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

NACA 64(3)-618 (naca643618-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NACA 64(3)-618 (naca643618-il)
Reynolds number: 500,000
Max Cl/Cd: 103.7 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca643618-il-500000-n5.txt
Download as CSV file: xf-naca643618-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64(3)-618                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -19.000  -0.8045   0.10280   0.09928  -0.0683   1.0000   0.0185
 -18.750  -0.8277   0.09491   0.09123  -0.0727   1.0000   0.0185
 -18.500  -0.8448   0.08828   0.08445  -0.0764   1.0000   0.0186
 -18.250  -0.8592   0.08223   0.07825  -0.0798   1.0000   0.0189
 -18.000  -0.8705   0.07700   0.07289  -0.0826   1.0000   0.0190
 -17.750  -0.8799   0.07212   0.06785  -0.0851   1.0000   0.0192
 -17.500  -0.8855   0.06803   0.06364  -0.0871   1.0000   0.0193
 -17.250  -0.8901   0.06430   0.05984  -0.0888   1.0000   0.0194
 -17.000  -0.8928   0.06090   0.05638  -0.0903   1.0000   0.0196
 -16.750  -0.8947   0.05773   0.05314  -0.0915   1.0000   0.0197
 -16.500  -0.8947   0.05487   0.05022  -0.0926   1.0000   0.0199
 -16.250  -0.8942   0.05218   0.04746  -0.0934   1.0000   0.0201
 -16.000  -0.8915   0.04980   0.04502  -0.0941   1.0000   0.0204
 -15.750  -0.8893   0.04749   0.04265  -0.0946   1.0000   0.0206
 -15.500  -0.8861   0.04538   0.04048  -0.0949   1.0000   0.0209
 -15.250  -0.8832   0.04336   0.03839  -0.0950   1.0000   0.0211
 -15.000  -0.8800   0.04150   0.03646  -0.0948   1.0000   0.0215
 -14.750  -0.8768   0.03975   0.03463  -0.0945   1.0000   0.0217
 -14.500  -0.8730   0.03815   0.03296  -0.0939   1.0000   0.0221
 -14.250  -0.8568   0.03626   0.03098  -0.0955   0.9879   0.0224
 -14.000  -0.8367   0.03444   0.02907  -0.0981   0.9750   0.0227
 -13.750  -0.8106   0.03260   0.02719  -0.1019   0.9631   0.0232
 -13.500  -0.7772   0.03096   0.02547  -0.1067   0.9531   0.0237
 -13.000  -0.7041   0.02804   0.02236  -0.1165   0.9274   0.0249
 -12.750  -0.6745   0.02687   0.02104  -0.1196   0.9101   0.0256
 -12.500  -0.6552   0.02584   0.01987  -0.1205   0.8927   0.0260
 -12.250  -0.6408   0.02491   0.01881  -0.1202   0.8770   0.0264
 -12.000  -0.6299   0.02391   0.01774  -0.1195   0.8628   0.0268
 -11.750  -0.6182   0.02303   0.01677  -0.1186   0.8506   0.0272
 -11.500  -0.6059   0.02223   0.01590  -0.1177   0.8389   0.0277
 -11.250  -0.5931   0.02149   0.01508  -0.1167   0.8289   0.0281
 -11.000  -0.5801   0.02078   0.01429  -0.1157   0.8187   0.0287
 -10.750  -0.5670   0.02008   0.01351  -0.1146   0.8096   0.0293
 -10.500  -0.5535   0.01945   0.01278  -0.1134   0.8001   0.0299
 -10.250  -0.5404   0.01881   0.01206  -0.1121   0.7916   0.0303
 -10.000  -0.5307   0.01807   0.01127  -0.1104   0.7827   0.0308
  -9.750  -0.5224   0.01747   0.01062  -0.1083   0.7747   0.0315
  -9.500  -0.5093   0.01695   0.01004  -0.1069   0.7668   0.0321
  -9.250  -0.4922   0.01651   0.00952  -0.1059   0.7595   0.0330
  -9.000  -0.4731   0.01608   0.00904  -0.1052   0.7530   0.0338
  -8.750  -0.4530   0.01568   0.00857  -0.1045   0.7463   0.0346
  -8.500  -0.4328   0.01527   0.00809  -0.1038   0.7401   0.0355
  -8.250  -0.4112   0.01485   0.00766  -0.1033   0.7335   0.0366
  -8.000  -0.3886   0.01451   0.00727  -0.1029   0.7268   0.0379
  -7.750  -0.3651   0.01421   0.00691  -0.1026   0.7207   0.0394
  -7.500  -0.3412   0.01387   0.00654  -0.1024   0.7144   0.0410
