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NACA 65(2)-415 a=0.5 (naca652415a05-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA 65(2)-415 a=0.5 (naca652415a05-il)
Reynolds number: 200,000
Max Cl/Cd: 73.24 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca652415a05-il-200000-n5.txt
Download as CSV file: xf-naca652415a05-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 65(2)-415 a=0.5                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.4002   0.09038   0.08647  -0.0634   0.8536   0.0221
 -11.500  -0.4200   0.08119   0.07727  -0.0687   0.8470   0.0226
 -11.250  -0.5232   0.05746   0.05320  -0.0841   0.8397   0.0210
 -11.000  -0.5523   0.05237   0.04786  -0.0851   0.8310   0.0210
 -10.750  -0.5595   0.05023   0.04558  -0.0845   0.8240   0.0213
 -10.500  -0.5754   0.04733   0.04246  -0.0827   0.8163   0.0216
 -10.250  -0.5905   0.04472   0.03959  -0.0796   0.8104   0.0218
 -10.000  -0.5971   0.04187   0.03645  -0.0775   0.8040   0.0223
  -9.750  -0.6006   0.03881   0.03299  -0.0752   0.7985   0.0228
  -9.500  -0.6000   0.03571   0.02941  -0.0729   0.7940   0.0233
  -9.250  -0.5936   0.03283   0.02602  -0.0711   0.7885   0.0240
  -9.000  -0.5812   0.03067   0.02345  -0.0696   0.7835   0.0246
  -8.750  -0.5623   0.02965   0.02234  -0.0690   0.7794   0.0253
  -8.500  -0.5424   0.02871   0.02127  -0.0684   0.7752   0.0260
  -8.250  -0.5218   0.02760   0.01999  -0.0678   0.7707   0.0270
  -8.000  -0.5009   0.02624   0.01838  -0.0671   0.7667   0.0278
  -7.750  -0.4790   0.02496   0.01681  -0.0665   0.7633   0.0286
  -7.500  -0.4559   0.02397   0.01552  -0.0659   0.7599   0.0296
  -7.250  -0.4322   0.02286   0.01439  -0.0657   0.7557   0.0306
  -7.000  -0.4082   0.02210   0.01357  -0.0654   0.7517   0.0316
  -6.750  -0.3840   0.02132   0.01268  -0.0651   0.7482   0.0326
  -6.500  -0.3597   0.02055   0.01179  -0.0646   0.7454   0.0336
  -6.250  -0.3350   0.01986   0.01102  -0.0644   0.7415   0.0347
  -6.000  -0.3101   0.01934   0.01039  -0.0640   0.7379   0.0360
  -5.750  -0.2872   0.01852   0.00958  -0.0635   0.7347   0.0374
  -5.500  -0.2636   0.01795   0.00898  -0.0631   0.7318   0.0386
  -5.250  -0.2399   0.01744   0.00841  -0.0625   0.7294   0.0400
  -5.000  -0.2159   0.01698   0.00791  -0.0622   0.7259   0.0416
  -4.750  -0.1912   0.01661   0.00748  -0.0618   0.7223   0.0437
  -4.500  -0.1679   0.01610   0.00697  -0.0614   0.7191   0.0463
  -4.250  -0.1432   0.01575   0.00655  -0.0610   0.7163   0.0492
  -4.000  -0.1179   0.01544   0.00616  -0.0607   0.7141   0.0526
  -3.750  -0.0931   0.01510   0.00582  -0.0604   0.7114   0.0585
  -3.500  -0.0679   0.01478   0.00554  -0.0602   0.7084   0.0696
  -3.250  -0.0436   0.01436   0.00526  -0.0600   0.7055   0.1013
  -3.000  -0.0228   0.01353   0.00493  -0.0594   0.7027   0.2195
  -2.750  -0.0065   0.01235   0.00463  -0.0581   0.7001   0.4379
