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NACA 65(2)-215 (naca652215-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NACA 65(2)-215 (naca652215-il)
Reynolds number: 200,000
Max Cl/Cd: 57.47 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca652215-il-200000.txt
Download as CSV file: xf-naca652215-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 65(2)-215                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.4007   0.09597   0.09261  -0.0468   1.0000   0.0843
 -11.500  -0.4188   0.08889   0.08556  -0.0507   1.0000   0.0877
  -9.500  -0.7657   0.04583   0.04031  -0.0513   0.9808   0.0530
  -9.250  -0.7560   0.03837   0.03179  -0.0510   0.9733   0.0450
  -9.000  -0.7253   0.03456   0.02765  -0.0534   0.9703   0.0454
  -8.750  -0.6969   0.03182   0.02466  -0.0546   0.9640   0.0458
  -8.500  -0.6621   0.02937   0.02194  -0.0566   0.9602   0.0458
  -8.250  -0.6239   0.02715   0.01954  -0.0590   0.9575   0.0464
  -8.000  -0.5926   0.02560   0.01790  -0.0600   0.9509   0.0474
  -7.750  -0.5585   0.02440   0.01663  -0.0617   0.9456   0.0497
  -7.500  -0.5248   0.02321   0.01534  -0.0629   0.9405   0.0515
  -7.250  -0.4967   0.02222   0.01424  -0.0630   0.9328   0.0529
  -7.000  -0.4660   0.02126   0.01320  -0.0636   0.9276   0.0543
  -6.750  -0.4462   0.02003   0.01205  -0.0625   0.9186   0.0568
  -6.500  -0.4250   0.01935   0.01136  -0.0616   0.9118   0.0603
  -6.250  -0.4084   0.01885   0.01081  -0.0599   0.9022   0.0635
  -6.000  -0.3923   0.01809   0.01002  -0.0580   0.8956   0.0670
  -5.750  -0.3784   0.01748   0.00943  -0.0560   0.8867   0.0721
  -5.500  -0.3617   0.01685   0.00877  -0.0543   0.8808   0.0811
  -5.250  -0.3478   0.01616   0.00817  -0.0523   0.8723   0.1008
  -5.000  -0.3499   0.01406   0.00713  -0.0485   0.8653   0.2911
  -4.750  -0.3481   0.01287   0.00716  -0.0444   0.8571   0.5471
  -4.500  -0.3247   0.01304   0.00736  -0.0431   0.8520   0.6018
  -4.250  -0.2990   0.01325   0.00746  -0.0423   0.8483   0.6303
  -4.000  -0.2746   0.01357   0.00778  -0.0413   0.8416   0.6491
  -3.750  -0.2485   0.01381   0.00797  -0.0405   0.8366   0.6650
  -3.500  -0.2223   0.01433   0.00849  -0.0391   0.8330   0.6851
  -3.250  -0.1993   0.01518   0.00938  -0.0371   0.8273   0.7101
  -3.000  -0.1732   0.01583   0.01008  -0.0354   0.8226   0.7225
  -2.750  -0.1464   0.01587   0.01005  -0.0350   0.8187   0.7293
  -2.500  -0.1192   0.01597   0.01008  -0.0346   0.8150   0.7345
  -2.250  -0.0949   0.01590   0.00993  -0.0346   0.8089   0.7420
  -2.000  -0.0678   0.01589   0.00989  -0.0343   0.8048   0.7453
  -1.750  -0.0400   0.01587   0.00980  -0.0342   0.8016   0.7490
  -1.500  -0.0139   0.01586   0.00974  -0.0342   0.7971   0.7537
  -1.250   0.0118   0.01575   0.00957  -0.0345   0.7918   0.7591
  -1.000   0.0391   0.01573   0.00953  -0.0344   0.7881   0.7620
  -0.750   0.0671   0.01571   0.00947  -0.0344   0.7852   0.7656
  -0.500   0.0929   0.01575   0.00950  -0.0345   0.7807   0.7701
  -0.250   0.1190   0.01571   0.00943  -0.0348   0.7757   0.7753
   0.000   0.1461   0.01572   0.00944  -0.0346   0.7721   0.7783
   0.250   0.1741   0.01571   0.00942  -0.0346   0.7694   0.7820
   0.500   0.2000   0.01579   0.00951  -0.0347   0.7651   0.7866
