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)-418 (naca643418-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 64(3)-418 (naca643418-il)
Reynolds number: 100,000
Max Cl/Cd: 42.68 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca643418-il-100000-n5.txt
Download as CSV file: xf-naca643418-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64(3)-418                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.750  -0.6934   0.07714   0.07070  -0.0771   1.0000   0.0420
 -14.500  -0.7092   0.07239   0.06582  -0.0793   1.0000   0.0423
 -14.250  -0.7265   0.06772   0.06097  -0.0812   1.0000   0.0425
 -14.000  -0.7385   0.06390   0.05702  -0.0823   1.0000   0.0428
 -13.750  -0.7486   0.06048   0.05344  -0.0830   1.0000   0.0431
 -13.500  -0.7564   0.05742   0.05023  -0.0833   1.0000   0.0436
 -13.250  -0.7631   0.05459   0.04725  -0.0832   1.0000   0.0440
 -13.000  -0.7685   0.05197   0.04448  -0.0828   1.0000   0.0445
 -12.750  -0.7724   0.04956   0.04189  -0.0820   1.0000   0.0450
 -12.500  -0.7747   0.04740   0.03957  -0.0808   1.0000   0.0455
 -12.250  -0.7762   0.04547   0.03748  -0.0793   1.0000   0.0461
 -12.000  -0.7790   0.04379   0.03564  -0.0772   1.0000   0.0467
 -11.750  -0.7858   0.04251   0.03420  -0.0742   1.0000   0.0473
 -11.500  -0.7793   0.04132   0.03301  -0.0727   0.9965   0.0481
 -11.250  -0.7516   0.03978   0.03145  -0.0748   0.9854   0.0496
 -11.000  -0.7230   0.03820   0.02975  -0.0770   0.9762   0.0512
 -10.750  -0.6910   0.03659   0.02792  -0.0792   0.9690   0.0531
 -10.500  -0.6591   0.03518   0.02639  -0.0808   0.9608   0.0548
 -10.250  -0.6279   0.03397   0.02522  -0.0828   0.9526   0.0569
 -10.000  -0.5975   0.03280   0.02396  -0.0846   0.9437   0.0597
  -9.750  -0.5678   0.03174   0.02279  -0.0858   0.9344   0.0624
  -9.500  -0.5396   0.03065   0.02173  -0.0872   0.9255   0.0651
  -9.250  -0.5165   0.02974   0.02076  -0.0875   0.9140   0.0684
  -9.000  -0.4940   0.02879   0.01976  -0.0878   0.9040   0.0722
  -8.750  -0.4768   0.02792   0.01887  -0.0874   0.8924   0.0761
  -8.500  -0.4609   0.02716   0.01803  -0.0864   0.8810   0.0807
  -8.250  -0.4484   0.02623   0.01710  -0.0852   0.8710   0.0859
  -8.000  -0.4393   0.02557   0.01639  -0.0832   0.8591   0.0920
  -7.750  -0.4306   0.02478   0.01560  -0.0813   0.8494   0.0990
  -7.500  -0.4199   0.02403   0.01487  -0.0796   0.8393   0.1088
  -7.250  -0.4080   0.02326   0.01411  -0.0781   0.8309   0.1227
  -7.000  -0.3969   0.02248   0.01341  -0.0764   0.8216   0.1423
  -6.750  -0.3846   0.02157   0.01261  -0.0749   0.8145   0.1733
  -6.500  -0.3756   0.02062   0.01191  -0.0732   0.8051   0.2187
  -6.250  -0.3653   0.01944   0.01113  -0.0716   0.7982   0.2970
  -6.000  -0.3519   0.01894   0.01126  -0.0696   0.7903   0.3962
  -5.750  -0.3293   0.01894   0.01130  -0.0687   0.7833   0.4568
  -5.500  -0.3036   0.01898   0.01122  -0.0682   0.7781   0.4893
  -5.250  -0.2802   0.01917   0.01136  -0.0673   0.7704   0.5117
  -5.000  -0.2545   0.01935   0.01143  -0.0667   0.7644   0.5302
  -4.750  -0.2271   0.01954   0.01150  -0.0662   0.7598   0.5461
