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

NACA 65(3)-618 (naca653618-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA 65(3)-618 (naca653618-il)
Reynolds number: 200,000
Max Cl/Cd: 70.19 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca653618-il-200000-n5.txt
Download as CSV file: xf-naca653618-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 65(3)-618                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -14.000  -0.5379   0.07121   0.06695  -0.1013   0.9812   0.0264
 -13.750  -0.5693   0.06200   0.05741  -0.1092   0.9725   0.0264
 -13.500  -0.5886   0.05524   0.05031  -0.1148   0.9635   0.0266
 -13.250  -0.5999   0.04982   0.04451  -0.1194   0.9543   0.0269
 -13.000  -0.6057   0.04518   0.03946  -0.1230   0.9444   0.0273
 -12.750  -0.6110   0.04131   0.03509  -0.1255   0.9321   0.0278
 -12.500  -0.5928   0.03934   0.03302  -0.1274   0.9239   0.0283
 -12.250  -0.5770   0.03790   0.03150  -0.1284   0.9136   0.0288
 -12.000  -0.5643   0.03626   0.02969  -0.1289   0.9038   0.0292
 -11.750  -0.5518   0.03483   0.02808  -0.1289   0.8941   0.0298
 -11.500  -0.5418   0.03338   0.02643  -0.1281   0.8845   0.0304
 -11.250  -0.5300   0.03194   0.02475  -0.1273   0.8757   0.0309
 -11.000  -0.5192   0.03069   0.02327  -0.1260   0.8669   0.0315
 -10.750  -0.5078   0.02955   0.02185  -0.1246   0.8588   0.0322
 -10.500  -0.4907   0.02845   0.02061  -0.1238   0.8522   0.0329
 -10.250  -0.4711   0.02755   0.01968  -0.1233   0.8453   0.0334
 -10.000  -0.4510   0.02670   0.01874  -0.1227   0.8395   0.0341
  -9.750  -0.4319   0.02590   0.01785  -0.1219   0.8329   0.0347
  -9.500  -0.4123   0.02514   0.01699  -0.1212   0.8264   0.0354
  -9.250  -0.3915   0.02442   0.01613  -0.1205   0.8213   0.0363
  -9.000  -0.3727   0.02378   0.01540  -0.1195   0.8151   0.0372
  -8.750  -0.3528   0.02317   0.01466  -0.1186   0.8094   0.0379
  -8.500  -0.3311   0.02239   0.01388  -0.1181   0.8047   0.0386
  -8.250  -0.3141   0.02179   0.01328  -0.1168   0.7991   0.0393
  -8.000  -0.2986   0.02126   0.01272  -0.1154   0.7930   0.0400
  -7.750  -0.2815   0.02072   0.01212  -0.1142   0.7880   0.0408
  -7.500  -0.2643   0.02020   0.01154  -0.1130   0.7832   0.0419
  -7.250  -0.2474   0.01975   0.01104  -0.1117   0.7777   0.0432
  -7.000  -0.2299   0.01927   0.01049  -0.1105   0.7730   0.0444
  -6.750  -0.2126   0.01871   0.00990  -0.1094   0.7690   0.0458
  -6.500  -0.1948   0.01827   0.00944  -0.1084   0.7642   0.0473
  -6.250  -0.1760   0.01786   0.00898  -0.1074   0.7591   0.0489
  -6.000  -0.1553   0.01747   0.00851  -0.1066   0.7547   0.0510
  -5.750  -0.1340   0.01702   0.00802  -0.1061   0.7511   0.0538
  -5.500  -0.1129   0.01668   0.00766  -0.1054   0.7468   0.0581
  -5.250  -0.0916   0.01630   0.00730  -0.1048   0.7425   0.0648
  -5.000  -0.0692   0.01589   0.00692  -0.1044   0.7387   0.0777
  -4.750  -0.0471   0.01533   0.00648  -0.1041   0.7354   0.1121
  -4.500  -0.0273   0.01447   0.00602  -0.1038   0.7319   0.2020
  -4.250  -0.0095   0.01334   0.00553  -0.1036   0.7274   0.3486
