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NACA 65(3)-218 (naca653218-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NACA 65(3)-218 (naca653218-il)
Reynolds number: 100,000
Max Cl/Cd: 35.2 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca653218-il-100000.txt
Download as CSV file: xf-naca653218-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 65(3)-218                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.4243   0.11396   0.10881  -0.0452   1.0000   0.1905
 -12.000  -0.7864   0.06298   0.05686  -0.0696   1.0000   0.0806
 -11.750  -0.8080   0.06091   0.05474  -0.0655   1.0000   0.0799
 -11.500  -0.8444   0.06093   0.05478  -0.0578   1.0000   0.0796
 -11.250  -0.8813   0.06117   0.05504  -0.0497   1.0000   0.0795
 -11.000  -0.9096   0.06027   0.05407  -0.0434   1.0000   0.0789
 -10.750  -0.9305   0.05850   0.05216  -0.0384   0.9994   0.0781
 -10.500  -0.9224   0.05380   0.04695  -0.0395   0.9919   0.0760
 -10.250  -0.9108   0.04970   0.04226  -0.0402   0.9844   0.0745
 -10.000  -0.8902   0.04691   0.03914  -0.0411   0.9777   0.0751
  -9.750  -0.8632   0.04442   0.03635  -0.0428   0.9723   0.0764
  -9.500  -0.8378   0.04209   0.03368  -0.0437   0.9664   0.0772
  -9.250  -0.8060   0.03983   0.03112  -0.0453   0.9611   0.0779
  -9.000  -0.7633   0.03766   0.02866  -0.0484   0.9579   0.0794
  -8.750  -0.7330   0.03632   0.02705  -0.0493   0.9518   0.0816
  -8.500  -0.6815   0.03426   0.02505  -0.0533   0.9496   0.0857
  -8.250  -0.6267   0.03271   0.02354  -0.0578   0.9478   0.0906
  -8.000  -0.5684   0.03121   0.02213  -0.0624   0.9467   0.0981
  -7.750  -0.5252   0.03018   0.02114  -0.0654   0.9439   0.1084
  -7.500  -0.5076   0.02929   0.02045  -0.0646   0.9367   0.1184
  -7.250  -0.4896   0.02814   0.01945  -0.0644   0.9301   0.1381
  -7.000  -0.4999   0.02730   0.01883  -0.0597   0.9198   0.1588
  -6.750  -0.5171   0.02550   0.01768  -0.0547   0.9115   0.2317
  -6.500  -0.5476   0.02507   0.01756  -0.0459   0.8999   0.2778
  -6.250  -0.5537   0.02469   0.01865  -0.0396   0.8942   0.5405
  -6.000  -0.5679   0.02547   0.01942  -0.0319   0.8841   0.5680
  -5.750  -0.5376   0.02701   0.02079  -0.0308   0.8801   0.6079
  -5.500  -0.3211   0.03808   0.03166  -0.0447   0.8899   0.6485
  -5.250  -0.5049   0.02979   0.02341  -0.0242   0.8691   0.6434
  -5.000  -0.2220   0.04052   0.03376  -0.0483   0.8836   0.6786
  -4.750  -0.1269   0.04125   0.03425  -0.0569   0.8844   0.6868
  -4.500  -0.1015   0.04098   0.03387  -0.0571   0.8800   0.6985
  -4.250  -0.0590   0.04076   0.03352  -0.0596   0.8773   0.7078
  -4.000  -0.0681   0.04112   0.03388  -0.0544   0.8679   0.7163
  -3.750  -0.0354   0.04094   0.03360  -0.0557   0.8642   0.7244
  -3.500  -0.0133   0.04052   0.03310  -0.0556   0.8609   0.7331
  -3.250  -0.0088   0.04102   0.03359  -0.0524   0.8533   0.7394
  -3.000  -0.0372   0.04095   0.03350  -0.0447   0.8459   0.7487
  -2.750   0.0283   0.04055   0.03299  -0.0510   0.8447   0.7533
  -2.500  -0.0179   0.04149   0.03399  -0.0402   0.8355   0.7602
  -2.250  -0.0469   0.04141   0.03390  -0.0321   0.8289   0.7675
  -2.000   0.0178   0.04107   0.03346  -0.0387   0.8275   0.7714
  -1.750  -0.2009   0.04147   0.03409  -0.0004   0.8135   0.7841
  -1.500  -0.1499   0.04163   0.03416  -0.0046   0.8109   0.7870
  -1.250  -0.1000   0.04161   0.03406  -0.0088   0.8088   0.7906
  -1.000  -0.2154   0.04085   0.03336   0.0116   0.8025   0.8017
  -0.750  -0.2043   0.04099   0.03348   0.0136   0.7987   0.8056
  -0.500  -0.1937   0.04089   0.03334   0.0151   0.7956   0.8104
  -0.250  -0.1932   0.04032   0.03270   0.0174   0.7931   0.8177
   0.250  -0.1707   0.04067   0.03302   0.0207   0.7864   0.8253
   0.500  -0.1725   0.04059   0.03291   0.0235   0.7840   0.8317
   0.750  -0.1617   0.04053   0.03281   0.0246   0.7804   0.8363
   1.000  -0.1408   0.04081   0.03308   0.0248   0.7775   0.8400
