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

NACA 65-210 (naca65210-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: NACA 65-210 (naca65210-il)
Reynolds number: 1,000,000
Max Cl/Cd: 69.18 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca65210-il-1000000-n5.txt
Download as CSV file: xf-naca65210-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 65-210                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.9905   0.03931   0.03699  -0.0534   1.0000   0.0037
 -12.500  -1.0185   0.03488   0.03228  -0.0502   1.0000   0.0037
 -12.250  -1.0351   0.03094   0.02800  -0.0470   1.0000   0.0037
 -12.000  -1.0363   0.02794   0.02468  -0.0449   1.0000   0.0038
 -11.750  -1.0307   0.02553   0.02200  -0.0431   1.0000   0.0039
 -11.500  -1.0190   0.02377   0.02003  -0.0418   1.0000   0.0041
 -11.250  -1.0022   0.02268   0.01883  -0.0409   1.0000   0.0043
 -11.000  -0.9848   0.02161   0.01763  -0.0399   1.0000   0.0045
 -10.750  -0.9662   0.02071   0.01663  -0.0390   1.0000   0.0046
 -10.500  -0.9469   0.01992   0.01574  -0.0382   1.0000   0.0048
 -10.250  -0.9278   0.01904   0.01475  -0.0372   0.9997   0.0050
 -10.000  -0.8995   0.01817   0.01376  -0.0382   0.9921   0.0053
  -9.750  -0.8698   0.01723   0.01266  -0.0395   0.9848   0.0055
  -9.500  -0.8392   0.01650   0.01182  -0.0409   0.9773   0.0058
  -9.250  -0.8088   0.01577   0.01097  -0.0421   0.9689   0.0060
  -9.000  -0.7803   0.01502   0.01013  -0.0429   0.9594   0.0065
  -8.750  -0.7525   0.01470   0.00977  -0.0434   0.9491   0.0069
  -8.500  -0.7272   0.01433   0.00933  -0.0432   0.9378   0.0072
  -8.250  -0.7028   0.01391   0.00882  -0.0428   0.9271   0.0077
  -8.000  -0.6784   0.01351   0.00832  -0.0425   0.9172   0.0081
  -7.750  -0.6542   0.01310   0.00780  -0.0420   0.9075   0.0085
  -7.500  -0.6292   0.01276   0.00738  -0.0417   0.8978   0.0088
  -7.250  -0.6055   0.01218   0.00670  -0.0412   0.8887   0.0093
  -6.750  -0.5543   0.01166   0.00610  -0.0408   0.8716   0.0105
  -6.500  -0.5284   0.01143   0.00581  -0.0407   0.8638   0.0112
  -6.250  -0.5025   0.01111   0.00543  -0.0405   0.8561   0.0117
  -6.000  -0.4767   0.01080   0.00504  -0.0403   0.8488   0.0122
  -5.750  -0.4505   0.01053   0.00471  -0.0402   0.8410   0.0126
  -5.500  -0.4239   0.01034   0.00445  -0.0401   0.8337   0.0129
  -5.250  -0.3988   0.00980   0.00383  -0.0398   0.8260   0.0138
  -5.000  -0.3725   0.00949   0.00346  -0.0397   0.8194   0.0146
  -4.750  -0.3457   0.00925   0.00320  -0.0397   0.8123   0.0154
  -4.500  -0.3187   0.00906   0.00297  -0.0397   0.8057   0.0164
  -4.250  -0.2915   0.00888   0.00274  -0.0397   0.7984   0.0174
  -4.000  -0.2644   0.00870   0.00251  -0.0397   0.7918   0.0182
  -3.750  -0.2369   0.00855   0.00232  -0.0397   0.7852   0.0187
  -3.500  -0.2097   0.00832   0.00204  -0.0397   0.7791   0.0208
  -3.250  -0.1821   0.00815   0.00186  -0.0398   0.7728   0.0235
  -3.000  -0.1545   0.00803   0.00171  -0.0399   0.7663   0.0259
  -2.750  -0.1267   0.00793   0.00158  -0.0400   0.7601   0.0276
  -2.500  -0.0990   0.00779   0.00144  -0.0401   0.7537   0.0346
  -2.250  -0.0713   0.00766   0.00132  -0.0402   0.7482   0.0447
  -2.000  -0.0439   0.00740   0.00120  -0.0403   0.7420   0.0895
  -1.750  -0.0175   0.00691   0.00104  -0.0405   0.7362   0.1985
  -1.500   0.0082   0.00613   0.00084  -0.0407   0.7303   0.3779
  -1.250   0.0335   0.00539   0.00073  -0.0408   0.7244   0.5707
  -1.000   0.0609   0.00521   0.00074  -0.0408   0.7189   0.6343
  -0.750   0.0890   0.00516   0.00074  -0.0409   0.7128   0.6569
  -0.500   0.1172   0.00516   0.00073  -0.0411   0.7073   0.6705
  -0.250   0.1456   0.00513   0.00074  -0.0412   0.7015   0.6866
   0.000   0.1739   0.00514   0.00075  -0.0414   0.6956   0.6967
   0.250   0.2023   0.00515   0.00076  -0.0415   0.6901   0.7029
   0.500   0.2308   0.00516   0.00078  -0.0417   0.6841   0.7089
   0.750   0.2589   0.00519   0.00080  -0.0418   0.6750   0.7148
   1.000   0.2867   0.00525   0.00082  -0.0419   0.6564   0.7211
   1.250   0.3145   0.00530   0.00085  -0.0419   0.6412   0.7268
   1.500   0.3422   0.00538   0.00089  -0.0420   0.6229   0.7331