  -2.500   0.0158   0.01197   0.00463  -0.0571   0.6979   0.5557
  -2.250   0.0408   0.01187   0.00469  -0.0566   0.6954   0.6129
  -2.000   0.0645   0.01186   0.00491  -0.0555   0.6926   0.6759
  -1.750   0.0883   0.01197   0.00514  -0.0543   0.6900   0.7235
  -1.500   0.1145   0.01204   0.00522  -0.0538   0.6876   0.7435
  -1.250   0.1422   0.01205   0.00516  -0.0539   0.6852   0.7534
  -1.000   0.1701   0.01206   0.00512  -0.0539   0.6831   0.7598
  -0.750   0.1982   0.01208   0.00506  -0.0540   0.6812   0.7675
  -0.500   0.2254   0.01214   0.00513  -0.0540   0.6787   0.7745
  -0.250   0.2526   0.01221   0.00520  -0.0541   0.6761   0.7820
   0.000   0.2800   0.01226   0.00524  -0.0541   0.6735   0.7894
   0.250   0.3073   0.01231   0.00528  -0.0541   0.6710   0.7967
   0.500   0.3350   0.01235   0.00529  -0.0542   0.6689   0.8050
   0.750   0.3626   0.01240   0.00534  -0.0542   0.6671   0.8118
   1.000   0.3906   0.01246   0.00537  -0.0543   0.6655   0.8204
   1.250   0.4165   0.01258   0.00555  -0.0541   0.6627   0.8277
   1.500   0.4428   0.01269   0.00570  -0.0540   0.6598   0.8366
   1.750   0.4692   0.01278   0.00584  -0.0539   0.6573   0.8439
   2.000   0.4960   0.01287   0.00595  -0.0538   0.6551   0.8531
   2.250   0.5229   0.01294   0.00605  -0.0537   0.6530   0.8607
   2.500   0.5503   0.01301   0.00613  -0.0537   0.6511   0.8700
   2.750   0.5775   0.01309   0.00625  -0.0536   0.6492   0.8779
   3.000   0.6018   0.01328   0.00653  -0.0532   0.6461   0.8880
   3.250   0.6273   0.01342   0.00676  -0.0529   0.6431   0.8970
   3.500   0.6537   0.01354   0.00694  -0.0528   0.6404   0.9067
   3.750   0.6812   0.01362   0.00708  -0.0529   0.6380   0.9168
   4.000   0.7110   0.01368   0.00719  -0.0533   0.6358   0.9256
   4.250   0.7405   0.01376   0.00731  -0.0538   0.6334   0.9356
   4.500   0.7687   0.01396   0.00765  -0.0544   0.6286   0.9457
   4.750   0.8007   0.01404   0.00782  -0.0555   0.6243   0.9546
   5.000   0.8352   0.01398   0.00781  -0.0569   0.6202   0.9631
   5.250   0.8689   0.01403   0.00797  -0.0585   0.6131   0.9717
   5.500   0.9045   0.01396   0.00797  -0.0602   0.6059   0.9798
   5.750   0.9389   0.01365   0.00769  -0.0616   0.5893   0.9895
   6.000   0.9649   0.01342   0.00747  -0.0615   0.5607   1.0000
   6.250   0.9783   0.01344   0.00747  -0.0590   0.5368   1.0000
   6.500   0.9939   0.01357   0.00755  -0.0569   0.5087   1.0000
   6.750   1.0048   0.01386   0.00762  -0.0540   0.4583   1.0000
   7.000   1.0006   0.01477   0.00808  -0.0490   0.3887   1.0000
   7.250   0.9875   0.01596   0.00892  -0.0428   0.3335   1.0000
   7.500   0.9744   0.01745   0.01012  -0.0373   0.2830   1.0000
   7.750   0.9647   0.01916   0.01154  -0.0331   0.2329   1.0000
   8.000   0.9590   0.02091   0.01303  -0.0297   0.1871   1.0000
   8.250   0.9546   0.02275   0.01460  -0.0268   0.1413   1.0000
