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NACA 66-210 (naca66210-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 66-210 (naca66210-il)
Reynolds number: 100,000
Max Cl/Cd: 36.72 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca66210-il-100000-n5.txt
Download as CSV file: xf-naca66210-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 66-210                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.5075   0.08989   0.08486  -0.0420   1.0000   0.0362
  -9.500  -0.5145   0.08429   0.07932  -0.0454   1.0000   0.0341
  -9.250  -0.5291   0.07791   0.07299  -0.0502   1.0000   0.0325
  -8.750  -0.5780   0.06947   0.06434  -0.0495   1.0000   0.0281
  -8.500  -0.5920   0.06652   0.06140  -0.0467   1.0000   0.0278
  -8.250  -0.6074   0.06405   0.05888  -0.0430   1.0000   0.0275
  -8.000  -0.6218   0.06167   0.05643  -0.0390   1.0000   0.0273
  -7.750  -0.6342   0.05912   0.05378  -0.0351   1.0000   0.0271
  -7.500  -0.6303   0.05509   0.04949  -0.0348   0.9961   0.0269
  -7.250  -0.6177   0.05049   0.04451  -0.0358   0.9900   0.0267
  -7.000  -0.6013   0.04612   0.03970  -0.0366   0.9849   0.0268
  -6.750  -0.5820   0.04305   0.03602  -0.0365   0.9791   0.0281
  -6.500  -0.5640   0.03875   0.03124  -0.0371   0.9748   0.0296
  -6.250  -0.5444   0.03573   0.02784  -0.0369   0.9697   0.0302
  -6.000  -0.5195   0.03295   0.02464  -0.0372   0.9663   0.0308
  -5.750  -0.4925   0.03060   0.02190  -0.0377   0.9635   0.0316
  -5.500  -0.4698   0.02895   0.01995  -0.0372   0.9590   0.0333
  -5.250  -0.4420   0.02748   0.01818  -0.0375   0.9557   0.0361
  -5.000  -0.4111   0.02579   0.01618  -0.0381   0.9533   0.0374
  -4.750  -0.3785   0.02425   0.01440  -0.0390   0.9515   0.0387
  -4.500  -0.3549   0.02319   0.01315  -0.0382   0.9472   0.0399
  -4.250  -0.3294   0.02203   0.01193  -0.0380   0.9439   0.0424
  -4.000  -0.3027   0.02109   0.01104  -0.0383   0.9410   0.0468
  -3.750  -0.2739   0.02029   0.01016  -0.0388   0.9386   0.0500
  -3.500  -0.2492   0.01970   0.00943  -0.0385   0.9351   0.0533
  -3.250  -0.2282   0.01913   0.00882  -0.0376   0.9303   0.0595
  -3.000  -0.2015   0.01865   0.00831  -0.0377   0.9272   0.0707
  -2.750  -0.1738   0.01803   0.00780  -0.0380   0.9248   0.1001
  -2.500  -0.1755   0.01550   0.00796  -0.0329   0.9201   0.6311
  -2.250  -0.1646   0.01601   0.00876  -0.0275   0.9152   0.7868
  -2.000  -0.1466   0.01667   0.00938  -0.0234   0.9120   0.8415
  -1.750  -0.1207   0.01726   0.00987  -0.0212   0.9102   0.8742
  -1.500  -0.0844   0.01778   0.01027  -0.0212   0.9095   0.9013
  -1.250  -0.0658   0.01784   0.01023  -0.0196   0.9045   0.9114
  -1.000  -0.0343   0.01787   0.01012  -0.0207   0.9015   0.9161
  -0.750  -0.0060   0.01786   0.01002  -0.0213   0.8987   0.9218
  -0.500   0.0255   0.01785   0.00992  -0.0225   0.8964   0.9258
  -0.250   0.0620   0.01785   0.00984  -0.0247   0.8948   0.9284
   0.000   0.0802   0.01792   0.00989  -0.0234   0.8891   0.9341
