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

NACA 63(4)-421 (naca634421-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NACA 63(4)-421 (naca634421-il)
Reynolds number: 500,000
Max Cl/Cd: 90.79 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca634421-il-500000-n5.txt
Download as CSV file: xf-naca634421-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 63(4)-421                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -19.750  -0.9716   0.09449   0.08982  -0.0554   1.0000   0.0267
 -19.500  -0.9732   0.09092   0.08619  -0.0570   1.0000   0.0273
 -19.250  -0.9729   0.08765   0.08285  -0.0584   1.0000   0.0278
 -19.000  -0.9730   0.08437   0.07951  -0.0598   1.0000   0.0283
 -18.750  -0.9704   0.08150   0.07656  -0.0609   1.0000   0.0290
 -18.500  -0.9686   0.07855   0.07353  -0.0620   1.0000   0.0295
 -18.250  -0.9681   0.07549   0.07042  -0.0632   1.0000   0.0300
 -18.000  -0.9675   0.07245   0.06734  -0.0643   1.0000   0.0305
 -17.750  -0.9651   0.06970   0.06456  -0.0653   1.0000   0.0311
 -17.500  -0.9623   0.06703   0.06183  -0.0662   1.0000   0.0316
 -17.250  -0.9577   0.06462   0.05936  -0.0669   1.0000   0.0323
 -17.000  -0.9529   0.06224   0.05693  -0.0676   1.0000   0.0329
 -16.750  -0.9459   0.06016   0.05478  -0.0682   1.0000   0.0336
 -16.500  -0.9435   0.05761   0.05220  -0.0688   1.0000   0.0341
 -16.250  -0.9394   0.05530   0.04985  -0.0694   1.0000   0.0346
 -16.000  -0.9345   0.05308   0.04761  -0.0699   1.0000   0.0354
 -15.750  -0.9283   0.05106   0.04555  -0.0703   1.0000   0.0360
 -15.500  -0.9219   0.04908   0.04353  -0.0706   1.0000   0.0367
 -15.000  -0.8818   0.04479   0.03911  -0.0765   0.9490   0.0384
 -14.750  -0.8404   0.04211   0.03634  -0.0847   0.9247   0.0397
 -14.500  -0.8120   0.04013   0.03421  -0.0891   0.8946   0.0409
 -14.250  -0.8005   0.03863   0.03255  -0.0896   0.8692   0.0418
 -14.000  -0.7912   0.03728   0.03107  -0.0894   0.8514   0.0425
 -13.750  -0.7835   0.03586   0.02955  -0.0890   0.8376   0.0433
 -13.500  -0.7770   0.03437   0.02799  -0.0886   0.8247   0.0442
 -13.250  -0.7691   0.03302   0.02657  -0.0881   0.8146   0.0454
 -13.000  -0.7606   0.03177   0.02524  -0.0876   0.8044   0.0467
 -12.750  -0.7511   0.03059   0.02399  -0.0870   0.7963   0.0479
 -12.500  -0.7429   0.02935   0.02269  -0.0864   0.7877   0.0493
 -12.250  -0.7349   0.02815   0.02143  -0.0856   0.7798   0.0506
 -12.000  -0.7257   0.02700   0.02025  -0.0849   0.7720   0.0527
 -11.500  -0.7071   0.02484   0.01798  -0.0832   0.7576   0.0562
 -11.250  -0.6972   0.02380   0.01691  -0.0824   0.7509   0.0586
 -11.000  -0.6868   0.02285   0.01590  -0.0814   0.7443   0.0611
 -10.750  -0.6778   0.02184   0.01486  -0.0804   0.7384   0.0642
 -10.500  -0.6665   0.02095   0.01394  -0.0794   0.7323   0.0673
 -10.250  -0.6569   0.02002   0.01299  -0.0782   0.7258   0.0710
  -9.750  -0.6364   0.01832   0.01125  -0.0757   0.7140   0.0805
  -9.500  -0.6260   0.01753   0.01044  -0.0743   0.7079   0.0860
  -9.250  -0.6167   0.01676   0.00965  -0.0726   0.7024   0.0926
  -9.000  -0.6100   0.01601   0.00890  -0.0705   0.6974   0.0999
  -8.750  -0.6041   0.01541   0.00831  -0.0680   0.6922   0.1078
  -8.500  -0.5902   0.01487   0.00778  -0.0667   0.6869   0.1184
  -8.250  -0.5734   0.01440   0.00731  -0.0656   0.6819   0.1304
  -8.000  -0.5542   0.01396   0.00689  -0.0649   0.6771   0.1431
