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LISSAMAN 7769 AIRFOIL (l7769-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: LISSAMAN 7769 AIRFOIL (l7769-il)
Reynolds number: 500,000
Max Cl/Cd: 113.72 at α=9°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-l7769-il-500000.txt
Download as CSV file: xf-l7769-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: LISSAMAN 7769 AIRFOIL                           
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4241   0.08811   0.08430  -0.0011   0.5155   0.0381
  -8.000  -0.4306   0.08419   0.08040  -0.0040   0.5142   0.0381
  -7.750  -0.4268   0.08040   0.07659  -0.0039   0.5123   0.0386
  -7.500  -0.4169   0.07800   0.07416  -0.0047   0.5100   0.0389
  -7.250  -0.4061   0.07555   0.07172  -0.0057   0.5084   0.0393
  -7.000  -0.3955   0.07281   0.06899  -0.0075   0.5066   0.0398
  -6.750  -0.3846   0.06976   0.06592  -0.0099   0.5048   0.0405
  -6.500  -0.3730   0.06616   0.06228  -0.0131   0.5030   0.0418
  -6.250  -0.3676   0.05550   0.05140  -0.0238   0.5024   0.0452
  -6.000  -0.3497   0.05357   0.04942  -0.0241   0.5003   0.0456
  -5.750  -0.3600   0.02713   0.02145  -0.0325   0.5013   0.0377
  -5.500  -0.3391   0.02357   0.01739  -0.0324   0.4994   0.0376
  -5.250  -0.3155   0.02119   0.01461  -0.0321   0.4974   0.0375
  -5.000  -0.2900   0.01966   0.01276  -0.0318   0.4953   0.0376
  -4.750  -0.2636   0.01856   0.01141  -0.0314   0.4931   0.0377
  -4.500  -0.2365   0.01762   0.01030  -0.0311   0.4911   0.0379
  -4.250  -0.2090   0.01691   0.00943  -0.0308   0.4888   0.0381
  -4.000  -0.1824   0.01565   0.00802  -0.0305   0.4865   0.0386
  -3.750  -0.1552   0.01484   0.00715  -0.0302   0.4844   0.0394
  -3.500  -0.1276   0.01437   0.00664  -0.0299   0.4824   0.0403
  -3.250  -0.0999   0.01396   0.00615  -0.0296   0.4806   0.0410
  -3.000  -0.0722   0.01361   0.00574  -0.0293   0.4786   0.0417
  -2.750  -0.0443   0.01332   0.00539  -0.0291   0.4766   0.0426
  -2.500  -0.0163   0.01299   0.00504  -0.0288   0.4750   0.0434
  -2.250   0.0118   0.01272   0.00475  -0.0285   0.4731   0.0443
  -2.000   0.0396   0.01232   0.00436  -0.0283   0.4711   0.0458
  -1.750   0.0676   0.01208   0.00412  -0.0280   0.4690   0.0478
  -1.500   0.0958   0.01191   0.00393  -0.0278   0.4670   0.0506
  -1.250   0.1239   0.01170   0.00373  -0.0276   0.4653   0.0549
  -1.000   0.1520   0.01155   0.00360  -0.0273   0.4636   0.0634
  -0.750   0.1801   0.01148   0.00361  -0.0271   0.4618   0.0860
  -0.500   0.2085   0.01152   0.00370  -0.0270   0.4602   0.1012
  -0.250   0.2371   0.01152   0.00373  -0.0269   0.4586   0.1103
   0.000   0.2657   0.01155   0.00380  -0.0268   0.4569   0.1187
   0.250   0.2942   0.01154   0.00381  -0.0267   0.4552   0.1260
   0.500   0.3227   0.01155   0.00384  -0.0266   0.4534   0.1336
   0.750   0.3511   0.01152   0.00381  -0.0265   0.4515   0.1413
   1.000   0.3795   0.01151   0.00381  -0.0264   0.4498   0.1495
   1.250   0.4078   0.01148   0.00379  -0.0263   0.4483   0.1586
   1.500   0.4361   0.01153   0.00383  -0.0262   0.4468   0.1677
   1.750   0.4640   0.01161   0.00394  -0.0261   0.4450   0.1792
   2.000   0.4924   0.01155   0.00397  -0.0260   0.4438   0.1914
   2.250   0.5206   0.01149   0.00403  -0.0259   0.4423   0.2118
   2.500   0.5598   0.00952   0.00414  -0.0285   0.4403   1.0000
   2.750   0.5874   0.00962   0.00420  -0.0282   0.4385   1.0000
   3.000   0.6151   0.00972   0.00427  -0.0280   0.4368   1.0000
