Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

BOEING-VERTOL VR-5 AIRFOIL (vr5-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: BOEING-VERTOL VR-5 AIRFOIL (vr5-il)
Reynolds number: 100,000
Max Cl/Cd: 55.41 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-vr5-il-100000-n5.txt
Download as CSV file: xf-vr5-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: BOEING-VERTOL VR-5 AIRFOIL                      
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.4190   0.11459   0.11009  -0.0157   1.0000   0.0489
 -10.000  -0.4198   0.11052   0.10607  -0.0214   1.0000   0.0498
  -9.750  -0.4182   0.10616   0.10177  -0.0265   1.0000   0.0500
  -9.500  -0.4158   0.10154   0.09720  -0.0319   1.0000   0.0502
  -9.250  -0.4131   0.09637   0.09205  -0.0390   0.9684   0.0503
  -9.000  -0.3929   0.09351   0.08919  -0.0314   0.9579   0.0527
  -8.750  -0.3844   0.09027   0.08593  -0.0328   0.9385   0.0547
  -8.500  -0.3820   0.08654   0.08219  -0.0352   0.9211   0.0559
  -8.250  -0.3823   0.08239   0.07803  -0.0385   0.9055   0.0564
  -8.000  -0.3848   0.07765   0.07326  -0.0435   0.8913   0.0561
  -7.750  -0.3899   0.06918   0.06457  -0.0513   0.8791   0.0423
  -7.500  -0.3857   0.06398   0.05918  -0.0535   0.8694   0.0357
  -7.000  -0.3739   0.05100   0.04523  -0.0585   0.8502   0.0311
  -6.750  -0.3612   0.04729   0.04121  -0.0585   0.8422   0.0310
  -6.250  -0.3286   0.04165   0.03511  -0.0586   0.8257   0.0328
  -6.000  -0.3084   0.03949   0.03273  -0.0588   0.8167   0.0343
  -5.750  -0.2884   0.03662   0.02944  -0.0584   0.8101   0.0350
  -5.500  -0.2657   0.03369   0.02607  -0.0582   0.8019   0.0354
  -5.250  -0.2432   0.03116   0.02306  -0.0575   0.7959   0.0361
  -5.000  -0.2179   0.02894   0.02037  -0.0572   0.7877   0.0376
  -4.750  -0.1925   0.02721   0.01808  -0.0564   0.7815   0.0401
  -4.500  -0.1672   0.02558   0.01633  -0.0564   0.7738   0.0421
  -4.250  -0.1416   0.02442   0.01498  -0.0560   0.7675   0.0447
  -4.000  -0.1147   0.02338   0.01368  -0.0557   0.7609   0.0482
  -3.750  -0.0877   0.02234   0.01239  -0.0552   0.7547   0.0506
  -3.500  -0.0625   0.02127   0.01133  -0.0548   0.7495   0.0543
  -3.250  -0.0358   0.02046   0.01046  -0.0545   0.7425   0.0569
  -3.000  -0.0100   0.01975   0.00964  -0.0539   0.7371   0.0600
  -2.750   0.0158   0.01912   0.00896  -0.0536   0.7311   0.0640
  -2.500   0.0415   0.01858   0.00841  -0.0532   0.7252   0.0677
  -2.250   0.0674   0.01814   0.00785  -0.0527   0.7207   0.0722
  -2.000   0.0941   0.01778   0.00745  -0.0527   0.7147   0.0798
  -1.750   0.1210   0.01745   0.00709  -0.0526   0.7091   0.0926
  -1.500   0.1473   0.01698   0.00668  -0.0523   0.7048   0.1269
  -1.250   0.1626   0.01496   0.00672  -0.0506   0.6994   0.6548
  -1.000   0.1821   0.01487   0.00690  -0.0479   0.6943   0.7662
  -0.750   0.2010   0.01485   0.00696  -0.0447   0.6901   0.8357
  -0.500   0.2206   0.01491   0.00710  -0.0413   0.6854   0.9070
  -0.250   0.2584   0.01495   0.00705  -0.0424   0.6801   0.9514
   0.000   0.2970   0.01495   0.00689  -0.0446   0.6757   0.9648
   0.250   0.3340   0.01496   0.00675  -0.0467   0.6716   0.9749
   0.500   0.3720   0.01506   0.00678  -0.0494   0.6657   0.9859
   0.750   0.4104   0.01511   0.00671  -0.0519   0.6610   0.9977
   1.000   0.4354   0.01517   0.00666  -0.0517   0.6572   1.0000
   1.250   0.4584   0.01539   0.00685  -0.0515   0.6514   1.0000
   1.500   0.4827   0.01556   0.00696  -0.0513   0.6466   1.0000
   1.750   0.5081   0.01569   0.00700  -0.0511   0.6428   1.0000
   2.000   0.5339   0.01593   0.00721  -0.0512   0.6380   1.0000
   2.250   0.5601   0.01618   0.00745  -0.0513   0.6329   1.0000
   2.500   0.5869   0.01635   0.00758  -0.0513   0.6288   1.0000
   2.750   0.6138   0.01653   0.00773  -0.0513   0.6247   1.0000
   3.000   0.6401   0.01682   0.00806  -0.0515   0.6182   1.0000
   3.250   0.6672   0.01689   0.00810  -0.0513   0.6126   1.0000
