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 (naca633418-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NACA 63 (naca633418-il)
Reynolds number: 500,000
Max Cl/Cd: 99.17 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca633418-il-500000.txt
Download as CSV file: xf-naca633418-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 63                                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -19.500  -0.9281   0.10255   0.09878  -0.0532   1.0000   0.0242
 -19.250  -0.9411   0.09683   0.09294  -0.0562   1.0000   0.0244
 -19.000  -0.9484   0.09213   0.08815  -0.0586   1.0000   0.0245
 -18.750  -0.9513   0.08818   0.08414  -0.0607   1.0000   0.0248
 -18.500  -0.9543   0.08429   0.08020  -0.0627   1.0000   0.0250
 -18.250  -0.9577   0.08036   0.07619  -0.0647   1.0000   0.0253
 -18.000  -0.9613   0.07648   0.07222  -0.0666   1.0000   0.0255
 -17.750  -0.9646   0.07274   0.06838  -0.0683   1.0000   0.0257
 -17.500  -0.9673   0.06919   0.06473  -0.0699   1.0000   0.0259
 -17.250  -0.9696   0.06572   0.06116  -0.0714   1.0000   0.0262
 -17.000  -0.9700   0.06261   0.05794  -0.0726   1.0000   0.0265
 -16.750  -0.9696   0.05970   0.05493  -0.0735   1.0000   0.0268
 -16.500  -0.9685   0.05691   0.05203  -0.0745   1.0000   0.0271
 -16.250  -0.9662   0.05433   0.04934  -0.0751   1.0000   0.0273
 -16.000  -0.9631   0.05191   0.04682  -0.0757   1.0000   0.0276
 -15.750  -0.9603   0.04949   0.04428  -0.0764   1.0000   0.0279
 -15.500  -0.9543   0.04755   0.04227  -0.0762   1.0000   0.0282
 -15.250  -0.9474   0.04580   0.04052  -0.0759   1.0000   0.0287
 -15.000  -0.9401   0.04408   0.03879  -0.0759   1.0000   0.0291
 -14.750  -0.9330   0.04236   0.03704  -0.0760   1.0000   0.0297
 -14.500  -0.9257   0.04071   0.03535  -0.0759   1.0000   0.0302
 -14.250  -0.9182   0.03911   0.03369  -0.0758   1.0000   0.0307
 -14.000  -0.9102   0.03758   0.03210  -0.0756   1.0000   0.0312
 -13.750  -0.9020   0.03610   0.03055  -0.0752   1.0000   0.0318
 -13.500  -0.8930   0.03472   0.02911  -0.0748   1.0000   0.0322
 -13.250  -0.8862   0.03326   0.02761  -0.0740   1.0000   0.0328
 -13.000  -0.8797   0.03182   0.02619  -0.0732   1.0000   0.0335
 -12.750  -0.8719   0.03053   0.02490  -0.0725   1.0000   0.0341
 -12.500  -0.8638   0.02932   0.02367  -0.0717   1.0000   0.0348
 -12.250  -0.8564   0.02816   0.02250  -0.0706   1.0000   0.0356
 -12.000  -0.8433   0.02701   0.02131  -0.0705   0.9902   0.0365
 -11.750  -0.8078   0.02546   0.01969  -0.0751   0.9696   0.0380
 -11.500  -0.7689   0.02392   0.01814  -0.0804   0.9530   0.0399
 -11.250  -0.7304   0.02275   0.01688  -0.0849   0.9333   0.0418
 -11.000  -0.7070   0.02180   0.01577  -0.0862   0.9099   0.0433
 -10.750  -0.6997   0.02065   0.01454  -0.0850   0.8897   0.0447
 -10.500  -0.6894   0.01984   0.01366  -0.0837   0.8749   0.0464
 -10.250  -0.6785   0.01912   0.01285  -0.0822   0.8626   0.0480
 -10.000  -0.6669   0.01847   0.01208  -0.0806   0.8516   0.0497
  -9.750  -0.6645   0.01752   0.01111  -0.0781   0.8405   0.0517
  -9.250  -0.6398   0.01653   0.00997  -0.0747   0.8229   0.0564
  -9.000  -0.6263   0.01587   0.00928  -0.0732   0.8150   0.0597
  -8.750  -0.6070   0.01543   0.00880  -0.0723   0.8076   0.0635
  -8.500  -0.5882   0.01490   0.00825  -0.0714   0.8004   0.0683
  -8.250  -0.5666   0.01453   0.00782  -0.0708   0.7941   0.0737
