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NACA 0010-66 (naca001066-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 0010-66 (naca001066-il)
Reynolds number: 100,000
Max Cl/Cd: 28.88 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca001066-il-100000-n5.txt
Download as CSV file: xf-naca001066-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 0010-66                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.7094   0.09433   0.08914  -0.0338   1.0000   0.0341
 -11.000  -0.7356   0.08528   0.08013  -0.0387   1.0000   0.0337
 -10.750  -0.7659   0.07875   0.07354  -0.0393   1.0000   0.0334
 -10.500  -0.7967   0.07391   0.06861  -0.0368   1.0000   0.0332
 -10.250  -0.8274   0.07014   0.06473  -0.0321   1.0000   0.0330
 -10.000  -0.8579   0.06711   0.06158  -0.0257   1.0000   0.0330
  -9.750  -0.8857   0.06381   0.05810  -0.0190   1.0000   0.0330
  -9.500  -0.9092   0.05994   0.05397  -0.0127   1.0000   0.0331
  -9.250  -0.9294   0.05595   0.04964  -0.0064   1.0000   0.0335
  -9.000  -0.9461   0.05200   0.04523   0.0001   1.0000   0.0343
  -8.750  -0.9586   0.04842   0.04103   0.0064   1.0000   0.0353
  -8.500  -0.9579   0.04588   0.03833   0.0103   1.0000   0.0364
  -8.250  -0.9513   0.04426   0.03657   0.0135   1.0000   0.0376
  -8.000  -0.9450   0.04223   0.03427   0.0170   1.0000   0.0388
  -7.750  -0.9369   0.04017   0.03189   0.0203   1.0000   0.0402
  -7.500  -0.9272   0.03824   0.02954   0.0235   1.0000   0.0425
  -7.250  -0.9155   0.03621   0.02697   0.0267   1.0000   0.0446
  -7.000  -0.9003   0.03419   0.02451   0.0291   1.0000   0.0460
  -6.750  -0.8829   0.03272   0.02298   0.0307   1.0000   0.0481
  -6.500  -0.8650   0.03173   0.02185   0.0324   1.0000   0.0505
  -6.250  -0.8448   0.03049   0.02035   0.0338   1.0000   0.0528
  -6.000  -0.8225   0.02919   0.01877   0.0350   1.0000   0.0546
  -5.750  -0.8002   0.02823   0.01752   0.0362   1.0000   0.0570
  -5.500  -0.7780   0.02709   0.01636   0.0370   1.0000   0.0597
  -5.250  -0.7560   0.02623   0.01545   0.0380   1.0000   0.0620
  -5.000  -0.7337   0.02540   0.01454   0.0391   1.0000   0.0643
  -4.750  -0.7117   0.02465   0.01366   0.0402   1.0000   0.0669
  -4.500  -0.6902   0.02398   0.01286   0.0415   1.0000   0.0697
  -4.250  -0.6702   0.02329   0.01221   0.0429   1.0000   0.0739
  -4.000  -0.6497   0.02278   0.01167   0.0443   1.0000   0.0801
  -3.750  -0.6294   0.02221   0.01108   0.0458   1.0000   0.0870
  -3.500  -0.6086   0.02171   0.01054   0.0471   1.0000   0.0970
  -3.250  -0.5876   0.02119   0.01009   0.0484   1.0000   0.1124
  -3.000  -0.5662   0.02068   0.00971   0.0495   1.0000   0.1366
  -2.750  -0.3803   0.02029   0.01279   0.0172   1.0000   0.8275
  -2.500  -0.3835   0.02051   0.01290   0.0242   1.0000   0.8931
  -2.250  -0.3473   0.02152   0.01373   0.0233   1.0000   0.9328
  -2.000  -0.2870   0.02249   0.01447   0.0169   1.0000   0.9571
  -1.750  -0.2070   0.02324   0.01501   0.0058   1.0000   0.9789
  -1.500  -0.1050   0.02350   0.01506  -0.0105   1.0000   1.0000
  -1.250  -0.0876   0.02343   0.01493  -0.0088   1.0000   1.0000
  -1.000  -0.0701   0.02337   0.01482  -0.0070   1.0000   1.0000
  -0.750  -0.0526   0.02333   0.01474  -0.0053   1.0000   1.0000