  -7.750  -0.5336   0.01353   0.00649  -0.0643   0.6719   0.1568
  -7.250  -0.4909   0.01264   0.00569  -0.0633   0.6619   0.1917
  -7.000  -0.4685   0.01216   0.00530  -0.0630   0.6567   0.2174
  -6.750  -0.4454   0.01166   0.00492  -0.0628   0.6508   0.2469
  -6.500  -0.4212   0.01123   0.00457  -0.0627   0.6452   0.2756
  -6.000  -0.3698   0.01051   0.00402  -0.0630   0.6366   0.3318
  -5.750  -0.3431   0.01018   0.00382  -0.0632   0.6320   0.3665
  -5.500  -0.3152   0.01000   0.00369  -0.0635   0.6272   0.3930
  -5.250  -0.2869   0.00990   0.00358  -0.0637   0.6227   0.4088
  -5.000  -0.2579   0.00981   0.00349  -0.0641   0.6188   0.4197
  -4.750  -0.2285   0.00975   0.00341  -0.0645   0.6147   0.4306
  -4.500  -0.1994   0.00968   0.00334  -0.0648   0.6105   0.4386
  -4.250  -0.1701   0.00965   0.00327  -0.0651   0.6063   0.4455
  -3.750  -0.1114   0.00958   0.00315  -0.0659   0.5989   0.4586
  -3.500  -0.0817   0.00956   0.00311  -0.0663   0.5950   0.4665
  -3.250  -0.0523   0.00953   0.00307  -0.0666   0.5909   0.4730
  -3.000  -0.0230   0.00952   0.00303  -0.0670   0.5868   0.4785
  -2.750   0.0064   0.00953   0.00299  -0.0673   0.5829   0.4830
  -2.500   0.0363   0.00952   0.00295  -0.0678   0.5790   0.4869
  -2.250   0.0658   0.00949   0.00293  -0.0681   0.5748   0.4908
  -2.000   0.0952   0.00948   0.00291  -0.0685   0.5709   0.4951
  -1.750   0.1245   0.00949   0.00289  -0.0689   0.5671   0.4994
  -1.500   0.1540   0.00952   0.00288  -0.0692   0.5637   0.5037
  -1.250   0.1838   0.00952   0.00287  -0.0697   0.5603   0.5075
  -1.000   0.2133   0.00951   0.00288  -0.0700   0.5565   0.5117
  -0.750   0.2427   0.00952   0.00290  -0.0704   0.5527   0.5160
  -0.500   0.2720   0.00955   0.00290  -0.0707   0.5491   0.5199
  -0.250   0.3012   0.00960   0.00291  -0.0711   0.5456   0.5236
   0.000   0.3309   0.00961   0.00293  -0.0715   0.5423   0.5272
   0.250   0.3603   0.00962   0.00297  -0.0719   0.5384   0.5309
   0.500   0.3895   0.00965   0.00300  -0.0722   0.5343   0.5346
   0.750   0.4185   0.00970   0.00303  -0.0725   0.5304   0.5383
   1.000   0.4475   0.00977   0.00307  -0.0728   0.5271   0.5420
   1.250   0.4770   0.00980   0.00312  -0.0732   0.5239   0.5457
   1.500   0.5061   0.00982   0.00319  -0.0735   0.5203   0.5497
   1.750   0.5351   0.00987   0.00326  -0.0738   0.5165   0.5538
   2.000   0.5638   0.00994   0.00332  -0.0741   0.5125   0.5578
   2.250   0.5923   0.01003   0.00338  -0.0743   0.5086   0.5616
   2.500   0.6214   0.01007   0.00346  -0.0747   0.5044   0.5651
   2.750   0.6499   0.01012   0.00355  -0.0749   0.4995   0.5690
   3.000   0.6782   0.01020   0.00364  -0.0751   0.4951   0.5731
   3.250   0.7061   0.01031   0.00373  -0.0752   0.4910   0.5776
   3.500   0.7349   0.01037   0.00383  -0.0755   0.4873   0.5820
   3.750   0.7633   0.01044   0.00394  -0.0757   0.4830   0.5861
   4.000   0.7911   0.01053   0.00406  -0.0759   0.4787   0.5904
   4.250   0.8186   0.01064   0.00418  -0.0759   0.4745   0.5948
   4.500   0.8464   0.01074   0.00431  -0.0761   0.4707   0.5992
   4.750   0.8744   0.01084   0.00444  -0.0762   0.4663   0.6032
   5.000   0.9016   0.01094   0.00459  -0.0763   0.4617   0.6073
   5.250   0.9278   0.01108   0.00473  -0.0761   0.4562   0.6119
   5.500   0.9544   0.01119   0.00489  -0.0761   0.4492   0.6170
   5.750   0.9797   0.01135   0.00505  -0.0758   0.4411   0.6219