  -7.250  -0.3169   0.01356   0.00620  -0.1022   0.7082   0.0429
  -7.000  -0.2919   0.01330   0.00589  -0.1020   0.7027   0.0451
  -6.750  -0.2664   0.01301   0.00558  -0.1020   0.6970   0.0477
  -6.500  -0.2406   0.01275   0.00529  -0.1020   0.6911   0.0510
  -6.250  -0.2147   0.01251   0.00502  -0.1020   0.6858   0.0553
  -6.000  -0.1881   0.01225   0.00477  -0.1021   0.6804   0.0613
  -5.750  -0.1615   0.01200   0.00452  -0.1022   0.6748   0.0692
  -5.500  -0.1349   0.01175   0.00428  -0.1023   0.6695   0.0796
  -5.250  -0.1078   0.01148   0.00405  -0.1026   0.6645   0.0944
  -5.000  -0.0805   0.01119   0.00382  -0.1029   0.6590   0.1151
  -4.500  -0.0261   0.01047   0.00333  -0.1036   0.6485   0.1873
  -4.250   0.0016   0.00993   0.00303  -0.1044   0.6432   0.2528
  -4.000   0.0296   0.00930   0.00272  -0.1052   0.6379   0.3429
  -3.750   0.0583   0.00893   0.00260  -0.1060   0.6333   0.4278
  -3.500   0.0877   0.00887   0.00257  -0.1064   0.6289   0.4549
  -3.250   0.1170   0.00883   0.00255  -0.1068   0.6242   0.4746
  -3.000   0.1461   0.00883   0.00253  -0.1071   0.6196   0.4903
  -2.750   0.1750   0.00885   0.00252  -0.1074   0.6153   0.5023
  -2.500   0.2044   0.00885   0.00255  -0.1077   0.6113   0.5173
  -2.250   0.2337   0.00888   0.00259  -0.1081   0.6071   0.5319
  -2.000   0.2628   0.00892   0.00259  -0.1084   0.6028   0.5389
  -1.750   0.2917   0.00897   0.00256  -0.1086   0.5989   0.5423
  -1.500   0.3208   0.00898   0.00256  -0.1089   0.5953   0.5460
  -1.250   0.3500   0.00899   0.00257  -0.1093   0.5916   0.5498
  -1.000   0.3790   0.00901   0.00258  -0.1096   0.5877   0.5530
  -0.750   0.4079   0.00905   0.00258  -0.1098   0.5839   0.5557
  -0.500   0.4366   0.00911   0.00259  -0.1101   0.5802   0.5586
  -0.250   0.4658   0.00914   0.00261  -0.1104   0.5768   0.5616
   0.000   0.4948   0.00916   0.00264  -0.1107   0.5734   0.5645
   0.250   0.5237   0.00919   0.00268  -0.1110   0.5701   0.5675
   0.500   0.5524   0.00924   0.00273  -0.1113   0.5669   0.5706
   0.750   0.5810   0.00931   0.00277  -0.1115   0.5639   0.5739
   1.000   0.6098   0.00937   0.00283  -0.1118   0.5612   0.5773
   1.250   0.6388   0.00942   0.00289  -0.1122   0.5585   0.5805
   1.500   0.6676   0.00946   0.00296  -0.1125   0.5557   0.5838
   1.750   0.6963   0.00952   0.00304  -0.1127   0.5529   0.5873
   2.000   0.7248   0.00958   0.00313  -0.1130   0.5500   0.5912
   2.250   0.7531   0.00967   0.00321  -0.1132   0.5472   0.5953
   2.500   0.7814   0.00978   0.00330  -0.1134   0.5446   0.5993
   2.750   0.8100   0.00982   0.00341  -0.1137   0.5420   0.6034
   3.000   0.8384   0.00988   0.00353  -0.1139   0.5386   0.6081
   3.250   0.8664   0.00996   0.00363  -0.1140   0.5347   0.6129
   3.500   0.8942   0.01006   0.00374  -0.1142   0.5311   0.6175
   3.750   0.9219   0.01017   0.00387  -0.1143   0.5282   0.6218
   4.000   0.9499   0.01025   0.00402  -0.1145   0.5256   0.6266
   4.250   0.9780   0.01033   0.00416  -0.1146   0.5226   0.6319
   4.500   1.0054   0.01042   0.00429  -0.1147   0.5181   0.6370
   4.750   1.0314   0.01054   0.00442  -0.1145   0.5118   0.6419
   5.000   1.0578   0.01063   0.00457  -0.1144   0.5049   0.6474
   5.250   1.0830   0.01076   0.00471  -0.1140   0.4962   0.6532
   5.500   1.1083   0.01088   0.00487  -0.1137   0.4872   0.6586
   5.750   1.1332   0.01102   0.00504  -0.1133   0.4794   0.6644
   6.000   1.1583   0.01117   0.00523  -0.1129   0.4716   0.6707
