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

NACA 63-415 AIRFOIL (n63415-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NACA 63-415 AIRFOIL (n63415-il)
Reynolds number: 1,000,000
Max Cl/Cd: 118.71 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n63415-il-1000000.txt
Download as CSV file: xf-n63415-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 63-415 AIRFOIL                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -19.000  -0.8646   0.12321   0.12092  -0.0296   1.0000   0.0126
 -18.750  -0.9113   0.10995   0.10745  -0.0369   1.0000   0.0125
 -18.500  -0.9426   0.10016   0.09750  -0.0423   1.0000   0.0125
 -18.250  -0.9666   0.09203   0.08924  -0.0468   1.0000   0.0125
 -18.000  -0.9822   0.08548   0.08257  -0.0505   1.0000   0.0125
 -17.750  -0.9996   0.07888   0.07585  -0.0541   1.0000   0.0125
 -17.500  -1.0116   0.07328   0.07015  -0.0573   1.0000   0.0126
 -17.250  -1.0199   0.06841   0.06518  -0.0599   1.0000   0.0127
 -17.000  -1.0288   0.06362   0.06029  -0.0625   1.0000   0.0129
 -16.750  -1.0375   0.05907   0.05562  -0.0649   1.0000   0.0129
 -16.500  -1.0407   0.05535   0.05182  -0.0668   1.0000   0.0130
 -16.250  -1.0452   0.05161   0.04798  -0.0685   1.0000   0.0132
 -16.000  -1.0464   0.04846   0.04474  -0.0699   1.0000   0.0133
 -15.750  -1.0484   0.04536   0.04154  -0.0711   1.0000   0.0135
 -15.500  -1.0478   0.04265   0.03874  -0.0720   1.0000   0.0136
 -15.250  -1.0453   0.04022   0.03622  -0.0727   1.0000   0.0138
 -15.000  -1.0394   0.03818   0.03410  -0.0733   1.0000   0.0140
 -14.750  -1.0350   0.03607   0.03190  -0.0737   1.0000   0.0141
 -14.500  -1.0307   0.03402   0.02976  -0.0740   1.0000   0.0142
 -14.250  -1.0249   0.03218   0.02783  -0.0741   1.0000   0.0144
 -14.000  -1.0280   0.02963   0.02519  -0.0738   1.0000   0.0147
 -13.750  -1.0237   0.02784   0.02335  -0.0735   1.0000   0.0150
 -13.500  -1.0170   0.02634   0.02179  -0.0730   1.0000   0.0152
 -13.250  -1.0072   0.02517   0.02059  -0.0725   1.0000   0.0155
 -13.000  -0.9986   0.02401   0.01939  -0.0716   1.0000   0.0157
 -12.750  -0.9888   0.02305   0.01839  -0.0706   1.0000   0.0161
 -12.500  -0.9819   0.02207   0.01736  -0.0690   1.0000   0.0164
 -12.250  -0.9776   0.02126   0.01650  -0.0668   1.0000   0.0167
 -12.000  -0.9689   0.02041   0.01560  -0.0653   0.9977   0.0169
 -11.750  -0.9379   0.01956   0.01467  -0.0676   0.9856   0.0173
 -11.500  -0.9051   0.01835   0.01338  -0.0706   0.9768   0.0179
 -11.250  -0.8692   0.01745   0.01246  -0.0737   0.9670   0.0187
 -11.000  -0.8331   0.01684   0.01180  -0.0764   0.9538   0.0194
 -10.750  -0.8051   0.01633   0.01121  -0.0773   0.9345   0.0200
 -10.500  -0.7833   0.01592   0.01069  -0.0767   0.9163   0.0207
 -10.250  -0.7617   0.01559   0.01026  -0.0760   0.9015   0.0211
 -10.000  -0.7450   0.01485   0.00942  -0.0748   0.8876   0.0219
  -9.750  -0.7235   0.01444   0.00896  -0.0742   0.8760   0.0228
  -9.500  -0.7004   0.01410   0.00856  -0.0737   0.8660   0.0236
  -9.250  -0.6764   0.01383   0.00822  -0.0733   0.8564   0.0246
  -9.000  -0.6513   0.01359   0.00793  -0.0730   0.8475   0.0253
  -8.750  -0.6298   0.01299   0.00725  -0.0725   0.8388   0.0267
  -8.500  -0.6049   0.01266   0.00690  -0.0722   0.8303   0.0279
  -8.250  -0.5795   0.01240   0.00658  -0.0720   0.8226   0.0290
  -8.000  -0.5532   0.01216   0.00629  -0.0720   0.8151   0.0301
  -7.750  -0.5287   0.01171   0.00578  -0.0717   0.8077   0.0317
  -7.500  -0.5026   0.01140   0.00546  -0.0717   0.8006   0.0334
