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NACA 66 (p51htip-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 66 (p51htip-il)
Reynolds number: 100,000
Max Cl/Cd: 38.74 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-p51htip-il-100000-n5.txt
Download as CSV file: xf-p51htip-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 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
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.4830   0.11034   0.10523  -0.0440   1.0000   0.0348
 -11.500  -0.4793   0.10657   0.10145  -0.0447   1.0000   0.0340
 -11.250  -0.4785   0.10228   0.09720  -0.0463   1.0000   0.0332
 -11.000  -0.4815   0.09720   0.09216  -0.0490   1.0000   0.0328
 -10.750  -0.4869   0.09160   0.08661  -0.0523   1.0000   0.0328
 -10.500  -0.4939   0.08566   0.08073  -0.0563   1.0000   0.0324
 -10.250  -0.5071   0.07923   0.07436  -0.0609   1.0000   0.0318
 -10.000  -0.5275   0.07448   0.06961  -0.0628   1.0000   0.0316
  -9.750  -0.5548   0.07150   0.06665  -0.0611   0.9982   0.0305
  -9.500  -0.5651   0.06592   0.06087  -0.0651   0.9856   0.0301
  -9.250  -0.5717   0.06143   0.05614  -0.0669   0.9748   0.0304
  -9.000  -0.5736   0.05739   0.05183  -0.0675   0.9658   0.0310
  -8.750  -0.5710   0.05334   0.04742  -0.0679   0.9593   0.0313
  -8.500  -0.5699   0.04994   0.04370  -0.0666   0.9511   0.0312
  -8.250  -0.5622   0.04629   0.03962  -0.0659   0.9459   0.0311
  -8.000  -0.5575   0.04342   0.03637  -0.0637   0.9386   0.0310
  -7.750  -0.5454   0.04048   0.03301  -0.0624   0.9336   0.0311
  -7.500  -0.5337   0.03797   0.03007  -0.0606   0.9282   0.0313
  -7.250  -0.5194   0.03572   0.02742  -0.0589   0.9230   0.0317
  -7.000  -0.4995   0.03362   0.02489  -0.0580   0.9195   0.0328
  -6.750  -0.4780   0.03207   0.02291  -0.0571   0.9163   0.0345
  -6.500  -0.4602   0.03068   0.02114  -0.0555   0.9117   0.0357
  -6.250  -0.4359   0.02858   0.01887  -0.0553   0.9088   0.0368
  -6.000  -0.4095   0.02709   0.01727  -0.0554   0.9064   0.0381
  -5.750  -0.3828   0.02606   0.01613  -0.0556   0.9042   0.0410
  -5.500  -0.3576   0.02510   0.01502  -0.0553   0.9013   0.0437
  -5.250  -0.3362   0.02423   0.01406  -0.0542   0.8974   0.0453
  -5.000  -0.3134   0.02347   0.01320  -0.0534   0.8943   0.0469
  -4.750  -0.2929   0.02258   0.01235  -0.0525   0.8917   0.0502
  -4.500  -0.2708   0.02199   0.01171  -0.0518   0.8895   0.0548
  -4.250  -0.2523   0.02156   0.01117  -0.0503   0.8865   0.0581
  -4.000  -0.2380   0.02117   0.01074  -0.0481   0.8822   0.0619
  -3.750  -0.2182   0.02080   0.01032  -0.0469   0.8790   0.0707
  -3.500  -0.1970   0.02030   0.00989  -0.0459   0.8764   0.0873
  -3.250  -0.1817   0.01918   0.00946  -0.0442   0.8743   0.2147
  -3.000  -0.1893   0.01778   0.00942  -0.0385   0.8693   0.4944
  -2.750  -0.1779   0.01806   0.01066  -0.0331   0.8663   0.7445
  -2.500  -0.1594   0.01889   0.01150  -0.0293   0.8636   0.8064
  -2.250  -0.1284   0.02023   0.01278  -0.0267   0.8626   0.8561
  -2.000  -0.0853   0.02085   0.01324  -0.0284   0.8621   0.8732
  -1.750  -0.0498   0.02095   0.01320  -0.0300   0.8609   0.8781
  -1.500  -0.0286   0.02093   0.01305  -0.0290   0.8589   0.8861
  -1.250  -0.0039   0.02113   0.01318  -0.0289   0.8553   0.8906
  -1.000   0.0167   0.02126   0.01324  -0.0281   0.8519   0.8965
  -0.750   0.0363   0.02130   0.01321  -0.0269   0.8488   0.9026
  -0.500   0.0699   0.02134   0.01318  -0.0285   0.8471   0.9056
