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RG 14 10% AIRFOIL (rg1410-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: RG 14 10% AIRFOIL (rg1410-il)
Reynolds number: 50,000
Max Cl/Cd: 32.17 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rg1410-il-50000.txt
Download as CSV file: xf-rg1410-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RG 14 10% AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4550   0.10359   0.09635  -0.0069   1.0000   0.3016
  -8.750  -0.4545   0.10059   0.09340  -0.0066   1.0000   0.3147
  -8.000  -0.4632   0.09276   0.08580  -0.0049   1.0000   0.3554
  -7.750  -0.4435   0.08830   0.08133  -0.0040   1.0000   0.3674
  -7.500  -0.4496   0.08597   0.07909  -0.0026   1.0000   0.3847
  -7.250  -0.4619   0.08401   0.07726  -0.0007   1.0000   0.4011
  -7.000  -0.5603   0.06316   0.05633  -0.0300   1.0000   0.1699
  -6.750  -0.5749   0.05563   0.04827  -0.0318   1.0000   0.1492
  -6.500  -0.5691   0.05122   0.04354  -0.0309   1.0000   0.1435
  -6.250  -0.5616   0.04695   0.03892  -0.0298   1.0000   0.1394
  -6.000  -0.5534   0.04263   0.03400  -0.0284   1.0000   0.1358
  -5.750  -0.5396   0.03945   0.03042  -0.0269   1.0000   0.1366
  -5.500  -0.5237   0.03690   0.02751  -0.0253   1.0000   0.1413
  -5.250  -0.5064   0.03425   0.02426  -0.0238   1.0000   0.1456
  -5.000  -0.4865   0.03171   0.02148  -0.0224   1.0000   0.1502
  -4.750  -0.4658   0.02984   0.01928  -0.0210   1.0000   0.1602
  -4.500  -0.4447   0.02804   0.01737  -0.0196   1.0000   0.1744
  -4.250  -0.4228   0.02630   0.01555  -0.0183   1.0000   0.1930
  -4.000  -0.4013   0.02480   0.01410  -0.0169   1.0000   0.2221
  -3.750  -0.3800   0.02337   0.01286  -0.0154   1.0000   0.2654
  -3.500  -0.3588   0.02185   0.01181  -0.0139   1.0000   0.3303
  -3.250  -0.3420   0.02015   0.01089  -0.0114   1.0000   0.4406
  -3.000  -0.3360   0.01847   0.01078  -0.0049   1.0000   0.6535
  -2.750  -0.0872   0.02000   0.01124  -0.0343   1.0000   1.0000
  -2.500  -0.0907   0.01955   0.01069  -0.0310   1.0000   1.0000
  -2.250  -0.0929   0.01926   0.01029  -0.0274   1.0000   1.0000
  -2.000  -0.0944   0.01907   0.00998  -0.0237   1.0000   1.0000
  -1.750  -0.0953   0.01895   0.00974  -0.0199   1.0000   1.0000
  -1.500  -0.0951   0.01889   0.00956  -0.0163   1.0000   1.0000
  -1.250  -0.0932   0.01888   0.00944  -0.0129   1.0000   1.0000
  -1.000  -0.0892   0.01894   0.00936  -0.0099   1.0000   1.0000
  -0.750  -0.0829   0.01906   0.00935  -0.0073   1.0000   1.0000
  -0.500  -0.0740   0.01924   0.00941  -0.0052   1.0000   1.0000
  -0.250  -0.0632   0.01950   0.00953  -0.0034   1.0000   1.0000
   0.000  -0.0509   0.01982   0.00974  -0.0020   1.0000   1.0000
   0.250  -0.0378   0.02020   0.01001  -0.0009   1.0000   1.0000
   0.500  -0.0240   0.02064   0.01037   0.0001   1.0000   1.0000
   0.750  -0.0099   0.02114   0.01079   0.0009   1.0000   1.0000
   1.000   0.0044   0.02171   0.01129   0.0015   1.0000   1.0000
   1.250   0.0195   0.02236   0.01188   0.0019   0.9997   1.0000
   1.500   0.0804   0.02379   0.01329  -0.0062   0.9796   1.0000
   1.750   0.1373   0.02497   0.01447  -0.0132   0.9592   1.0000
   2.000   0.1886   0.02591   0.01544  -0.0188   0.9381   1.0000
   2.250   0.2402   0.02672   0.01631  -0.0241   0.9169   1.0000
   2.500   0.2907   0.02738   0.01705  -0.0288   0.8955   1.0000
   2.750   0.3365   0.02789   0.01768  -0.0324   0.8732   1.0000
   3.000   0.3914   0.02819   0.01813  -0.0370   0.8520   1.0000
   3.250   0.4348   0.02843   0.01851  -0.0395   0.8287   1.0000
   3.500   0.4949   0.02812   0.01844  -0.0437   0.8061   1.0000
   3.750   0.5565   0.02708   0.01765  -0.0466   0.7795   1.0000
   4.000   0.6011   0.02622   0.01696  -0.0467   0.7505   1.0000
   4.250   0.6375   0.02568   0.01656  -0.0458   0.7219   1.0000
   4.500   0.6708   0.02527   0.01628  -0.0444   0.6926   1.0000
   4.750   0.7033   0.02479   0.01587  -0.0427   0.6607   1.0000
   5.000   0.7285   0.02464   0.01574  -0.0402   0.6247   1.0000
   5.250   0.7562   0.02432   0.01534  -0.0376   0.5846   1.0000
   5.500   0.7778   0.02438   0.01529  -0.0345   0.5393   1.0000
   5.750   0.7958   0.02474   0.01551  -0.0314   0.4901   1.0000
   6.000   0.8143   0.02532   0.01586  -0.0285   0.4408   1.0000
   6.250   0.8326   0.02615   0.01644  -0.0259   0.3951   1.0000
   6.500   0.8508   0.02720   0.01733  -0.0237   0.3546   1.0000
   6.750   0.8704   0.02841   0.01836  -0.0218   0.3198   1.0000
   7.000   0.8900   0.02974   0.01954  -0.0201   0.2891   1.0000
   7.250   0.9092   0.03136   0.02119  -0.0185   0.2635   1.0000
   7.500   0.9299   0.03300   0.02276  -0.0172   0.2410   1.0000
   7.750   0.9484   0.03497   0.02491  -0.0157   0.2226   1.0000
   8.000   0.9667   0.03691   0.02696  -0.0142   0.2057   1.0000
   8.250   0.9839   0.03930   0.02955  -0.0127   0.1925   1.0000
   8.500   0.9991   0.04174   0.03218  -0.0111   0.1801   1.0000
   8.750   1.0166   0.04444   0.03497  -0.0098   0.1698   1.0000
   9.000   1.0223   0.04757   0.03864  -0.0074   0.1622   1.0000
   9.250   1.0318   0.05073   0.04200  -0.0057   0.1544   1.0000
   9.500   1.0272   0.05475   0.04654  -0.0030   0.1509   1.0000
   9.750   1.0238   0.05874   0.05088  -0.0009   0.1476   1.0000
  10.000   1.0335   0.06230   0.05447   0.0003   0.1416   1.0000
  10.250   1.0137   0.06694   0.05949   0.0026   0.1411   1.0000
  10.500   0.9914   0.07177   0.06457   0.0044   0.1413   1.0000
  10.750   0.9690   0.07655   0.06948   0.0058   0.1420   1.0000
  11.000   0.9467   0.08191   0.07491   0.0059   0.1426   1.0000
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