   6.000   1.0052   0.01151   0.00522  -0.0756   0.4354   0.6264
   6.250   1.0312   0.01164   0.00542  -0.0754   0.4297   0.6310
   6.500   1.0555   0.01182   0.00562  -0.0750   0.4233   0.6358
   6.750   1.0798   0.01201   0.00583  -0.0746   0.4172   0.6408
   7.000   1.1038   0.01220   0.00604  -0.0741   0.4097   0.6456
   7.250   1.1249   0.01245   0.00631  -0.0732   0.4017   0.6508
   7.500   1.1476   0.01264   0.00655  -0.0725   0.3926   0.6563
   7.750   1.1664   0.01294   0.00684  -0.0712   0.3821   0.6615
   8.000   1.1806   0.01326   0.00715  -0.0691   0.3680   0.6663
   8.250   1.1897   0.01370   0.00756  -0.0662   0.3487   0.6717
   8.500   1.1928   0.01442   0.00820  -0.0626   0.3242   0.6777
   8.750   1.1943   0.01532   0.00901  -0.0591   0.3028   0.6835
   9.000   1.1957   0.01634   0.00996  -0.0559   0.2835   0.6887
   9.250   1.2005   0.01733   0.01092  -0.0534   0.2671   0.6945
   9.500   1.2050   0.01842   0.01198  -0.0510   0.2513   0.7009
   9.750   1.2078   0.01969   0.01319  -0.0487   0.2346   0.7069
  10.000   1.2108   0.02101   0.01450  -0.0466   0.2192   0.7131
  10.250   1.2123   0.02252   0.01598  -0.0445   0.2033   0.7197
  10.500   1.2147   0.02406   0.01749  -0.0426   0.1890   0.7258
  10.750   1.2167   0.02568   0.01909  -0.0409   0.1759   0.7319
  11.000   1.2198   0.02730   0.02071  -0.0394   0.1646   0.7391
  11.250   1.2228   0.02901   0.02241  -0.0380   0.1547   0.7461
  11.500   1.2254   0.03077   0.02419  -0.0367   0.1450   0.7529
  11.750   1.2299   0.03247   0.02592  -0.0357   0.1365   0.7603
  12.000   1.2330   0.03435   0.02780  -0.0346   0.1280   0.7671
  12.250   1.2368   0.03622   0.02971  -0.0337   0.1199   0.7748
  12.500   1.2394   0.03828   0.03178  -0.0329   0.1111   0.7832
  12.750   1.2424   0.04035   0.03387  -0.0322   0.1038   0.7917
  13.000   1.2436   0.04264   0.03617  -0.0316   0.0951   0.8008
  13.250   1.2460   0.04489   0.03844  -0.0310   0.0873   0.8099
  13.500   1.2498   0.04705   0.04064  -0.0306   0.0812   0.8204
  13.750   1.2519   0.04941   0.04305  -0.0302   0.0753   0.8320
  14.000   1.2549   0.05169   0.04538  -0.0299   0.0699   0.8456
  14.250   1.2581   0.05394   0.04770  -0.0295   0.0655   0.8625
  14.500   1.2589   0.05628   0.05014  -0.0289   0.0611   0.8890
  15.000   1.2680   0.06112   0.05511  -0.0294   0.0536   1.0000
  15.250   1.2725   0.06369   0.05771  -0.0298   0.0505   1.0000
  15.500   1.2765   0.06634   0.06038  -0.0301   0.0476   1.0000
  15.750   1.2809   0.06901   0.06308  -0.0306   0.0452   1.0000
  16.000   1.2844   0.07179   0.06589  -0.0311   0.0430   1.0000
  16.250   1.2888   0.07454   0.06868  -0.0317   0.0411   1.0000
  16.500   1.2924   0.07740   0.07157  -0.0323   0.0392   1.0000
  16.750   1.2956   0.08038   0.07460  -0.0331   0.0379   1.0000
  17.000   1.3004   0.08316   0.07743  -0.0338   0.0365   1.0000
  17.250   1.3031   0.08626   0.08057  -0.0347   0.0353   1.0000
  17.500   1.3055   0.08943   0.08378  -0.0356   0.0342   1.0000
  17.750   1.3086   0.09255   0.08697  -0.0366   0.0334   1.0000
  18.000   1.3124   0.09560   0.09008  -0.0376   0.0323   1.0000
  18.250   1.3149   0.09884   0.09338  -0.0387   0.0315   1.0000
  18.500   1.3166   0.10223   0.09682  -0.0399   0.0307   1.0000
<< Back to NACA 63(4)-421 (naca634421-il)

Polar data table (+)

Polar graphs


<< Back to NACA 63(4)-421 (naca634421-il)