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BOEING-VERTOL VR-5 AIRFOIL (vr5-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: BOEING-VERTOL VR-5 AIRFOIL (vr5-il)
Reynolds number: 200,000
Max Cl/Cd: 77.99 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-vr5-il-200000-n5.txt
Download as CSV file: xf-vr5-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3237   0.09868   0.09537  -0.0181   0.8470   0.0269
  -9.750  -0.3270   0.09424   0.09090  -0.0193   0.8413   0.0264
  -9.250  -0.4498   0.09256   0.08917  -0.0164   0.8619   0.0195
  -9.000  -0.4472   0.08907   0.08566  -0.0177   0.8534   0.0192
  -8.750  -0.4460   0.08492   0.08150  -0.0201   0.8443   0.0190
  -8.500  -0.4460   0.08007   0.07664  -0.0241   0.8352   0.0187
  -8.000  -0.4486   0.06826   0.06468  -0.0367   0.8168   0.0182
  -7.750  -0.4460   0.06254   0.05879  -0.0409   0.8091   0.0180
  -7.500  -0.4399   0.05692   0.05297  -0.0442   0.8006   0.0179
  -7.250  -0.4307   0.05154   0.04731  -0.0463   0.7933   0.0179
  -7.000  -0.4183   0.04590   0.04131  -0.0479   0.7856   0.0186
  -6.750  -0.4058   0.03846   0.03324  -0.0487   0.7793   0.0194
  -6.500  -0.3894   0.03256   0.02669  -0.0488   0.7720   0.0196
  -6.250  -0.3693   0.02927   0.02294  -0.0486   0.7654   0.0200
  -6.000  -0.3456   0.02755   0.02099  -0.0486   0.7574   0.0205
  -5.750  -0.3215   0.02594   0.01908  -0.0484   0.7507   0.0211
  -5.500  -0.2961   0.02424   0.01706  -0.0483   0.7431   0.0223
  -5.250  -0.2703   0.02231   0.01462  -0.0478   0.7367   0.0242
  -5.000  -0.2441   0.02068   0.01268  -0.0476   0.7302   0.0253
  -4.750  -0.2176   0.01976   0.01162  -0.0476   0.7237   0.0264
  -4.500  -0.1908   0.01889   0.01057  -0.0474   0.7180   0.0279
  -4.250  -0.1633   0.01805   0.00954  -0.0473   0.7113   0.0300
  -4.000  -0.1366   0.01726   0.00860  -0.0471   0.7056   0.0324
  -3.750  -0.1094   0.01672   0.00803  -0.0471   0.6993   0.0348
  -3.500  -0.0819   0.01625   0.00747  -0.0471   0.6931   0.0377
  -3.000  -0.0278   0.01507   0.00615  -0.0470   0.6825   0.0424
  -2.750  -0.0005   0.01461   0.00565  -0.0469   0.6771   0.0444
  -2.250   0.0548   0.01392   0.00483  -0.0470   0.6666   0.0493
  -2.000   0.0825   0.01357   0.00443  -0.0471   0.6614   0.0523
  -1.750   0.1103   0.01331   0.00410  -0.0472   0.6573   0.0561
  -1.500   0.1388   0.01311   0.00386  -0.0474   0.6522   0.0614
  -1.250   0.1670   0.01287   0.00367  -0.0476   0.6472   0.0763
  -1.000   0.1945   0.01246   0.00349  -0.0478   0.6430   0.1523
  -0.750   0.2153   0.01078   0.00345  -0.0475   0.6388   0.6255
  -0.500   0.2406   0.01062   0.00352  -0.0467   0.6340   0.7058
  -0.250   0.2650   0.01053   0.00360  -0.0456   0.6296   0.7726
   0.000   0.2882   0.01050   0.00364  -0.0441   0.6259   0.8224
   0.250   0.3104   0.01047   0.00374  -0.0423   0.6209   0.8642
   0.500   0.3342   0.01048   0.00376  -0.0410   0.6164   0.8938
   0.750   0.3613   0.01051   0.00372  -0.0407   0.6125   0.9111
   1.000   0.3900   0.01054   0.00371  -0.0408   0.6085   0.9256
   1.250   0.4202   0.01057   0.00373  -0.0413   0.6041   0.9398
   1.500   0.4526   0.01060   0.00373  -0.0424   0.6003   0.9531
   1.750   0.4872   0.01065   0.00371  -0.0438   0.5964   0.9664
   2.000   0.5232   0.01069   0.00375  -0.0458   0.5905   0.9817
   2.250   0.5577   0.01074   0.00376  -0.0474   0.5845   1.0000
   2.500   0.5851   0.01084   0.00380  -0.0475   0.5795   1.0000
   2.750   0.6130   0.01095   0.00391  -0.0478   0.5737   1.0000
   3.000   0.6408   0.01106   0.00398  -0.0480   0.5686   1.0000
   3.250   0.6688   0.01119   0.00409  -0.0483   0.5640   1.0000
   3.500   0.6969   0.01132   0.00426  -0.0486   0.5586   1.0000
   3.750   0.7249   0.01145   0.00438  -0.0488   0.5535   1.0000
   4.000   0.7529   0.01160   0.00453  -0.0490   0.5483   1.0000