  -7.250  -0.4758   0.01118   0.00519  -0.0717   0.7934   0.0350
  -7.000  -0.4487   0.01100   0.00495  -0.0717   0.7868   0.0361
  -6.750  -0.4225   0.01058   0.00451  -0.0717   0.7798   0.0388
  -6.500  -0.3955   0.01037   0.00425  -0.0717   0.7730   0.0409
  -6.250  -0.3675   0.01018   0.00404  -0.0718   0.7667   0.0427
  -6.000  -0.3404   0.00987   0.00371  -0.0719   0.7600   0.0469
  -5.750  -0.3126   0.00968   0.00349  -0.0720   0.7537   0.0504
  -5.500  -0.2849   0.00939   0.00324  -0.0722   0.7470   0.0585
  -5.250  -0.2574   0.00910   0.00298  -0.0724   0.7407   0.0751
  -5.000  -0.2298   0.00870   0.00273  -0.0727   0.7345   0.1078
  -4.750  -0.2022   0.00829   0.00248  -0.0730   0.7279   0.1517
  -4.500  -0.1746   0.00784   0.00223  -0.0734   0.7219   0.2094
  -4.250  -0.1467   0.00728   0.00197  -0.0739   0.7157   0.2880
  -4.000  -0.1185   0.00686   0.00178  -0.0744   0.7094   0.3602
  -3.750  -0.0897   0.00663   0.00167  -0.0748   0.7034   0.4069
  -3.500  -0.0606   0.00649   0.00160  -0.0751   0.6971   0.4380
  -3.250  -0.0315   0.00642   0.00154  -0.0754   0.6911   0.4593
  -3.000  -0.0021   0.00636   0.00150  -0.0757   0.6852   0.4753
  -2.750   0.0272   0.00633   0.00146  -0.0760   0.6789   0.4893
  -2.500   0.0562   0.00631   0.00144  -0.0763   0.6729   0.5068
  -2.000   0.1150   0.00626   0.00141  -0.0769   0.6611   0.5369
  -1.750   0.1442   0.00626   0.00140  -0.0771   0.6554   0.5457
  -1.500   0.1737   0.00626   0.00139  -0.0774   0.6493   0.5556
  -1.250   0.2027   0.00626   0.00140  -0.0777   0.6434   0.5659
  -1.000   0.2321   0.00629   0.00140  -0.0780   0.6380   0.5732
  -0.750   0.2615   0.00627   0.00140  -0.0782   0.6320   0.5802
  -0.500   0.2905   0.00632   0.00141  -0.0785   0.6260   0.5871
  -0.250   0.3199   0.00632   0.00142  -0.0788   0.6206   0.5937
   0.000   0.3492   0.00633   0.00144  -0.0790   0.6147   0.6007
   0.250   0.3781   0.00640   0.00146  -0.0793   0.6087   0.6070
   0.500   0.4075   0.00638   0.00149  -0.0796   0.6032   0.6134
   0.750   0.4366   0.00643   0.00152  -0.0798   0.5970   0.6200
   1.000   0.4655   0.00647   0.00155  -0.0800   0.5910   0.6260
   1.250   0.4948   0.00648   0.00160  -0.0803   0.5850   0.6322
   1.500   0.5237   0.00655   0.00164  -0.0805   0.5789   0.6385
   1.750   0.5527   0.00658   0.00169  -0.0808   0.5732   0.6449
   2.000   0.5818   0.00662   0.00175  -0.0810   0.5671   0.6515
   2.250   0.6104   0.00670   0.00181  -0.0812   0.5608   0.6575
   2.500   0.6394   0.00672   0.00187  -0.0814   0.5544   0.6640
   2.750   0.6678   0.00680   0.00194  -0.0816   0.5458   0.6709
   3.000   0.6966   0.00685   0.00201  -0.0818   0.5371   0.6773
   3.250   0.7249   0.00694   0.00209  -0.0819   0.5291   0.6840
   3.750   0.7816   0.00709   0.00227  -0.0821   0.5097   0.6972
   4.000   0.8095   0.00721   0.00237  -0.0822   0.4970   0.7044
   4.250   0.8374   0.00731   0.00247  -0.0823   0.4831   0.7109
   4.500   0.8647   0.00746   0.00259  -0.0822   0.4666   0.7177
   4.750   0.8923   0.00761   0.00272  -0.0823   0.4520   0.7246
   5.000   0.9195   0.00775   0.00287  -0.0822   0.4371   0.7315
   5.250   0.9461   0.00797   0.00304  -0.0821   0.4182   0.7387
   5.500   0.9719   0.00823   0.00323  -0.0819   0.3925   0.7454
   5.750   0.9960   0.00862   0.00350  -0.0814   0.3566   0.7528
   6.000   1.0185   0.00916   0.00385  -0.0807   0.3119   0.7600
   6.250   1.0392   0.00982   0.00429  -0.0798   0.2631   0.7675