   1.250  -0.1025   0.04114   0.03338   0.0226   0.7740   0.8441
   1.500  -0.1039   0.04121   0.03343   0.0251   0.7701   0.8505
   1.750  -0.0994   0.04145   0.03367   0.0272   0.7669   0.8549
   2.000  -0.0844   0.04176   0.03399   0.0280   0.7628   0.8598
   2.250  -0.0521   0.04205   0.03427   0.0265   0.7582   0.8649
   2.500  -0.0354   0.04238   0.03460   0.0269   0.7528   0.8701
   2.750  -0.0299   0.04273   0.03498   0.0289   0.7480   0.8753
   3.000  -0.0047   0.04307   0.03533   0.0283   0.7426   0.8810
   3.250   0.0223   0.04341   0.03567   0.0278   0.7355   0.8865
   3.500   0.0293   0.04381   0.03612   0.0296   0.7293   0.8929
   3.750   0.0730   0.04407   0.03640   0.0271   0.7228   0.8980
   4.000   0.0745   0.04451   0.03688   0.0293   0.7143   0.9049
   4.250   0.1066   0.04480   0.03722   0.0283   0.7074   0.9113
   4.500   0.1227   0.04521   0.03767   0.0289   0.6982   0.9190
   4.750   0.1551   0.04553   0.03806   0.0276   0.6907   0.9259
   5.000   0.1749   0.04598   0.03857   0.0276   0.6814   0.9339
   5.250   0.2130   0.04622   0.03889   0.0256   0.6735   0.9406
   5.500   0.2360   0.04685   0.03960   0.0247   0.6628   0.9490
   5.750   0.2875   0.04693   0.03979   0.0212   0.6557   0.9550
   6.000   0.3153   0.04772   0.04070   0.0190   0.6434   0.9626
   6.250   0.3809   0.04732   0.04044   0.0142   0.6379   0.9666
   6.500   0.4122   0.04799   0.04125   0.0115   0.6241   0.9736
   6.750   0.4562   0.04826   0.04167   0.0078   0.6119   0.9789
   7.000   0.5259   0.04687   0.04048   0.0034   0.6056   0.9826
   7.250   0.5715   0.04672   0.04051  -0.0003   0.5919   0.9880
   7.500   0.6401   0.04396   0.03798  -0.0035   0.5797   0.9925
   7.750   0.8451   0.02750   0.02182  -0.0096   0.5688   0.9785
   8.000   0.8863   0.02549   0.01998  -0.0106   0.5374   0.9863
   8.250   0.8984   0.02552   0.02013  -0.0101   0.4889   1.0000
   8.500   0.8558   0.02616   0.02075  -0.0010   0.4885   1.0000
   8.750   0.8263   0.02668   0.02122   0.0060   0.4706   1.0000
   9.000   0.8316   0.02584   0.01934   0.0106   0.3259   1.0000
   9.250   0.8065   0.02875   0.02145   0.0143   0.2331   1.0000
   9.500   0.7854   0.03208   0.02403   0.0172   0.1608   1.0000
   9.750   0.7805   0.03454   0.02602   0.0190   0.1277   1.0000
  10.000   0.7882   0.03617   0.02743   0.0202   0.1112   1.0000
  10.250   0.8014   0.03750   0.02856   0.0212   0.0997   1.0000
  10.500   0.8224   0.03844   0.02949   0.0218   0.0919   1.0000
  10.750   0.8532   0.03922   0.03006   0.0221   0.0856   1.0000
  11.000   0.8798   0.04019   0.03107   0.0222   0.0802   1.0000
  11.250   0.9316   0.04120   0.03184   0.0209   0.0752   1.0000
  11.500   0.9653   0.04263   0.03348   0.0205   0.0727   1.0000
  11.750   0.9995   0.04433   0.03535   0.0199   0.0705   1.0000
  12.000   1.0286   0.04613   0.03721   0.0193   0.0678   1.0000
  12.250   1.0784   0.04919   0.04025   0.0167   0.0654   1.0000
  12.500   1.0981   0.05221   0.04356   0.0168   0.0648   1.0000
  12.750   1.1087   0.05498   0.04662   0.0177   0.0647   1.0000
  13.000   1.1131   0.05797   0.04991   0.0190   0.0646   1.0000
  13.250   1.1173   0.06127   0.05347   0.0201   0.0647   1.0000
  13.500   1.1154   0.06469   0.05716   0.0215   0.0648   1.0000
  13.750   1.1146   0.06855   0.06125   0.0224   0.0650   1.0000
  14.000   1.1050   0.07223   0.06516   0.0237   0.0651   1.0000
  14.250   1.0865   0.07499   0.06821   0.0254   0.0654   1.0000
  14.500   1.0169   0.07959   0.07340   0.0274   0.0673   1.0000
  14.750   0.9601   0.08726   0.08151   0.0264   0.0691   1.0000
  15.000   0.9157   0.09541   0.08995   0.0237   0.0708   1.0000
  15.250   0.8759   0.10428   0.09900   0.0199   0.0724   1.0000
  15.500   0.8461   0.11321   0.10805   0.0156   0.0739   1.0000
  15.750   0.8449   0.11906   0.11392   0.0137   0.0751   1.0000
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