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NACA 65(2)-215 (naca652215-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NACA 65(2)-215 (naca652215-il)
Reynolds number: 100,000
Max Cl/Cd: 46.14 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca652215-il-100000.txt
Download as CSV file: xf-naca652215-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 65(2)-215                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.4886   0.11043   0.10534  -0.0389   1.0000   0.1661
 -11.250  -0.4647   0.10796   0.10283  -0.0370   1.0000   0.1706
 -11.000  -0.5009   0.10241   0.09744  -0.0423   1.0000   0.1808
 -10.750  -0.4678   0.10032   0.09527  -0.0392   1.0000   0.1853
 -10.500  -0.4992   0.09500   0.09011  -0.0434   1.0000   0.1965
 -10.250  -0.4676   0.09343   0.08847  -0.0403   1.0000   0.2034
  -8.500  -0.8439   0.05407   0.04773  -0.0237   1.0000   0.0895
  -8.250  -0.8338   0.04928   0.04275  -0.0230   0.9981   0.0840
  -8.000  -0.8136   0.04464   0.03710  -0.0232   0.9917   0.0761
  -7.750  -0.7865   0.04113   0.03321  -0.0245   0.9862   0.0751
  -7.500  -0.7580   0.03871   0.03032  -0.0257   0.9808   0.0761
  -7.250  -0.7292   0.03646   0.02766  -0.0266   0.9752   0.0765
  -7.000  -0.6930   0.03427   0.02511  -0.0285   0.9712   0.0769
  -6.750  -0.6646   0.03277   0.02331  -0.0289   0.9653   0.0776
  -6.500  -0.6284   0.03040   0.02104  -0.0308   0.9613   0.0812
  -6.250  -0.5887   0.02914   0.01974  -0.0334   0.9577   0.0859
  -6.000  -0.5615   0.02820   0.01870  -0.0333   0.9519   0.0892
  -5.750  -0.5308   0.02696   0.01757  -0.0341   0.9472   0.0944
  -5.500  -0.4954   0.02608   0.01671  -0.0360   0.9431   0.1044
  -5.250  -0.4820   0.02524   0.01602  -0.0341   0.9356   0.1128
  -5.000  -0.4577   0.02426   0.01513  -0.0342   0.9300   0.1325
  -4.750  -0.4524   0.02237   0.01407  -0.0318   0.9236   0.2252
  -4.500  -0.4601   0.02126   0.01495  -0.0250   0.9162   0.6068
  -4.250  -0.4276   0.02289   0.01654  -0.0233   0.9122   0.6685
  -4.000  -0.4189   0.02374   0.01731  -0.0189   0.9046   0.6922
  -3.750  -0.3920   0.02506   0.01858  -0.0166   0.9000   0.7142
  -3.500  -0.3561   0.02799   0.02153  -0.0122   0.8973   0.7484
  -3.000  -0.3085   0.03096   0.02437  -0.0049   0.8872   0.7923
  -2.750  -0.2582   0.03145   0.02468  -0.0081   0.8844   0.7996
  -2.500  -0.2282   0.03123   0.02432  -0.0094   0.8810   0.8089
  -2.250  -0.2275   0.03138   0.02442  -0.0050   0.8738   0.8162
  -2.000  -0.2154   0.03107   0.02402  -0.0034   0.8682   0.8250
  -1.750  -0.1658   0.03117   0.02400  -0.0075   0.8658   0.8294
  -1.500  -0.1970   0.03087   0.02369   0.0012   0.8577   0.8400
  -1.250  -0.1660   0.03094   0.02368   0.0002   0.8534   0.8444
  -1.000  -0.1322   0.03087   0.02352  -0.0017   0.8500   0.8498
  -0.750  -0.1402   0.03077   0.02339   0.0032   0.8440   0.8576
  -0.500  -0.1263   0.03081   0.02340   0.0047   0.8387   0.8636
  -0.250  -0.1070   0.03063   0.02314   0.0050   0.8346   0.8708
   0.000  -0.0613   0.03081   0.02327   0.0014   0.8323   0.8738
   0.250  -0.0832   0.03086   0.02333   0.0084   0.8247   0.8835
   0.500  -0.0600   0.03093   0.02337   0.0083   0.8204   0.8890
   0.750  -0.0224   0.03115   0.02355   0.0059   0.8175   0.8936
   1.000  -0.0250   0.03125   0.02365   0.0097   0.8117   0.9028
