.9792   0.0555
  -4.000  -0.5072   0.01639   0.00728   0.0132   0.9772   0.0593
  -3.750  -0.4781   0.01604   0.00695   0.0126   0.9755   0.0668
  -3.500  -0.4509   0.01569   0.00665   0.0124   0.9734   0.0800
  -3.250  -0.4275   0.01536   0.00639   0.0131   0.9701   0.0986
  -3.000  -0.4012   0.01501   0.00618   0.0130   0.9675   0.1272
  -2.750  -0.3735   0.01464   0.00598   0.0126   0.9653   0.1673
  -2.500  -0.3456   0.01421   0.00580   0.0122   0.9635   0.2251
  -2.250  -0.3249   0.01355   0.00559   0.0131   0.9604   0.3287
  -2.000  -0.3232   0.01171   0.00542   0.0184   0.9559   0.6826
  -1.750  -0.2786   0.01208   0.00641   0.0163   0.9579   0.8575
  -1.500  -0.2458   0.01246   0.00678   0.0158   0.9561   0.8912
  -1.250  -0.2099   0.01282   0.00709   0.0145   0.9547   0.9079
  -1.000  -0.1712   0.01326   0.00751   0.0126   0.9539   0.9229
  -0.750  -0.1210   0.01391   0.00812   0.0084   0.9551   0.9374
  -0.500  -0.0730   0.01429   0.00849   0.0043   0.9556   0.9465
  -0.250  -0.0373   0.01436   0.00853   0.0024   0.9538   0.9506
   0.000   0.0000   0.01436   0.00853   0.0000   0.9521   0.9521
   0.250   0.0373   0.01436   0.00853  -0.0024   0.9506   0.9538
   0.500   0.0731   0.01429   0.00849  -0.0043   0.9466   0.9557
   0.750   0.1210   0.01391   0.00812  -0.0084   0.9374   0.9552
   1.000   0.1711   0.01326   0.00751  -0.0126   0.9230   0.9539
   1.250   0.2099   0.01281   0.00709  -0.0145   0.9079   0.9547
   1.500   0.2459   0.01245   0.00678  -0.0158   0.8912   0.9561
   1.750   0.2786   0.01207   0.00640  -0.0163   0.8574   0.9579
   2.000   0.3231   0.01171   0.00542  -0.0184   0.6838   0.9559
   2.250   0.3248   0.01355   0.00559  -0.0131   0.3286   0.9604
   2.500   0.3456   0.01421   0.00579  -0.0122   0.2251   0.9635
   2.750   0.3735   0.01464   0.00597  -0.0126   0.1675   0.9653
   3.000   0.4012   0.01501   0.00617  -0.0130   0.1272   0.9675
   3.250   0.4275   0.01536   0.00639  -0.0131   0.0987   0.9702
   3.500   0.4508   0.01569   0.00665  -0.0124   0.0800   0.9735
   3.750   0.4781   0.01603   0.00695  -0.0126   0.0669   0.9756
   4.000   0.5073   0.01638   0.00727  -0.0132   0.0594   0.9773
   4.250   0.5351   0.01675   0.00766  -0.0134   0.0555   0.9793
   4.500   0.5617   0.01712   0.00809  -0.0135   0.0526   0.9816
   4.750   0.5866   0.01753   0.00854  -0.0131   0.0503   0.9844
   5.000   0.6138   0.01802   0.00904  -0.0133   0.0483   0.9861
   5.250   0.6403   0.01874   0.00975  -0.0135   0.0462   0.9876
   5.500   0.6685   0.01920   0.01033  -0.0138   0.0446   0.9893
   5.750   0.6958   0.01979   0.01101  -0.0140   0.0431   0.9912
   6.000   0.7222   0.02047   0.01178  -0.0140   0.0417   0.9929
   6.250   0.7484   0.02113   0.01252  -0.0140   0.0401   0.9945
   6.500   0.7763   0.02175   0.01320  -0.0145   0.0382   0.9959
   6.750   0.8026   0.02287   0.01438  -0.0147   0.0364   0.9971
   7.000   0.8294   0.02387   0.01556  -0.0148   0.0351   0.9985
   7.250   0.8559   0.02467   0.01659  -0.0149   0.0332   0.9999
   7.500   0.8740   0.02555   0.01766  -0.0132   0.0317   1.0000
   7.750   0.8904   0.02637   0.01861  -0.0113   0.0302   1.0000
   8.000   0.9059   0.02703   0.01936  -0.0094   0.0289   1.0000
   8.250   0.9195   0.02829   0.02069  -0.0072   0.0275   1.0000
   8.500   0.9323   0.02960   0.02231  -0.0046   0.0265   1.0000
   8.750   0.9433   0.03112   0.02418  -0.0017   0.0252   1.0000
   9.000   0.9524   0.03259   0.02595   0.0014   0.0239   1.0000
   9.250   0.9612   0.03372   0.02729   0.0044   0.0227   1.0000
   9.500   0.9705   0.03445   0.02813   0.0073   0.0217   1.0000
   9.750   0.9792   0.03515   0.02888   0.0102   0.0211   1.0000
  10.000   0.9843   0.03631   0.03016   0.0136   0.0205   1.0000
  10.250   0.9798   0.03867   0.03284   0.0184   0.0200   1.0000
  10.500   0.9656   0.04183   0.03648   0.0245   0.0195   1.0000
  10.750   0.9434   0.04536   0.04042   0.0313   0.0191   1.0000
  11.000   0.9146   0.04847   0.04382   0.0387   0.0188   1.0000
  11.250   0.8827   0.05184   0.04743   0.0455   0.0187   1.0000
  11.500   0.8484   0.05620   0.05202   0.0502   0.0187   1.0000
  11.750   0.8122   0.06182   0.05783   0.0520   0.0188   1.0000
<< Back to NACA 0010-65 (naca001065-il)

Polar data table (+)

Polar graphs


<< Back to NACA 0010-65 (naca001065-il)