  -0.250   0.1007   0.02136   0.01315  -0.0295   0.8453   0.9091
   0.000   0.1085   0.02150   0.01327  -0.0263   0.8406   0.9164
   0.250   0.1353   0.02166   0.01342  -0.0268   0.8370   0.9195
   0.500   0.1638   0.02173   0.01348  -0.0274   0.8341   0.9228
   0.750   0.1914   0.02176   0.01349  -0.0278   0.8317   0.9266
   1.000   0.2173   0.02174   0.01348  -0.0277   0.8295   0.9310
   1.250   0.2375   0.02205   0.01383  -0.0272   0.8238   0.9349
   1.500   0.2638   0.02217   0.01398  -0.0275   0.8199   0.9385
   1.750   0.2924   0.02218   0.01404  -0.0280   0.8170   0.9425
   2.000   0.3244   0.02215   0.01407  -0.0290   0.8148   0.9456
   2.250   0.3463   0.02249   0.01450  -0.0289   0.8079   0.9498
   2.500   0.3774   0.02254   0.01464  -0.0300   0.8039   0.9528
   2.750   0.4118   0.02245   0.01466  -0.0314   0.8010   0.9554
   3.000   0.4335   0.02267   0.01500  -0.0309   0.7938   0.9606
   3.250   0.4696   0.02259   0.01506  -0.0327   0.7888   0.9629
   3.500   0.5100   0.02225   0.01489  -0.0347   0.7853   0.9644
   3.750   0.5369   0.02200   0.01480  -0.0345   0.7737   0.9687
   4.000   0.5828   0.01946   0.01236  -0.0340   0.7441   0.9682
   4.250   0.6065   0.01783   0.01077  -0.0309   0.6923   0.9730
   4.500   0.6380   0.01647   0.00868  -0.0286   0.5025   0.9748
   4.750   0.6360   0.01850   0.00924  -0.0243   0.2574   0.9836
   5.000   0.6481   0.02045   0.01011  -0.0232   0.0896   0.9900
   5.250   0.6714   0.02137   0.01091  -0.0232   0.0666   0.9956
   5.500   0.6918   0.02213   0.01169  -0.0226   0.0570   1.0000
   5.750   0.6931   0.02259   0.01219  -0.0182   0.0533   1.0000
   6.000   0.6910   0.02313   0.01274  -0.0133   0.0509   1.0000
   6.250   0.6894   0.02360   0.01326  -0.0084   0.0493   1.0000
   6.500   0.6904   0.02409   0.01381  -0.0039   0.0476   1.0000
   6.750   0.6973   0.02473   0.01451  -0.0006   0.0450   1.0000
   7.000   0.7088   0.02551   0.01531   0.0017   0.0421   1.0000
   7.250   0.7240   0.02663   0.01638   0.0033   0.0398   1.0000
   7.500   0.7499   0.02806   0.01782   0.0034   0.0383   1.0000
   7.750   0.7817   0.02949   0.01941   0.0027   0.0369   1.0000
   8.000   0.8104   0.03091   0.02101   0.0023   0.0349   1.0000
   8.250   0.8355   0.03234   0.02259   0.0024   0.0328   1.0000
   8.500   0.8611   0.03407   0.02449   0.0024   0.0317   1.0000
   8.750   0.8848   0.03603   0.02665   0.0027   0.0308   1.0000
   9.000   0.9057   0.03824   0.02908   0.0033   0.0302   1.0000
   9.250   0.9234   0.04072   0.03183   0.0042   0.0297   1.0000
   9.500   0.9374   0.04361   0.03500   0.0054   0.0292   1.0000
   9.750   0.9440   0.04667   0.03838   0.0075   0.0286   1.0000
  10.000   0.9450   0.04864   0.04076   0.0107   0.0279   1.0000
  10.250   0.9433   0.05094   0.04343   0.0139   0.0273   1.0000
  10.500   0.9372   0.05351   0.04632   0.0173   0.0270   1.0000
  10.750   0.9288   0.05633   0.04941   0.0205   0.0269   1.0000
  11.000   0.9174   0.05933   0.05268   0.0233   0.0269   1.0000
  11.250   0.9036   0.06258   0.05617   0.0257   0.0269   1.0000
  11.500   0.8884   0.06606   0.05988   0.0275   0.0269   1.0000
  11.750   0.8697   0.07007   0.06410   0.0287   0.0270   1.0000
  12.000   0.8502   0.07443   0.06865   0.0290   0.0270   1.0000
  12.250   0.8308   0.07918   0.07356   0.0284   0.0272   1.0000
  12.500   0.8088   0.08480   0.07933   0.0266   0.0273   1.0000
  12.750   0.7872   0.09120   0.08586   0.0236   0.0275   1.0000
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