   6.500   1.0583   0.01059   0.00480  -0.0786   0.2094   0.7753
   6.750   1.0769   0.01135   0.00533  -0.0774   0.1628   0.7835
   7.000   1.0957   0.01206   0.00584  -0.0762   0.1257   0.7919
   7.250   1.1149   0.01268   0.00634  -0.0750   0.0971   0.8007
   7.500   1.1338   0.01330   0.00685  -0.0738   0.0744   0.8099
   7.750   1.1524   0.01388   0.00735  -0.0725   0.0574   0.8199
   8.000   1.1711   0.01442   0.00785  -0.0712   0.0467   0.8296
   8.250   1.1905   0.01487   0.00831  -0.0700   0.0414   0.8404
   8.500   1.2091   0.01530   0.00878  -0.0686   0.0378   0.8521
   8.750   1.2265   0.01572   0.00924  -0.0671   0.0351   0.8646
   9.000   1.2385   0.01621   0.00978  -0.0645   0.0325   0.8800
   9.250   1.2521   0.01656   0.01022  -0.0622   0.0313   0.8995
   9.500   1.2612   0.01693   0.01070  -0.0591   0.0299   0.9304
   9.750   1.2714   0.01744   0.01128  -0.0566   0.0284   1.0000
  10.000   1.2843   0.01817   0.01203  -0.0548   0.0269   1.0000
  10.250   1.3000   0.01876   0.01266  -0.0536   0.0258   1.0000
  10.500   1.3140   0.01948   0.01340  -0.0522   0.0246   1.0000
  10.750   1.3241   0.02045   0.01438  -0.0504   0.0231   1.0000
  11.000   1.3359   0.02137   0.01534  -0.0489   0.0222   1.0000
  11.250   1.3496   0.02220   0.01621  -0.0478   0.0211   1.0000
  11.500   1.3619   0.02314   0.01718  -0.0465   0.0203   1.0000
  11.750   1.3703   0.02441   0.01847  -0.0451   0.0192   1.0000
  12.000   1.3779   0.02579   0.01990  -0.0437   0.0184   1.0000
  12.250   1.3901   0.02687   0.02103  -0.0427   0.0178   1.0000
  12.500   1.4013   0.02806   0.02227  -0.0418   0.0172   1.0000
  12.750   1.4120   0.02932   0.02355  -0.0409   0.0166   1.0000
  13.000   1.4201   0.03083   0.02511  -0.0400   0.0160   1.0000
  13.250   1.4228   0.03285   0.02718  -0.0389   0.0154   1.0000
  13.500   1.4282   0.03471   0.02911  -0.0380   0.0151   1.0000
  13.750   1.4362   0.03638   0.03085  -0.0374   0.0148   1.0000
  14.000   1.4436   0.03815   0.03269  -0.0368   0.0145   1.0000
  14.250   1.4493   0.04014   0.03474  -0.0363   0.0142   1.0000
  14.500   1.4557   0.04211   0.03677  -0.0359   0.0140   1.0000
  14.750   1.4609   0.04425   0.03898  -0.0356   0.0137   1.0000
  15.000   1.4656   0.04654   0.04133  -0.0354   0.0134   1.0000
  15.250   1.4693   0.04899   0.04384  -0.0354   0.0132   1.0000
  15.500   1.4713   0.05169   0.04660  -0.0354   0.0129   1.0000
  15.750   1.4711   0.05476   0.04975  -0.0356   0.0128   1.0000
  16.000   1.4672   0.05838   0.05345  -0.0360   0.0125   1.0000
  16.250   1.4596   0.06257   0.05774  -0.0366   0.0123   1.0000
  16.500   1.4621   0.06558   0.06084  -0.0371   0.0122   1.0000
  16.750   1.4631   0.06888   0.06423  -0.0379   0.0121   1.0000
  17.000   1.4646   0.07218   0.06762  -0.0387   0.0120   1.0000
  17.250   1.4640   0.07582   0.07136  -0.0397   0.0119   1.0000
  17.500   1.4634   0.07955   0.07518  -0.0408   0.0118   1.0000
  17.750   1.4626   0.08339   0.07911  -0.0421   0.0116   1.0000
  18.000   1.4611   0.08742   0.08324  -0.0436   0.0115   1.0000
  18.250   1.4582   0.09172   0.08764  -0.0452   0.0114   1.0000
  18.500   1.4555   0.09609   0.09209  -0.0469   0.0112   1.0000
  18.750   1.4518   0.10066   0.09676  -0.0488   0.0111   1.0000
  19.000   1.4477   0.10540   0.10159  -0.0509   0.0110   1.0000
  19.250   1.4429   0.11030   0.10659  -0.0532   0.0109   1.0000
<< Back to NACA 63-415 AIRFOIL (n63415-il)

Polar data table (+)

Polar graphs


<< Back to NACA 63-415 AIRFOIL (n63415-il)