   0.750   0.2258   0.01584   0.00957  -0.0349   0.7601   0.7918
   1.000   0.2523   0.01589   0.00965  -0.0347   0.7566   0.7951
   1.250   0.2805   0.01589   0.00965  -0.0348   0.7538   0.7990
   1.500   0.3070   0.01598   0.00977  -0.0350   0.7500   0.8042
   1.750   0.3311   0.01615   0.01000  -0.0348   0.7449   0.8089
   2.000   0.3572   0.01622   0.01012  -0.0345   0.7411   0.8129
   2.250   0.3857   0.01622   0.01013  -0.0347   0.7381   0.8176
   2.500   0.4130   0.01632   0.01027  -0.0350   0.7345   0.8233
   2.750   0.4347   0.01653   0.01060  -0.0341   0.7285   0.8274
   3.000   0.4620   0.01650   0.01062  -0.0339   0.7242   0.8324
   3.250   0.4932   0.01637   0.01049  -0.0345   0.7209   0.8385
   3.500   0.5132   0.01658   0.01084  -0.0333   0.7136   0.8429
   3.750   0.5407   0.01646   0.01077  -0.0330   0.7083   0.8481
   4.000   0.5706   0.01626   0.01061  -0.0332   0.7025   0.8547
   4.250   0.5954   0.01589   0.01032  -0.0319   0.6923   0.8593
   4.500   0.6248   0.01493   0.00930  -0.0308   0.6750   0.8650
   4.750   0.6510   0.01423   0.00857  -0.0296   0.6548   0.8715
   5.000   0.6745   0.01390   0.00829  -0.0281   0.6406   0.8769
   5.250   0.6981   0.01367   0.00812  -0.0271   0.6253   0.8846
   5.500   0.7175   0.01346   0.00801  -0.0250   0.6059   0.8914
   5.750   0.7381   0.01325   0.00784  -0.0233   0.5809   0.9000
   6.000   0.7534   0.01311   0.00772  -0.0206   0.5414   0.9081
   6.250   0.7596   0.01332   0.00754  -0.0163   0.4447   0.9191
   6.500   0.7431   0.01453   0.00798  -0.0088   0.3085   0.9351
   6.750   0.7247   0.01618   0.00888  -0.0020   0.1764   0.9568
   7.000   0.7283   0.01837   0.01043  -0.0004   0.0856   0.9769
   7.250   0.7490   0.01980   0.01179  -0.0015   0.0695   1.0000
   7.500   0.7598   0.02057   0.01258  -0.0002   0.0639   1.0000
   7.750   0.7688   0.02186   0.01380   0.0011   0.0591   1.0000
   8.000   0.7855   0.02280   0.01477   0.0017   0.0553   1.0000
   8.250   0.8016   0.02383   0.01579   0.0024   0.0523   1.0000
   8.500   0.8178   0.02501   0.01692   0.0032   0.0500   1.0000
   8.750   0.8400   0.02638   0.01825   0.0036   0.0480   1.0000
   9.000   0.8643   0.02732   0.01925   0.0038   0.0464   1.0000
   9.250   0.8885   0.02832   0.02029   0.0040   0.0442   1.0000
   9.500   0.9152   0.02944   0.02143   0.0038   0.0425   1.0000
   9.750   0.9495   0.03092   0.02290   0.0028   0.0412   1.0000
  10.000   1.0172   0.03488   0.02696  -0.0032   0.0398   1.0000
  10.250   1.0388   0.03665   0.02896  -0.0028   0.0395   1.0000
  10.500   1.0539   0.03827   0.03084  -0.0014   0.0390   1.0000
  10.750   1.0656   0.04005   0.03289   0.0002   0.0384   1.0000
  11.000   1.0791   0.04253   0.03565   0.0015   0.0382   1.0000
  11.250   1.0895   0.04553   0.03893   0.0029   0.0384   1.0000
  11.500   1.0959   0.04884   0.04252   0.0045   0.0388   1.0000
  11.750   1.1008   0.05301   0.04693   0.0059   0.0393   1.0000
  12.000   1.1144   0.05570   0.04980   0.0069   0.0405   1.0000
  12.250   1.0473   0.06262   0.05760   0.0146   0.0468   1.0000
  12.500   0.9380   0.05869   0.05421   0.0206   0.0455   1.0000
  12.750   0.9171   0.06435   0.06006   0.0212   0.0467   1.0000
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