  -8.000  -0.5458   0.01399   0.00732  -0.0702   0.7871   0.0814
  -7.750  -0.5238   0.01353   0.00686  -0.0697   0.7805   0.0913
  -7.500  -0.5010   0.01307   0.00644  -0.0694   0.7744   0.1048
  -7.250  -0.4775   0.01260   0.00603  -0.0691   0.7679   0.1232
  -7.000  -0.4545   0.01205   0.00558  -0.0689   0.7618   0.1503
  -6.750  -0.4309   0.01149   0.00516  -0.0687   0.7558   0.1860
  -6.500  -0.4072   0.01085   0.00473  -0.0687   0.7495   0.2335
  -6.250  -0.3830   0.01021   0.00431  -0.0688   0.7438   0.2890
  -6.000  -0.3575   0.00971   0.00400  -0.0689   0.7382   0.3443
  -5.750  -0.3302   0.00940   0.00382  -0.0691   0.7320   0.3864
  -5.500  -0.3022   0.00923   0.00369  -0.0693   0.7263   0.4151
  -5.250  -0.2736   0.00916   0.00358  -0.0695   0.7211   0.4360
  -5.000  -0.2447   0.00907   0.00351  -0.0698   0.7152   0.4527
  -4.750  -0.2159   0.00901   0.00343  -0.0700   0.7095   0.4663
  -4.500  -0.1869   0.00901   0.00336  -0.0702   0.7042   0.4781
  -4.250  -0.1576   0.00899   0.00331  -0.0705   0.6988   0.4896
  -4.000  -0.1286   0.00895   0.00329  -0.0707   0.6933   0.4995
  -3.750  -0.0993   0.00897   0.00322  -0.0710   0.6882   0.5088
  -3.500  -0.0702   0.00897   0.00322  -0.0712   0.6829   0.5180
  -3.250  -0.0409   0.00897   0.00319  -0.0715   0.6773   0.5268
  -3.000  -0.0118   0.00898   0.00318  -0.0717   0.6723   0.5352
  -2.750   0.0177   0.00905   0.00316  -0.0720   0.6676   0.5430
  -2.500   0.0467   0.00901   0.00317  -0.0722   0.6624   0.5497
  -2.250   0.0761   0.00903   0.00315  -0.0725   0.6572   0.5561
  -2.000   0.1054   0.00905   0.00310  -0.0727   0.6523   0.5619
  -1.750   0.1345   0.00904   0.00312  -0.0730   0.6474   0.5672
  -1.500   0.1638   0.00905   0.00312  -0.0733   0.6424   0.5726
  -1.250   0.1934   0.00909   0.00309  -0.0736   0.6377   0.5778
  -1.000   0.2223   0.00911   0.00309  -0.0738   0.6331   0.5827
  -0.750   0.2515   0.00910   0.00312  -0.0741   0.6283   0.5876
  -0.500   0.2809   0.00912   0.00312  -0.0744   0.6232   0.5929
  -0.250   0.3102   0.00915   0.00310  -0.0747   0.6187   0.5976
   0.000   0.3392   0.00919   0.00315  -0.0749   0.6144   0.6023
   0.250   0.3683   0.00921   0.00320  -0.0752   0.6097   0.6073
   0.500   0.3976   0.00924   0.00321  -0.0755   0.6048   0.6123
   0.750   0.4267   0.00928   0.00323  -0.0757   0.6004   0.6170
   1.000   0.4556   0.00934   0.00330  -0.0760   0.5961   0.6219
   1.250   0.4846   0.00937   0.00337  -0.0762   0.5913   0.6271
   1.500   0.5138   0.00942   0.00339  -0.0765   0.5866   0.6320
   1.750   0.5426   0.00947   0.00345  -0.0767   0.5822   0.6368
   2.000   0.5713   0.00953   0.00355  -0.0769   0.5776   0.6420
   2.250   0.6002   0.00957   0.00362  -0.0772   0.5726   0.6475
   2.500   0.6290   0.00963   0.00366  -0.0774   0.5678   0.6524
   2.750   0.6576   0.00973   0.00376  -0.0776   0.5631   0.6572
   3.000   0.6860   0.00976   0.00387  -0.0777   0.5584   0.6626
   3.250   0.7147   0.00983   0.00395  -0.0779   0.5533   0.6683
   3.500   0.7429   0.00990   0.00403  -0.0781   0.5484   0.6734
   3.750   0.7711   0.00999   0.00416  -0.0782   0.5435   0.6786
   4.000   0.7993   0.01004   0.00427  -0.0783   0.5381   0.6843
   4.250   0.8274   0.01012   0.00434  -0.0784   0.5323   0.6897
   4.500   0.8548   0.01020   0.00447  -0.0784   0.5260   0.6950