  -4.500  -0.2031   0.01980   0.01170  -0.0653   0.7525   0.5608
  -4.250  -0.1774   0.02005   0.01186  -0.0646   0.7465   0.5762
  -4.000  -0.1499   0.02041   0.01215  -0.0637   0.7419   0.5896
  -3.750  -0.1252   0.02070   0.01242  -0.0627   0.7353   0.5985
  -3.500  -0.0992   0.02071   0.01234  -0.0624   0.7295   0.6052
  -3.250  -0.0719   0.02044   0.01188  -0.0628   0.7250   0.6120
  -3.000  -0.0452   0.02046   0.01185  -0.0624   0.7202   0.6153
  -2.750  -0.0199   0.02047   0.01181  -0.0621   0.7143   0.6193
  -2.500   0.0072   0.02035   0.01159  -0.0622   0.7096   0.6242
  -2.250   0.0359   0.02010   0.01117  -0.0629   0.7057   0.6302
  -2.000   0.0610   0.02017   0.01123  -0.0624   0.7002   0.6332
  -1.750   0.0868   0.02018   0.01121  -0.0622   0.6948   0.6367
  -1.500   0.1145   0.02010   0.01106  -0.0623   0.6905   0.6409
  -1.250   0.1438   0.01995   0.01079  -0.0629   0.6871   0.6457
  -1.000   0.1692   0.01995   0.01076  -0.0630   0.6819   0.6497
  -0.750   0.1947   0.02002   0.01084  -0.0627   0.6773   0.6526
  -0.500   0.2218   0.02004   0.01083  -0.0627   0.6734   0.6563
  -0.250   0.2506   0.02000   0.01073  -0.0631   0.6703   0.6605
   0.000   0.2782   0.02001   0.01069  -0.0635   0.6665   0.6651
   0.250   0.3029   0.02011   0.01082  -0.0634   0.6615   0.6690
   0.500   0.3289   0.02019   0.01092  -0.0632   0.6573   0.6722
   0.750   0.3567   0.02023   0.01094  -0.0633   0.6540   0.6762
   1.000   0.3861   0.02024   0.01091  -0.0637   0.6514   0.6812
   1.250   0.4110   0.02043   0.01113  -0.0638   0.6472   0.6868
   1.500   0.4342   0.02067   0.01146  -0.0633   0.6430   0.6903
   1.750   0.4599   0.02082   0.01165  -0.0631   0.6394   0.6945
   2.000   0.4879   0.02089   0.01173  -0.0633   0.6363   0.6995
   2.500   0.5402   0.02125   0.01216  -0.0633   0.6297   0.7093
   2.750   0.5617   0.02159   0.01262  -0.0626   0.6253   0.7143
   3.000   0.5875   0.02179   0.01286  -0.0626   0.6216   0.7205
   3.250   0.6154   0.02190   0.01301  -0.0628   0.6185   0.7263
   3.500   0.6437   0.02196   0.01312  -0.0628   0.6160   0.7315
   3.750   0.6624   0.02242   0.01371  -0.0618   0.6107   0.7380
   4.000   0.6844   0.02277   0.01415  -0.0613   0.6060   0.7445
   4.250   0.7090   0.02295   0.01443  -0.0608   0.6024   0.7499
   4.500   0.7381   0.02302   0.01455  -0.0610   0.5995   0.7566
   4.750   0.7637   0.02326   0.01487  -0.0609   0.5960   0.7636
   5.000   0.7756   0.02392   0.01573  -0.0589   0.5898   0.7704
   5.250   0.8004   0.02417   0.01606  -0.0586   0.5856   0.7788
   5.500   0.8287   0.02415   0.01613  -0.0585   0.5822   0.7855
   5.750   0.8508   0.02441   0.01651  -0.0577   0.5773   0.7938
   6.000   0.8651   0.02483   0.01708  -0.0558   0.5696   0.8019
   6.250   0.8990   0.02434   0.01664  -0.0561   0.5641   0.8099
   6.500   0.9107   0.02474   0.01720  -0.0538   0.5551   0.8193
   6.750   0.9406   0.02425   0.01677  -0.0534   0.5473   0.8284
   7.000   0.9522   0.02446   0.01712  -0.0509   0.5370   0.8387
   7.250   0.9858   0.02375   0.01643  -0.0509   0.5277   0.8489