  -4.000   0.0128   0.01275   0.00558  -0.1033   0.7235   0.4961
  -3.750   0.0405   0.01276   0.00561  -0.1034   0.7202   0.5414
  -3.500   0.0690   0.01286   0.00568  -0.1035   0.7175   0.5715
  -3.250   0.0959   0.01315   0.00601  -0.1031   0.7144   0.6060
  -3.000   0.1222   0.01350   0.00635  -0.1026   0.7108   0.6308
  -2.750   0.1483   0.01372   0.00661  -0.1019   0.7073   0.6406
  -2.500   0.1769   0.01372   0.00650  -0.1023   0.7041   0.6466
  -2.250   0.2060   0.01370   0.00637  -0.1028   0.7013   0.6502
  -2.000   0.2350   0.01371   0.00632  -0.1031   0.6988   0.6528
  -1.750   0.2615   0.01374   0.00634  -0.1031   0.6954   0.6557
  -1.500   0.2890   0.01377   0.00633  -0.1032   0.6922   0.6589
  -1.250   0.3173   0.01378   0.00629  -0.1036   0.6893   0.6624
  -1.000   0.3465   0.01377   0.00620  -0.1042   0.6865   0.6658
  -0.750   0.3755   0.01377   0.00615  -0.1046   0.6839   0.6685
  -0.500   0.4044   0.01381   0.00615  -0.1050   0.6815   0.6710
  -0.250   0.4304   0.01388   0.00625  -0.1049   0.6782   0.6738
   0.000   0.4575   0.01394   0.00631  -0.1050   0.6753   0.6766
   0.250   0.4855   0.01399   0.00635  -0.1053   0.6725   0.6797
   0.500   0.5143   0.01404   0.00636  -0.1058   0.6699   0.6833
   0.750   0.5434   0.01408   0.00637  -0.1063   0.6675   0.6865
   1.000   0.5727   0.01413   0.00641  -0.1067   0.6653   0.6889
   1.250   0.5984   0.01424   0.00657  -0.1066   0.6623   0.6916
   1.500   0.6245   0.01435   0.00673  -0.1066   0.6594   0.6945
   1.750   0.6516   0.01445   0.00686  -0.1067   0.6565   0.6979
   2.000   0.6797   0.01453   0.00694  -0.1071   0.6538   0.7017
   2.250   0.7084   0.01461   0.00703  -0.1075   0.6513   0.7051
   2.500   0.7370   0.01469   0.00714  -0.1078   0.6492   0.7078
   2.750   0.7643   0.01482   0.00731  -0.1080   0.6469   0.7109
   3.000   0.7883   0.01499   0.00758  -0.1076   0.6435   0.7143
   3.250   0.8142   0.01513   0.00778  -0.1076   0.6403   0.7181
   3.500   0.8417   0.01526   0.00794  -0.1079   0.6375   0.7221
   3.750   0.8688   0.01536   0.00811  -0.1079   0.6349   0.7253
   4.000   0.8975   0.01545   0.00825  -0.1083   0.6325   0.7288
   4.250   0.9236   0.01561   0.00848  -0.1082   0.6296   0.7328
   4.500   0.9456   0.01581   0.00879  -0.1075   0.6250   0.7372
   4.750   0.9712   0.01592   0.00897  -0.1074   0.6207   0.7413
   5.000   0.9985   0.01596   0.00907  -0.1074   0.6170   0.7446
   5.250   1.0260   0.01604   0.00922  -0.1075   0.6133   0.7486
   5.500   1.0446   0.01625   0.00958  -0.1061   0.6076   0.7536
   6.000   1.0941   0.01629   0.00976  -0.1052   0.5953   0.7628
   6.250   1.1108   0.01637   0.00996  -0.1032   0.5862   0.7676
   6.500   1.1297   0.01637   0.01001  -0.1016   0.5755   0.7730
   6.750   1.1450   0.01635   0.01003  -0.0993   0.5608   0.7783
   7.000   1.1526   0.01642   0.01015  -0.0956   0.5440   0.7834
   7.250   1.1583   0.01662   0.01038  -0.0917   0.5249   0.7901
   7.500   1.1655   0.01695   0.01070  -0.0883   0.5025   0.7968
   7.750   1.1703   0.01741   0.01114  -0.0845   0.4747   0.8035