   3.500   0.6935   0.01709   0.00833  -0.0514   0.6050   1.0000
   3.750   0.7205   0.01717   0.00840  -0.0512   0.5983   1.0000
   4.000   0.7471   0.01736   0.00865  -0.0512   0.5912   1.0000
   4.250   0.7739   0.01751   0.00884  -0.0512   0.5845   1.0000
   4.500   0.8010   0.01767   0.00902  -0.0511   0.5792   1.0000
   4.750   0.8271   0.01798   0.00946  -0.0512   0.5723   1.0000
   5.000   0.8545   0.01813   0.00964  -0.0511   0.5672   1.0000
   5.250   0.8804   0.01845   0.01008  -0.0512   0.5601   1.0000
   5.500   0.9071   0.01863   0.01033  -0.0511   0.5535   1.0000
   5.750   0.9332   0.01888   0.01071  -0.0510   0.5460   1.0000
   6.000   0.9596   0.01902   0.01093  -0.0508   0.5374   1.0000
   6.250   0.9847   0.01924   0.01130  -0.0505   0.5265   1.0000
   6.500   1.0100   0.01934   0.01152  -0.0501   0.5139   1.0000
   6.750   1.0344   0.01943   0.01172  -0.0496   0.4976   1.0000
   7.000   1.0581   0.01951   0.01189  -0.0490   0.4773   1.0000
   7.250   1.0809   0.01969   0.01220  -0.0484   0.4543   1.0000
   7.500   1.1027   0.01991   0.01246  -0.0477   0.4252   1.0000
   7.750   1.1226   0.02026   0.01269  -0.0466   0.3875   1.0000
   8.000   1.1394   0.02096   0.01322  -0.0454   0.3445   1.0000
   8.250   1.1519   0.02203   0.01408  -0.0440   0.2972   1.0000
   8.500   1.1607   0.02343   0.01524  -0.0424   0.2562   1.0000
   8.750   1.1671   0.02499   0.01663  -0.0407   0.2135   1.0000
   9.000   1.1668   0.02689   0.01827  -0.0386   0.1606   1.0000
   9.250   1.1627   0.02927   0.02033  -0.0367   0.1282   1.0000
   9.500   1.1634   0.03144   0.02239  -0.0352   0.1054   1.0000
   9.750   1.1655   0.03358   0.02446  -0.0340   0.0881   1.0000
  10.000   1.1680   0.03574   0.02658  -0.0330   0.0762   1.0000
  10.250   1.1712   0.03791   0.02877  -0.0320   0.0675   1.0000
  10.500   1.1714   0.04040   0.03122  -0.0312   0.0615   1.0000
  10.750   1.1762   0.04251   0.03348  -0.0305   0.0558   1.0000
  11.000   1.1772   0.04502   0.03603  -0.0298   0.0516   1.0000
  11.250   1.1799   0.04739   0.03850  -0.0291   0.0482   1.0000
  11.500   1.1831   0.04973   0.04095  -0.0284   0.0452   1.0000
  11.750   1.1854   0.05219   0.04349  -0.0279   0.0428   1.0000
  12.000   1.1863   0.05476   0.04607  -0.0271   0.0410   1.0000
  12.250   1.1925   0.05685   0.04832  -0.0263   0.0391   1.0000
  12.500   1.1984   0.05899   0.05059  -0.0256   0.0372   1.0000
  12.750   1.2035   0.06125   0.05293  -0.0250   0.0355   1.0000
  13.000   1.2077   0.06361   0.05533  -0.0246   0.0341   1.0000
  13.250   1.2135   0.06584   0.05757  -0.0238   0.0327   1.0000
  13.500   1.2211   0.06805   0.06001  -0.0231   0.0317   1.0000
  13.750   1.2282   0.07038   0.06254  -0.0224   0.0308   1.0000
  14.000   1.2338   0.07297   0.06531  -0.0218   0.0299   1.0000
  14.250   1.2377   0.07581   0.06835  -0.0215   0.0292   1.0000
  14.500   1.2392   0.07897   0.07169  -0.0214   0.0286   1.0000
  14.750   1.2386   0.08238   0.07527  -0.0217   0.0280   1.0000
  15.000   1.2370   0.08593   0.07897  -0.0223   0.0273   1.0000
  15.250   1.2349   0.08960   0.08275  -0.0230   0.0268   1.0000
  15.500   1.2332   0.09328   0.08653  -0.0236   0.0262   1.0000
  15.750   1.2239   0.09830   0.09177  -0.0251   0.0258   1.0000
  16.000   1.2108   0.10414   0.09789  -0.0274   0.0256   1.0000
  16.250   1.1962   0.11051   0.10453  -0.0303   0.0254   1.0000
  16.500   1.1798   0.11750   0.11177  -0.0338   0.0253   1.0000
  16.750   1.1619   0.12519   0.11971  -0.0380   0.0253   1.0000
  17.000   1.1424   0.13379   0.12852  -0.0432   0.0254   1.0000
  17.250   1.1207   0.14353   0.13846  -0.0493   0.0255   1.0000
  17.500   1.0967   0.15475   0.14986  -0.0567   0.0256   1.0000
  17.750   1.0701   0.16796   0.16319  -0.0653   0.0259   1.0000
<< Back to BOEING-VERTOL VR-5 AIRFOIL (vr5-il)

Polar data table (+)

Polar graphs


<< Back to BOEING-VERTOL VR-5 AIRFOIL (vr5-il)