   1.250  -0.0040   0.03151   0.02391   0.0097   0.8066   0.9089
   1.500   0.0215   0.03163   0.02401   0.0093   0.8026   0.9164
   1.750   0.0629   0.03199   0.02438   0.0062   0.7989   0.9206
   2.000   0.0595   0.03225   0.02466   0.0097   0.7918   0.9315
   2.250   0.1036   0.03261   0.02505   0.0060   0.7873   0.9355
   2.500   0.1579   0.03292   0.02540   0.0011   0.7841   0.9393
   2.750   0.1636   0.03349   0.02602   0.0024   0.7754   0.9494
   3.000   0.2128   0.03379   0.02638  -0.0019   0.7705   0.9537
   3.250   0.2441   0.03432   0.02697  -0.0041   0.7638   0.9607
   3.500   0.2901   0.03478   0.02753  -0.0086   0.7568   0.9650
   3.750   0.3532   0.03486   0.02772  -0.0147   0.7529   0.9674
   4.000   0.3787   0.03563   0.02859  -0.0168   0.7423   0.9752
   4.250   0.4430   0.03541   0.02854  -0.0227   0.7376   0.9771
   4.500   0.4728   0.03599   0.02925  -0.0249   0.7262   0.9850
   4.750   0.5484   0.03500   0.02847  -0.0313   0.7215   0.9852
   5.000   0.5922   0.03482   0.02848  -0.0346   0.7087   0.9910
   5.250   0.7339   0.02560   0.01946  -0.0399   0.6867   0.9791
   5.500   0.7883   0.02248   0.01644  -0.0407   0.6607   0.9830
   5.750   0.8356   0.02042   0.01451  -0.0420   0.6294   0.9879
   6.000   0.8698   0.01885   0.01300  -0.0416   0.5631   0.9959
   6.250   0.8574   0.01916   0.01216  -0.0340   0.3544   1.0000
   6.500   0.8274   0.02026   0.01268  -0.0252   0.2728   1.0000
   6.750   0.7971   0.02088   0.01302  -0.0163   0.2311   1.0000
   7.000   0.7664   0.02114   0.01313  -0.0073   0.2107   1.0000
   7.250   0.7438   0.02272   0.01413  -0.0009   0.1554   1.0000
   7.500   0.7399   0.02449   0.01550   0.0024   0.1244   1.0000
   7.750   0.7461   0.02600   0.01681   0.0045   0.1086   1.0000
   8.000   0.7595   0.02727   0.01798   0.0059   0.0974   1.0000
   8.250   0.7799   0.02848   0.01914   0.0067   0.0891   1.0000
   8.500   0.8168   0.03011   0.02050   0.0058   0.0823   1.0000
   8.750   0.8493   0.03136   0.02189   0.0053   0.0774   1.0000
   9.000   0.8877   0.03302   0.02351   0.0037   0.0725   1.0000
   9.250   0.9498   0.03658   0.02711  -0.0014   0.0695   1.0000
   9.500   0.9773   0.03873   0.02956  -0.0014   0.0685   1.0000
   9.750   0.9984   0.04090   0.03207  -0.0008   0.0671   1.0000
  10.000   1.0156   0.04320   0.03468   0.0002   0.0657   1.0000
  10.250   1.0311   0.04604   0.03788   0.0014   0.0655   1.0000
  10.500   1.0423   0.04925   0.04146   0.0029   0.0660   1.0000
  10.750   1.0489   0.05273   0.04528   0.0047   0.0669   1.0000
  11.000   1.0536   0.05649   0.04933   0.0064   0.0680   1.0000
  11.250   1.0621   0.06139   0.05442   0.0071   0.0694   1.0000
  11.500   1.0550   0.06343   0.05684   0.0106   0.0716   1.0000
  11.750   0.9971   0.06713   0.06116   0.0172   0.0756   1.0000
  12.000   0.9719   0.07178   0.06606   0.0190   0.0782   1.0000
  12.250   0.9612   0.07680   0.07122   0.0194   0.0805   1.0000
  12.500   0.8988   0.08364   0.07850   0.0191   0.0869   1.0000
  12.750   0.8429   0.09254   0.08758   0.0152   0.0892   1.0000
  13.000   0.7417   0.09077   0.08610   0.0191   0.0802   1.0000
  13.250   0.6241   0.11520   0.11077   0.0039   0.0978   1.0000
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