   7.500   0.9873   0.02422   0.01710  -0.0469   0.5164   0.8615
   7.750   1.0024   0.02418   0.01716  -0.0447   0.5058   0.8747
   8.000   1.0208   0.02392   0.01697  -0.0427   0.4942   0.8891
   8.250   1.0147   0.02445   0.01769  -0.0378   0.4817   0.9102
   8.500   1.0197   0.02481   0.01819  -0.0347   0.4668   0.9386
   8.750   1.0306   0.02530   0.01878  -0.0335   0.4472   1.0000
   9.000   1.0350   0.02643   0.01994  -0.0320   0.4242   1.0000
   9.250   1.0401   0.02759   0.02105  -0.0305   0.3923   1.0000
   9.500   1.0524   0.02815   0.02129  -0.0291   0.3481   1.0000
   9.750   1.0528   0.02979   0.02263  -0.0273   0.3062   1.0000
  10.000   1.0481   0.03201   0.02459  -0.0255   0.2687   1.0000
  10.250   1.0428   0.03447   0.02683  -0.0240   0.2369   1.0000
  10.500   1.0382   0.03703   0.02921  -0.0228   0.2089   1.0000
  10.750   1.0348   0.03961   0.03165  -0.0218   0.1848   1.0000
  11.000   1.0343   0.04205   0.03398  -0.0210   0.1628   1.0000
  11.250   1.0344   0.04450   0.03633  -0.0204   0.1438   1.0000
  11.500   1.0356   0.04693   0.03866  -0.0199   0.1276   1.0000
  11.750   1.0384   0.04929   0.04095  -0.0195   0.1140   1.0000
  12.000   1.0421   0.05162   0.04323  -0.0192   0.1024   1.0000
  12.250   1.0468   0.05390   0.04551  -0.0190   0.0927   1.0000
  12.500   1.0513   0.05625   0.04783  -0.0188   0.0849   1.0000
  12.750   1.0557   0.05865   0.05021  -0.0187   0.0786   1.0000
  13.000   1.0620   0.06091   0.05250  -0.0187   0.0726   1.0000
  13.250   1.0658   0.06346   0.05499  -0.0187   0.0683   1.0000
  13.500   1.0736   0.06562   0.05725  -0.0187   0.0637   1.0000
  13.750   1.0786   0.06811   0.05975  -0.0189   0.0604   1.0000
  14.000   1.0862   0.07034   0.06204  -0.0190   0.0570   1.0000
  14.250   1.0928   0.07273   0.06448  -0.0192   0.0542   1.0000
  14.500   1.0989   0.07517   0.06692  -0.0194   0.0519   1.0000
  14.750   1.1075   0.07738   0.06924  -0.0196   0.0495   1.0000
  15.000   1.1143   0.07983   0.07175  -0.0199   0.0474   1.0000
  15.250   1.1208   0.08228   0.07416  -0.0203   0.0458   1.0000
  15.500   1.1291   0.08464   0.07670  -0.0205   0.0439   1.0000
  15.750   1.1362   0.08714   0.07930  -0.0210   0.0423   1.0000
  16.000   1.1422   0.08979   0.08199  -0.0216   0.0409   1.0000
  16.250   1.1496   0.09219   0.08439  -0.0221   0.0397   1.0000
  16.500   1.1555   0.09503   0.08743  -0.0226   0.0386   1.0000
  16.750   1.1608   0.09795   0.09052  -0.0233   0.0376   1.0000
  17.000   1.1653   0.10098   0.09368  -0.0242   0.0367   1.0000
  17.250   1.1688   0.10414   0.09694  -0.0252   0.0358   1.0000
  17.500   1.1739   0.10702   0.09987  -0.0262   0.0351   1.0000
  17.750   1.1782   0.11008   0.10300  -0.0273   0.0344   1.0000
  18.000   1.1724   0.11500   0.10820  -0.0295   0.0338   1.0000
  18.250   1.1662   0.12008   0.11352  -0.0318   0.0332   1.0000
  18.500   1.1582   0.12557   0.11924  -0.0347   0.0327   1.0000
  18.750   1.1490   0.13142   0.12530  -0.0379   0.0322   1.0000
<< Back to NACA 64(3)-418 (naca643418-il)

Polar data table (+)

Polar graphs


<< Back to NACA 64(3)-418 (naca643418-il)