   4.750   0.8823   0.01025   0.00458  -0.0784   0.5191   0.7010
   5.000   0.9100   0.01038   0.00468  -0.0784   0.5130   0.7067
   5.250   0.9370   0.01042   0.00482  -0.0783   0.5063   0.7119
   5.500   0.9635   0.01051   0.00492  -0.0781   0.4977   0.7177
   5.750   0.9899   0.01060   0.00504  -0.0779   0.4870   0.7240
   6.000   1.0152   0.01072   0.00517  -0.0775   0.4771   0.7297
   6.250   1.0416   0.01080   0.00534  -0.0773   0.4681   0.7357
   6.500   1.0673   0.01098   0.00550  -0.0771   0.4591   0.7420
   6.750   1.0923   0.01109   0.00568  -0.0766   0.4483   0.7478
   7.000   1.1167   0.01126   0.00588  -0.0761   0.4358   0.7543
   7.500   1.1620   0.01172   0.00635  -0.0746   0.4040   0.7673
   7.750   1.1827   0.01204   0.00664  -0.0735   0.3840   0.7742
   8.000   1.2003   0.01247   0.00700  -0.0720   0.3594   0.7812
   8.250   1.2138   0.01302   0.00746  -0.0698   0.3297   0.7886
   8.500   1.2239   0.01372   0.00801  -0.0672   0.2984   0.7968
   8.750   1.2274   0.01440   0.00861  -0.0633   0.2701   0.8049
   9.000   1.2291   0.01528   0.00937  -0.0595   0.2426   0.8146
   9.250   1.2291   0.01624   0.01026  -0.0556   0.2169   0.8247
   9.500   1.2300   0.01729   0.01124  -0.0522   0.1925   0.8362
   9.750   1.2298   0.01850   0.01237  -0.0490   0.1709   0.8495
  10.000   1.2305   0.01971   0.01356  -0.0460   0.1517   0.8651
  10.250   1.2302   0.02098   0.01484  -0.0430   0.1342   0.8851
  10.500   1.2281   0.02226   0.01614  -0.0398   0.1190   0.9196
  10.750   1.2339   0.02380   0.01766  -0.0388   0.1032   1.0000
  11.000   1.2386   0.02548   0.01927  -0.0376   0.0911   1.0000
  11.250   1.2439   0.02715   0.02090  -0.0365   0.0817   1.0000
  11.500   1.2492   0.02885   0.02258  -0.0354   0.0743   1.0000
  11.750   1.2522   0.03079   0.02448  -0.0343   0.0682   1.0000
  12.000   1.2597   0.03241   0.02613  -0.0336   0.0636   1.0000
  12.250   1.2613   0.03456   0.02826  -0.0327   0.0592   1.0000
  12.500   1.2693   0.03623   0.02998  -0.0321   0.0559   1.0000
  12.750   1.2723   0.03839   0.03214  -0.0314   0.0529   1.0000
  13.000   1.2769   0.04047   0.03426  -0.0309   0.0502   1.0000
  13.250   1.2831   0.04247   0.03631  -0.0305   0.0479   1.0000
  13.500   1.2854   0.04490   0.03875  -0.0302   0.0459   1.0000
  13.750   1.2882   0.04734   0.04123  -0.0299   0.0440   1.0000
  14.000   1.2947   0.04947   0.04343  -0.0298   0.0423   1.0000
  14.250   1.2991   0.05186   0.04586  -0.0298   0.0407   1.0000
  14.500   1.3000   0.05468   0.04870  -0.0298   0.0395   1.0000
  14.750   1.3013   0.05753   0.05161  -0.0299   0.0383   1.0000
  15.000   1.3079   0.05984   0.05400  -0.0301   0.0371   1.0000
  15.250   1.3129   0.06238   0.05659  -0.0304   0.0359   1.0000
  15.500   1.3161   0.06517   0.05942  -0.0308   0.0348   1.0000
  15.750   1.3158   0.06840   0.06268  -0.0313   0.0339   1.0000
  16.000   1.3174   0.07148   0.06582  -0.0318   0.0331   1.0000
  16.250   1.3225   0.07419   0.06862  -0.0323   0.0323   1.0000
  16.500   1.3265   0.07706   0.07157  -0.0330   0.0315   1.0000
  16.750   1.3298   0.08006   0.07463  -0.0337   0.0307   1.0000
  17.000   1.3325   0.08318   0.07780  -0.0345   0.0300   1.0000
  17.250   1.3333   0.08658   0.08123  -0.0355   0.0294   1.0000
<< Back to NACA 63 (naca633418-il)

Polar data table (+)

Polar graphs


<< Back to NACA 63 (naca633418-il)