   0.250   0.1062   0.01794   0.00988  -0.0236   0.8853   0.9391
   0.500   0.1426   0.01795   0.00988  -0.0257   0.8830   0.9415
   0.750   0.1794   0.01794   0.00988  -0.0279   0.8809   0.9438
   1.000   0.1989   0.01806   0.01002  -0.0269   0.8744   0.9500
   1.250   0.2310   0.01809   0.01009  -0.0282   0.8707   0.9535
   1.500   0.2687   0.01809   0.01016  -0.0306   0.8681   0.9557
   1.750   0.2989   0.01817   0.01032  -0.0316   0.8635   0.9595
   2.000   0.3256   0.01825   0.01049  -0.0319   0.8578   0.9646
   2.250   0.3648   0.01823   0.01061  -0.0344   0.8545   0.9666
   2.500   0.3999   0.01826   0.01078  -0.0362   0.8494   0.9696
   2.750   0.4324   0.01823   0.01091  -0.0374   0.8423   0.9734
   3.000   0.4772   0.01703   0.00989  -0.0384   0.8218   0.9727
   3.250   0.5118   0.01559   0.00853  -0.0370   0.7828   0.9744
   3.500   0.5387   0.01467   0.00762  -0.0350   0.7148   0.9782
   3.750   0.5535   0.01529   0.00656  -0.0307   0.3760   0.9825
   4.000   0.5620   0.01780   0.00742  -0.0288   0.0898   0.9899
   4.250   0.5879   0.01867   0.00822  -0.0290   0.0653   0.9958
   4.500   0.6090   0.01937   0.00896  -0.0283   0.0558   1.0000
   4.750   0.6177   0.01990   0.00952  -0.0251   0.0505   1.0000
   5.000   0.6244   0.02058   0.01024  -0.0215   0.0476   1.0000
   5.250   0.6334   0.02121   0.01098  -0.0183   0.0455   1.0000
   5.500   0.6455   0.02200   0.01184  -0.0156   0.0433   1.0000
   5.750   0.6618   0.02288   0.01277  -0.0139   0.0400   1.0000
   6.000   0.6806   0.02414   0.01398  -0.0128   0.0368   1.0000
   6.250   0.7057   0.02579   0.01568  -0.0125   0.0353   1.0000
   6.500   0.7324   0.02728   0.01734  -0.0123   0.0343   1.0000
   6.750   0.7595   0.02906   0.01934  -0.0121   0.0334   1.0000
   7.000   0.7854   0.03111   0.02171  -0.0117   0.0327   1.0000
   7.250   0.8084   0.03321   0.02416  -0.0109   0.0317   1.0000
   7.500   0.8281   0.03508   0.02635  -0.0099   0.0296   1.0000
   7.750   0.8462   0.03724   0.02881  -0.0087   0.0283   1.0000
   8.000   0.8617   0.03990   0.03185  -0.0072   0.0277   1.0000
   8.250   0.8743   0.04280   0.03514  -0.0054   0.0274   1.0000
   8.500   0.8834   0.04595   0.03869  -0.0033   0.0272   1.0000
   8.750   0.8886   0.04935   0.04248  -0.0010   0.0271   1.0000
   9.000   0.8935   0.05230   0.04572   0.0009   0.0265   1.0000
   9.250   0.8955   0.05531   0.04893   0.0028   0.0257   1.0000
   9.500   0.8910   0.05916   0.05298   0.0048   0.0250   1.0000
   9.750   0.8779   0.06384   0.05786   0.0072   0.0246   1.0000
  10.000   0.8634   0.06623   0.06052   0.0106   0.0243   1.0000
  10.250   0.8479   0.06956   0.06404   0.0127   0.0242   1.0000
  10.500   0.8301   0.07316   0.06784   0.0139   0.0241   1.0000
  10.750   0.8132   0.07751   0.07232   0.0139   0.0242   1.0000
  11.000   0.7962   0.08237   0.07730   0.0127   0.0243   1.0000
  11.250   0.7806   0.08791   0.08291   0.0106   0.0245   1.0000
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