  -0.500  -0.0351   0.02330   0.01469  -0.0035   1.0000   1.0000
  -0.250  -0.0176   0.02328   0.01465  -0.0018   1.0000   1.0000
   0.000   0.0000   0.02327   0.01464   0.0000   1.0000   1.0000
   0.250   0.0176   0.02328   0.01465   0.0018   1.0000   1.0000
   0.500   0.0351   0.02330   0.01468   0.0035   1.0000   1.0000
   0.750   0.0526   0.02333   0.01474   0.0053   1.0000   1.0000
   1.000   0.0701   0.02337   0.01482   0.0070   1.0000   1.0000
   1.250   0.0876   0.02342   0.01492   0.0088   1.0000   1.0000
   1.500   0.1050   0.02349   0.01505   0.0105   1.0000   1.0000
   1.750   0.2066   0.02324   0.01501  -0.0057   0.9791   1.0000
   2.000   0.2870   0.02248   0.01446  -0.0169   0.9571   1.0000
   2.250   0.3473   0.02151   0.01372  -0.0233   0.9328   1.0000
   2.500   0.3836   0.02050   0.01290  -0.0242   0.8932   1.0000
   2.750   0.3803   0.02028   0.01277  -0.0172   0.8270   1.0000
   3.000   0.5661   0.02068   0.00971  -0.0495   0.1366   1.0000
   3.250   0.5875   0.02119   0.01007  -0.0484   0.1124   1.0000
   3.500   0.6085   0.02170   0.01054  -0.0471   0.0970   1.0000
   3.750   0.6293   0.02221   0.01107  -0.0457   0.0870   1.0000
   4.000   0.6496   0.02278   0.01167  -0.0443   0.0802   1.0000
   4.250   0.6701   0.02328   0.01221  -0.0429   0.0739   1.0000
   4.500   0.6902   0.02398   0.01286  -0.0415   0.0697   1.0000
   4.750   0.7116   0.02464   0.01365  -0.0402   0.0669   1.0000
   5.000   0.7336   0.02540   0.01453  -0.0391   0.0643   1.0000
   5.250   0.7559   0.02622   0.01544  -0.0380   0.0620   1.0000
   5.500   0.7779   0.02708   0.01636  -0.0370   0.0597   1.0000
   5.750   0.8001   0.02823   0.01752  -0.0361   0.0570   1.0000
   6.000   0.8224   0.02919   0.01876  -0.0350   0.0546   1.0000
   6.250   0.8447   0.03048   0.02034  -0.0338   0.0528   1.0000
   6.500   0.8649   0.03172   0.02184  -0.0324   0.0505   1.0000
   6.750   0.8828   0.03270   0.02296  -0.0307   0.0480   1.0000
   7.000   0.9002   0.03417   0.02450  -0.0291   0.0460   1.0000
   7.250   0.9155   0.03620   0.02696  -0.0267   0.0446   1.0000
   7.500   0.9271   0.03823   0.02953  -0.0235   0.0425   1.0000
   7.750   0.9369   0.04017   0.03189  -0.0203   0.0402   1.0000
   8.000   0.9449   0.04222   0.03426  -0.0170   0.0388   1.0000
   8.250   0.9513   0.04424   0.03654  -0.0135   0.0376   1.0000
   8.500   0.9579   0.04586   0.03831  -0.0103   0.0364   1.0000
   8.750   0.9586   0.04840   0.04101  -0.0064   0.0353   1.0000
   9.000   0.9462   0.05199   0.04521  -0.0001   0.0343   1.0000
   9.250   0.9293   0.05595   0.04964   0.0064   0.0335   1.0000
   9.500   0.9094   0.05992   0.05395   0.0127   0.0331   1.0000
   9.750   0.8858   0.06381   0.05810   0.0190   0.0330   1.0000
  10.000   0.8581   0.06712   0.06158   0.0257   0.0330   1.0000
  10.250   0.8275   0.07015   0.06474   0.0321   0.0330   1.0000
  10.500   0.7969   0.07393   0.06863   0.0368   0.0332   1.0000
  10.750   0.7661   0.07877   0.07356   0.0392   0.0334   1.0000
  11.000   0.7359   0.08532   0.08017   0.0386   0.0337   1.0000
  11.250   0.7096   0.09438   0.08918   0.0337   0.0341   1.0000
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