   8.500   0.9537   0.02450   0.01613  -0.0244   0.1047   1.0000
   8.750   0.9560   0.02613   0.01759  -0.0224   0.0772   1.0000
   9.000   0.9611   0.02764   0.01898  -0.0208   0.0592   1.0000
   9.250   0.9686   0.02902   0.02033  -0.0194   0.0494   1.0000
   9.500   0.9772   0.03036   0.02167  -0.0181   0.0429   1.0000
   9.750   0.9855   0.03175   0.02306  -0.0169   0.0386   1.0000
  10.000   0.9951   0.03307   0.02443  -0.0158   0.0353   1.0000
  10.250   1.0022   0.03461   0.02597  -0.0147   0.0327   1.0000
  10.500   1.0120   0.03597   0.02742  -0.0137   0.0308   1.0000
  10.750   1.0209   0.03742   0.02894  -0.0127   0.0293   1.0000
  11.000   1.0293   0.03897   0.03054  -0.0118   0.0283   1.0000
  11.250   1.0357   0.04070   0.03230  -0.0109   0.0271   1.0000
  11.500   1.0425   0.04245   0.03411  -0.0100   0.0263   1.0000
  11.750   1.0525   0.04396   0.03571  -0.0093   0.0252   1.0000
  12.000   1.0610   0.04562   0.03744  -0.0086   0.0244   1.0000
  12.250   1.0700   0.04726   0.03914  -0.0080   0.0236   1.0000
  12.500   1.0787   0.04896   0.04088  -0.0074   0.0228   1.0000
  12.750   1.0872   0.05070   0.04266  -0.0069   0.0223   1.0000
  13.000   1.0946   0.05256   0.04455  -0.0062   0.0216   1.0000
  13.250   1.1051   0.05418   0.04626  -0.0056   0.0213   1.0000
  13.500   1.1158   0.05581   0.04799  -0.0051   0.0209   1.0000
  13.750   1.1264   0.05748   0.04977  -0.0046   0.0205   1.0000
  14.000   1.1373   0.05916   0.05155  -0.0041   0.0201   1.0000
  14.250   1.1477   0.06093   0.05343  -0.0037   0.0197   1.0000
  14.500   1.1574   0.06279   0.05541  -0.0033   0.0193   1.0000
  14.750   1.1663   0.06478   0.05750  -0.0030   0.0189   1.0000
  15.000   1.1748   0.06684   0.05967  -0.0028   0.0186   1.0000
  15.250   1.1823   0.06904   0.06196  -0.0027   0.0183   1.0000
  15.500   1.1891   0.07132   0.06432  -0.0027   0.0180   1.0000
  15.750   1.1958   0.07363   0.06668  -0.0027   0.0177   1.0000
  16.000   1.1981   0.07663   0.06987  -0.0028   0.0174   1.0000
  16.250   1.1982   0.07995   0.07342  -0.0032   0.0172   1.0000
  16.500   1.1958   0.08364   0.07735  -0.0038   0.0170   1.0000
  16.750   1.1920   0.08765   0.08158  -0.0045   0.0168   1.0000
  17.000   1.1861   0.09203   0.08619  -0.0056   0.0167   1.0000
  17.250   1.1779   0.09687   0.09126  -0.0071   0.0166   1.0000
  17.500   1.1674   0.10223   0.09686  -0.0089   0.0165   1.0000
  17.750   1.1550   0.10809   0.10295  -0.0113   0.0164   1.0000
  18.000   1.1401   0.11463   0.10972  -0.0143   0.0163   1.0000
  18.250   1.1239   0.12168   0.11700  -0.0179   0.0164   1.0000
  18.500   1.1042   0.12986   0.12542  -0.0224   0.0163   1.0000
  18.750   1.0813   0.13928   0.13506  -0.0280   0.0164   1.0000
  19.000   1.0532   0.15068   0.14670  -0.0352   0.0165   1.0000
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