   6.500   1.2016   0.01161   0.00567  -0.1110   0.4388   0.6834
   6.750   1.2193   0.01195   0.00595  -0.1094   0.4112   0.6905
   7.000   1.2284   0.01256   0.00638  -0.1063   0.3714   0.6971
   7.250   1.2310   0.01329   0.00697  -0.1021   0.3375   0.7039
   7.500   1.2333   0.01418   0.00771  -0.0981   0.3035   0.7112
   7.750   1.2348   0.01517   0.00856  -0.0942   0.2701   0.7179
   8.000   1.2359   0.01624   0.00951  -0.0905   0.2390   0.7254
   8.250   1.2370   0.01741   0.01056  -0.0870   0.2110   0.7330
   8.500   1.2396   0.01859   0.01168  -0.0840   0.1875   0.7404
   8.750   1.2424   0.01985   0.01287  -0.0812   0.1659   0.7486
   9.000   1.2457   0.02118   0.01414  -0.0787   0.1457   0.7564
   9.250   1.2473   0.02268   0.01557  -0.0762   0.1266   0.7651
   9.500   1.2505   0.02419   0.01704  -0.0740   0.1097   0.7738
   9.750   1.2544   0.02570   0.01854  -0.0721   0.0957   0.7839
  10.000   1.2587   0.02727   0.02009  -0.0703   0.0834   0.7938
  10.250   1.2644   0.02880   0.02163  -0.0688   0.0739   0.8045
  10.500   1.2700   0.03037   0.02322  -0.0673   0.0655   0.8154
  10.750   1.2757   0.03197   0.02485  -0.0659   0.0583   0.8274
  11.000   1.2809   0.03365   0.02656  -0.0646   0.0518   0.8408
  11.250   1.2870   0.03524   0.02821  -0.0633   0.0471   0.8560
  11.750   1.2958   0.03846   0.03160  -0.0603   0.0391   0.9101
  12.000   1.3017   0.04009   0.03331  -0.0593   0.0362   1.0000
  12.250   1.3099   0.04190   0.03515  -0.0588   0.0337   1.0000
  12.500   1.3176   0.04380   0.03707  -0.0583   0.0314   1.0000
  12.750   1.3257   0.04571   0.03901  -0.0579   0.0296   1.0000
  13.000   1.3336   0.04768   0.04101  -0.0576   0.0280   1.0000
  13.250   1.3407   0.04974   0.04311  -0.0573   0.0265   1.0000
  13.500   1.3485   0.05178   0.04520  -0.0571   0.0252   1.0000
  13.750   1.3564   0.05385   0.04731  -0.0569   0.0241   1.0000
  14.000   1.3626   0.05614   0.04963  -0.0568   0.0229   1.0000
  14.250   1.3696   0.05836   0.05190  -0.0567   0.0220   1.0000
  14.500   1.3766   0.06062   0.05423  -0.0567   0.0211   1.0000
  14.750   1.3833   0.06294   0.05660  -0.0567   0.0202   1.0000
  15.000   1.3884   0.06550   0.05920  -0.0568   0.0194   1.0000
  15.250   1.3944   0.06798   0.06174  -0.0570   0.0187   1.0000
  15.500   1.4002   0.07054   0.06437  -0.0572   0.0180   1.0000
  15.750   1.4058   0.07312   0.06702  -0.0575   0.0174   1.0000
  16.000   1.4101   0.07594   0.06989  -0.0579   0.0168   1.0000
  16.250   1.4139   0.07884   0.07285  -0.0583   0.0163   1.0000
  16.500   1.4174   0.08183   0.07591  -0.0588   0.0159   1.0000
  16.750   1.4220   0.08471   0.07886  -0.0594   0.0154   1.0000
  17.000   1.4253   0.08779   0.08202  -0.0600   0.0149   1.0000
  17.250   1.4288   0.09087   0.08518  -0.0607   0.0145   1.0000
  17.500   1.4309   0.09419   0.08856  -0.0616   0.0142   1.0000
  17.750   1.4328   0.09758   0.09201  -0.0625   0.0138   1.0000
  18.000   1.4326   0.10132   0.09583  -0.0636   0.0135   1.0000
  18.250   1.4343   0.10479   0.09938  -0.0646   0.0133   1.0000
  18.500   1.4352   0.10842   0.10310  -0.0658   0.0131   1.0000
  18.750   1.4363   0.11202   0.10679  -0.0671   0.0128   1.0000
  19.000   1.4363   0.11588   0.11074  -0.0685   0.0126   1.0000
  19.250   1.4365   0.11969   0.11464  -0.0700   0.0124   1.0000
<< Back to NACA 64(3)-618 (naca643618-il)

Polar data table (+)

Polar graphs


<< Back to NACA 64(3)-618 (naca643618-il)