   1.750   0.3686   0.00557   0.00094  -0.0418   0.5784   0.7390
   2.000   0.3932   0.00598   0.00105  -0.0413   0.4921   0.7455
   2.250   0.4141   0.00693   0.00136  -0.0405   0.3317   0.7517
   2.500   0.4364   0.00771   0.00166  -0.0400   0.2040   0.7580
   2.750   0.4601   0.00834   0.00194  -0.0395   0.1086   0.7649
   3.000   0.4846   0.00882   0.00220  -0.0392   0.0457   0.7716
   3.250   0.5113   0.00903   0.00237  -0.0391   0.0328   0.7786
   3.500   0.5381   0.00920   0.00255  -0.0391   0.0285   0.7851
   3.750   0.5648   0.00940   0.00275  -0.0390   0.0241   0.7922
   4.000   0.5916   0.00956   0.00296  -0.0389   0.0224   0.7992
   4.250   0.6183   0.00973   0.00317  -0.0388   0.0204   0.8071
   4.500   0.6445   0.00994   0.00339  -0.0386   0.0181   0.8145
   4.750   0.6702   0.01025   0.00372  -0.0384   0.0156   0.8222
   5.000   0.6962   0.01045   0.00399  -0.0382   0.0151   0.8295
   5.250   0.7221   0.01070   0.00429  -0.0380   0.0144   0.8375
   5.500   0.7475   0.01097   0.00461  -0.0376   0.0136   0.8458
   5.750   0.7728   0.01124   0.00492  -0.0373   0.0129   0.8541
   6.000   0.7977   0.01153   0.00526  -0.0369   0.0122   0.8630
   6.250   0.8219   0.01189   0.00568  -0.0364   0.0116   0.8717
   6.500   0.8450   0.01237   0.00623  -0.0357   0.0111   0.8816
   6.750   0.8661   0.01302   0.00701  -0.0346   0.0106   0.8927
   7.000   0.8889   0.01342   0.00748  -0.0339   0.0105   0.9039
   7.250   0.9120   0.01373   0.00786  -0.0332   0.0103   0.9156
   7.500   0.9342   0.01410   0.00832  -0.0323   0.0100   0.9284
   7.750   0.9553   0.01451   0.00882  -0.0312   0.0098   0.9432
   8.000   0.9775   0.01493   0.00933  -0.0304   0.0095   0.9640
   8.250   1.0048   0.01543   0.00989  -0.0308   0.0091   1.0000
   8.500   1.0287   0.01584   0.01034  -0.0304   0.0087   1.0000
   8.750   1.0531   0.01615   0.01066  -0.0302   0.0082   1.0000
   9.000   1.0762   0.01662   0.01117  -0.0298   0.0079   1.0000
   9.250   1.0977   0.01727   0.01187  -0.0291   0.0075   1.0000
   9.500   1.1158   0.01836   0.01307  -0.0279   0.0071   1.0000
   9.750   1.1374   0.01895   0.01373  -0.0273   0.0070   1.0000
  10.000   1.1591   0.01947   0.01433  -0.0267   0.0068   1.0000
  10.250   1.1795   0.02014   0.01509  -0.0259   0.0066   1.0000
  10.500   1.1994   0.02082   0.01585  -0.0250   0.0063   1.0000
  10.750   1.2189   0.02149   0.01660  -0.0241   0.0060   1.0000
  11.000   1.2389   0.02201   0.01719  -0.0233   0.0057   1.0000
  11.250   1.2593   0.02239   0.01760  -0.0226   0.0054   1.0000
  11.500   1.2767   0.02307   0.01835  -0.0214   0.0052   1.0000
  11.750   1.2939   0.02351   0.01881  -0.0202   0.0050   1.0000
  12.000   1.3064   0.02436   0.01974  -0.0183   0.0048   1.0000
  12.250   1.3160   0.02544   0.02093  -0.0162   0.0046   1.0000
  12.500   1.3257   0.02651   0.02212  -0.0142   0.0045   1.0000
  12.750   1.3350   0.02762   0.02335  -0.0123   0.0044   1.0000
  13.000   1.3419   0.02895   0.02482  -0.0104   0.0043   1.0000
  13.250   1.3493   0.03025   0.02624  -0.0086   0.0042   1.0000
  13.500   1.3544   0.03178   0.02792  -0.0069   0.0041   1.0000
  13.750   1.3586   0.03343   0.02970  -0.0053   0.0040   1.0000
  14.000   1.3616   0.03525   0.03166  -0.0039   0.0039   1.0000
  14.250   1.3653   0.03703   0.03356  -0.0027   0.0038   1.0000
  14.500   1.3672   0.03907   0.03572  -0.0017   0.0036   1.0000
  14.750   1.3679   0.04132   0.03808  -0.0010   0.0035   1.0000
  15.000   1.3619   0.04440   0.04133  -0.0003   0.0035   1.0000
  15.250   1.3552   0.04773   0.04482  -0.0002   0.0035   1.0000
  15.500   1.3488   0.05120   0.04843  -0.0004   0.0034   1.0000
  15.750   1.3384   0.05541   0.05279  -0.0012   0.0033   1.0000
  16.000   1.3249   0.06035   0.05788  -0.0027   0.0033   1.0000
  16.250   1.3056   0.06660   0.06431  -0.0053   0.0033   1.0000
  16.500   1.2796   0.07474   0.07264  -0.0096   0.0033   1.0000
  16.750   1.2128   0.09339   0.09166  -0.0215   0.0035   1.0000
<< Back to NACA 65-210 (naca65210-il)

Polar data table (+)

Polar graphs


<< Back to NACA 65-210 (naca65210-il)