   4.250   0.7809   0.01174   0.00473  -0.0492   0.5424   1.0000
   4.500   0.8088   0.01190   0.00489  -0.0494   0.5372   1.0000
   4.750   0.8366   0.01206   0.00511  -0.0496   0.5314   1.0000
   5.000   0.8643   0.01221   0.00532  -0.0498   0.5240   1.0000
   5.250   0.8918   0.01236   0.00550  -0.0500   0.5161   1.0000
   5.500   0.9191   0.01250   0.00570  -0.0501   0.5062   1.0000
   5.750   0.9464   0.01264   0.00593  -0.0502   0.4947   1.0000
   6.000   0.9733   0.01279   0.00612  -0.0503   0.4806   1.0000
   6.250   0.9998   0.01295   0.00634  -0.0503   0.4633   1.0000
   6.500   1.0256   0.01315   0.00653  -0.0502   0.4378   1.0000
   6.750   1.0495   0.01351   0.00676  -0.0499   0.4008   1.0000
   7.000   1.0718   0.01408   0.00716  -0.0495   0.3610   1.0000
   7.250   1.0921   0.01487   0.00775  -0.0490   0.3138   1.0000
   7.750   1.1268   0.01696   0.00940  -0.0475   0.2296   1.0000
   8.000   1.1408   0.01825   0.01040  -0.0466   0.1696   1.0000
   8.250   1.1493   0.01994   0.01172  -0.0452   0.1186   1.0000
   8.500   1.1617   0.02119   0.01285  -0.0441   0.0905   1.0000
   8.750   1.1729   0.02242   0.01398  -0.0428   0.0733   1.0000
   9.000   1.1837   0.02359   0.01515  -0.0416   0.0632   1.0000
   9.250   1.1953   0.02478   0.01639  -0.0406   0.0554   1.0000
   9.500   1.2052   0.02614   0.01779  -0.0395   0.0489   1.0000
   9.750   1.2150   0.02755   0.01925  -0.0386   0.0432   1.0000
  10.000   1.2236   0.02909   0.02085  -0.0377   0.0390   1.0000
  10.250   1.2317   0.03072   0.02253  -0.0369   0.0352   1.0000
  10.500   1.2374   0.03262   0.02446  -0.0360   0.0324   1.0000
  10.750   1.2450   0.03438   0.02633  -0.0353   0.0300   1.0000
  11.000   1.2510   0.03632   0.02836  -0.0347   0.0280   1.0000
  11.250   1.2541   0.03858   0.03068  -0.0340   0.0265   1.0000
  11.500   1.2572   0.04087   0.03305  -0.0334   0.0255   1.0000
  11.750   1.2617   0.04305   0.03536  -0.0328   0.0246   1.0000
  12.000   1.2655   0.04531   0.03773  -0.0323   0.0237   1.0000
  12.250   1.2688   0.04764   0.04016  -0.0318   0.0230   1.0000
  12.500   1.2719   0.05002   0.04264  -0.0313   0.0223   1.0000
  12.750   1.2745   0.05247   0.04518  -0.0310   0.0217   1.0000
  13.000   1.2763   0.05503   0.04781  -0.0306   0.0211   1.0000
  13.250   1.2764   0.05781   0.05065  -0.0303   0.0205   1.0000
  13.500   1.2799   0.06029   0.05324  -0.0299   0.0200   1.0000
  13.750   1.2838   0.06277   0.05586  -0.0297   0.0195   1.0000
  14.000   1.2872   0.06536   0.05858  -0.0296   0.0189   1.0000
  14.250   1.2900   0.06803   0.06138  -0.0294   0.0185   1.0000
  14.500   1.2923   0.07079   0.06426  -0.0293   0.0181   1.0000
  14.750   1.2942   0.07367   0.06726  -0.0294   0.0178   1.0000
  15.000   1.2956   0.07667   0.07040  -0.0296   0.0174   1.0000
  15.250   1.2963   0.07982   0.07366  -0.0299   0.0171   1.0000
  15.500   1.2964   0.08308   0.07702  -0.0304   0.0167   1.0000
  15.750   1.2959   0.08645   0.08048  -0.0310   0.0164   1.0000
  16.000   1.2945   0.08997   0.08408  -0.0316   0.0161   1.0000
  16.250   1.2915   0.09389   0.08816  -0.0325   0.0158   1.0000
  16.500   1.2868   0.09825   0.09272  -0.0338   0.0155   1.0000
  16.750   1.2810   0.10287   0.09755  -0.0353   0.0153   1.0000
  17.000   1.2740   0.10783   0.10271  -0.0370   0.0151   1.0000
  17.250   1.2656   0.11316   0.10824  -0.0392   0.0149   1.0000
  17.500   1.2560   0.11890   0.11418  -0.0417   0.0148   1.0000
  17.750   1.2448   0.12512   0.12059  -0.0447   0.0146   1.0000
  18.000   1.2323   0.13185   0.12753  -0.0483   0.0145   1.0000
  18.250   1.2180   0.13927   0.13515  -0.0524   0.0145   1.0000
  18.500   1.2015   0.14760   0.14368  -0.0574   0.0144   1.0000
  18.750   1.1817   0.15727   0.15357  -0.0635   0.0144   1.0000
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