   8.000   1.1715   0.01814   0.01173  -0.0806   0.4383   0.8115
   8.250   1.1641   0.01928   0.01268  -0.0755   0.3971   0.8187
   8.500   1.1542   0.02082   0.01402  -0.0707   0.3580   0.8275
   8.750   1.1428   0.02261   0.01564  -0.0661   0.3203   0.8358
   9.000   1.1331   0.02459   0.01745  -0.0622   0.2833   0.8457
   9.250   1.1235   0.02663   0.01936  -0.0584   0.2482   0.8556
   9.500   1.1153   0.02878   0.02135  -0.0552   0.2141   0.8668
   9.750   1.1095   0.03087   0.02333  -0.0523   0.1830   0.8794
  10.000   1.1035   0.03299   0.02532  -0.0495   0.1521   0.8941
  10.250   1.0998   0.03502   0.02724  -0.0471   0.1242   0.9128
  10.500   1.0973   0.03706   0.02919  -0.0451   0.0980   0.9419
  11.000   1.1018   0.04117   0.03309  -0.0429   0.0611   1.0000
  11.250   1.1079   0.04320   0.03507  -0.0423   0.0506   1.0000
  11.500   1.1151   0.04515   0.03701  -0.0417   0.0444   1.0000
  11.750   1.1222   0.04716   0.03901  -0.0413   0.0402   1.0000
  12.000   1.1306   0.04908   0.04098  -0.0409   0.0370   1.0000
  12.250   1.1372   0.05121   0.04311  -0.0405   0.0347   1.0000
  12.500   1.1459   0.05316   0.04515  -0.0402   0.0329   1.0000
  12.750   1.1531   0.05528   0.04733  -0.0399   0.0311   1.0000
  13.000   1.1579   0.05769   0.04977  -0.0396   0.0299   1.0000
  13.250   1.1651   0.05989   0.05206  -0.0395   0.0289   1.0000
  13.500   1.1721   0.06215   0.05440  -0.0393   0.0277   1.0000
  13.750   1.1783   0.06452   0.05684  -0.0393   0.0267   1.0000
  14.000   1.1836   0.06701   0.05937  -0.0393   0.0259   1.0000
  14.250   1.1875   0.06970   0.06210  -0.0393   0.0252   1.0000
  14.500   1.1949   0.07203   0.06453  -0.0393   0.0244   1.0000
  14.750   1.2013   0.07449   0.06709  -0.0395   0.0236   1.0000
  15.000   1.2074   0.07701   0.06968  -0.0397   0.0229   1.0000
  15.250   1.2133   0.07957   0.07230  -0.0399   0.0224   1.0000
  15.500   1.2187   0.08221   0.07499  -0.0402   0.0219   1.0000
  15.750   1.2240   0.08484   0.07765  -0.0405   0.0215   1.0000
  16.000   1.2307   0.08734   0.08023  -0.0407   0.0211   1.0000
  16.250   1.2378   0.08983   0.08283  -0.0411   0.0207   1.0000
  16.500   1.2449   0.09230   0.08542  -0.0414   0.0203   1.0000
  16.750   1.2517   0.09483   0.08805  -0.0418   0.0199   1.0000
  17.000   1.2581   0.09742   0.09074  -0.0423   0.0195   1.0000
  17.250   1.2645   0.10002   0.09343  -0.0429   0.0192   1.0000
  17.500   1.2704   0.10271   0.09621  -0.0435   0.0189   1.0000
  17.750   1.2762   0.10543   0.09901  -0.0443   0.0186   1.0000
  18.000   1.2818   0.10815   0.10180  -0.0451   0.0184   1.0000
  18.250   1.2877   0.11079   0.10448  -0.0459   0.0181   1.0000
  18.500   1.2933   0.11350   0.10725  -0.0467   0.0179   1.0000
  18.750   1.2943   0.11708   0.11104  -0.0480   0.0176   1.0000
  19.000   1.2943   0.12086   0.11501  -0.0495   0.0174   1.0000
  19.250   1.2931   0.12489   0.11922  -0.0513   0.0171   1.0000
<< Back to NACA 65(3)-618 (naca653618-il)

Polar data table (+)

Polar graphs


<< Back to NACA 65(3)-618 (naca653618-il)