   3.250   0.6428   0.00980   0.00430  -0.0278   0.4349   1.0000
   3.500   0.6706   0.00984   0.00428  -0.0275   0.4326   1.0000
   3.750   0.6982   0.00998   0.00435  -0.0273   0.4301   1.0000
   4.000   0.7259   0.01007   0.00446  -0.0271   0.4278   1.0000
   4.250   0.7537   0.01011   0.00453  -0.0269   0.4251   1.0000
   4.500   0.7816   0.01016   0.00459  -0.0267   0.4225   1.0000
   4.750   0.8094   0.01023   0.00466  -0.0266   0.4203   1.0000
   5.000   0.8373   0.01031   0.00473  -0.0264   0.4183   1.0000
   5.250   0.8651   0.01039   0.00477  -0.0263   0.4160   1.0000
   5.500   0.8928   0.01049   0.00488  -0.0261   0.4127   1.0000
   5.750   0.9206   0.01046   0.00490  -0.0260   0.4088   1.0000
   6.000   0.9485   0.01048   0.00495  -0.0258   0.4055   1.0000
   6.250   0.9763   0.01052   0.00499  -0.0257   0.4027   1.0000
   6.500   1.0040   0.01061   0.00505  -0.0256   0.3996   1.0000
   6.750   1.0316   0.01071   0.00523  -0.0255   0.3966   1.0000
   7.000   1.0592   0.01077   0.00537  -0.0254   0.3931   1.0000
   7.250   1.0869   0.01082   0.00545  -0.0253   0.3895   1.0000
   7.500   1.1145   0.01086   0.00550  -0.0251   0.3857   1.0000
   7.750   1.1420   0.01094   0.00564  -0.0250   0.3812   1.0000
   8.000   1.1696   0.01095   0.00573  -0.0249   0.3751   1.0000
   8.250   1.1968   0.01098   0.00575  -0.0248   0.3682   1.0000
   8.500   1.2243   0.01101   0.00588  -0.0247   0.3593   1.0000
   8.750   1.2514   0.01110   0.00600  -0.0246   0.3490   1.0000
   9.000   1.2782   0.01124   0.00617  -0.0245   0.3359   1.0000
   9.250   1.3043   0.01148   0.00639  -0.0244   0.3163   1.0000
   9.500   1.3281   0.01205   0.00682  -0.0242   0.2835   1.0000
   9.750   1.3487   0.01308   0.00765  -0.0240   0.2450   1.0000
  10.000   1.3688   0.01415   0.00859  -0.0237   0.2169   1.0000
  10.250   1.3893   0.01511   0.00948  -0.0234   0.1971   1.0000
  10.500   1.4095   0.01605   0.01037  -0.0231   0.1803   1.0000
  10.750   1.4294   0.01696   0.01127  -0.0228   0.1641   1.0000
  11.000   1.4476   0.01802   0.01228  -0.0225   0.1478   1.0000
  11.250   1.4634   0.01925   0.01347  -0.0221   0.1322   1.0000
  11.500   1.4754   0.02078   0.01496  -0.0217   0.1167   1.0000
  11.750   1.4811   0.02290   0.01705  -0.0215   0.1014   1.0000
  12.000   1.4744   0.02708   0.02129  -0.0236   0.0893   1.0000
  12.250   1.4558   0.03120   0.02545  -0.0237   0.0818   1.0000
  12.500   1.4378   0.03529   0.02952  -0.0236   0.0723   1.0000
  12.750   1.4185   0.03955   0.03372  -0.0237   0.0606   1.0000
  13.000   1.4001   0.04378   0.03790  -0.0238   0.0499   1.0000
  13.250   1.3829   0.04802   0.04210  -0.0241   0.0407   1.0000
  13.500   1.3698   0.05195   0.04601  -0.0245   0.0348   1.0000
  13.750   1.3633   0.05544   0.04953  -0.0249   0.0317   1.0000
  14.000   1.3573   0.05902   0.05314  -0.0255   0.0293   1.0000
  14.250   1.3556   0.06222   0.05640  -0.0261   0.0277   1.0000
  14.500   1.3516   0.06578   0.06000  -0.0268   0.0263   1.0000
  14.750   1.3459   0.06965   0.06392  -0.0277   0.0252   1.0000
  15.000   1.3447   0.07301   0.06736  -0.0285   0.0241   1.0000
  15.250   1.3438   0.07640   0.07082  -0.0293   0.0235   1.0000
  15.500   1.3418   0.08000   0.07448  -0.0303   0.0226   1.0000
  15.750   1.3381   0.08390   0.07845  -0.0315   0.0220   1.0000
  16.000   1.3331   0.08807   0.08267  -0.0328   0.0215   1.0000
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