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BOEING-VERTOL VR-5 AIRFOIL (vr5-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: BOEING-VERTOL VR-5 AIRFOIL (vr5-il)
Reynolds number: 200,000
Max Cl/Cd: 79.93 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-vr5-il-200000.txt
Download as CSV file: xf-vr5-il-200000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4219   0.10501   0.10196  -0.0189   1.0000   0.0410
  -9.500  -0.4200   0.10011   0.09710  -0.0273   1.0000   0.0415
  -9.250  -0.4171   0.09441   0.09145  -0.0365   1.0000   0.0417
  -9.000  -0.4130   0.08828   0.08525  -0.0470   0.9643   0.0418
  -8.750  -0.4085   0.08298   0.08002  -0.0442   0.9508   0.0426
  -8.500  -0.4022   0.08123   0.07825  -0.0399   0.9356   0.0434
  -8.250  -0.4031   0.07811   0.07511  -0.0405   0.9194   0.0440
  -8.000  -0.4040   0.07449   0.07142  -0.0429   0.9054   0.0446
  -7.750  -0.4013   0.07081   0.06766  -0.0450   0.8934   0.0456
  -7.500  -0.3974   0.06696   0.06370  -0.0473   0.8828   0.0469
  -7.250  -0.3917   0.06298   0.05956  -0.0496   0.8729   0.0486
  -7.000  -0.3802   0.06010   0.05600  -0.0541   0.8618   0.0525
  -6.750  -0.3742   0.05363   0.04939  -0.0550   0.8543   0.0536
  -6.500  -0.3596   0.05026   0.04606  -0.0549   0.8458   0.0549
  -6.250  -0.3432   0.04787   0.04362  -0.0548   0.8380   0.0573
  -6.000  -0.3187   0.04880   0.04373  -0.0546   0.8296   0.0652
  -5.750  -0.3064   0.04177   0.03687  -0.0557   0.8227   0.0678
  -5.500  -0.2863   0.03946   0.03449  -0.0556   0.8151   0.0709
  -5.250  -0.2636   0.03737   0.03182  -0.0556   0.8079   0.0806
  -5.000  -0.2423   0.03463   0.02913  -0.0556   0.8004   0.0838
  -4.750  -0.2187   0.03296   0.02703  -0.0554   0.7937   0.0957
  -4.500  -0.1950   0.03072   0.02479  -0.0555   0.7862   0.1013
  -4.250  -0.1591   0.02399   0.01650  -0.0525   0.7820   0.0535
  -4.000  -0.1307   0.02248   0.01472  -0.0523   0.7745   0.0530
  -3.750  -0.1051   0.02017   0.01226  -0.0520   0.7687   0.0557
  -3.500  -0.0777   0.01914   0.01113  -0.0518   0.7622   0.0585
  -3.250  -0.0502   0.01815   0.00998  -0.0514   0.7556   0.0609
  -3.000  -0.0229   0.01756   0.00920  -0.0509   0.7505   0.0643
  -2.750   0.0047   0.01654   0.00815  -0.0508   0.7437   0.0664
  -2.500   0.0309   0.01578   0.00740  -0.0505   0.7386   0.0711
  -2.250   0.0581   0.01528   0.00687  -0.0504   0.7330   0.0749
  -2.000   0.0857   0.01488   0.00641  -0.0503   0.7269   0.0786
  -1.750   0.1122   0.01433   0.00588  -0.0501   0.7224   0.0867
  -1.500   0.1402   0.01399   0.00554  -0.0503   0.7169   0.0983
  -1.250   0.1649   0.01253   0.00506  -0.0506   0.7115   0.3640
  -1.000   0.1773   0.01140   0.00539  -0.0466   0.7074   0.7809
  -0.750   0.1987   0.01146   0.00553  -0.0445   0.7026   0.8352
  -0.500   0.2203   0.01153   0.00564  -0.0425   0.6971   0.8687
  -0.250   0.2393   0.01160   0.00568  -0.0396   0.6929   0.9051
   0.000   0.2605   0.01165   0.00569  -0.0373   0.6889   0.9418
   0.250   0.3057   0.01172   0.00573  -0.0400   0.6834   0.9727
   0.500   0.3559   0.01176   0.00566  -0.0446   0.6789   0.9853
   0.750   0.3997   0.01180   0.00557  -0.0481   0.6754   0.9935
   1.000   0.4400   0.01189   0.00564  -0.0513   0.6703   1.0000
   1.250   0.4624   0.01198   0.00569  -0.0511   0.6655   1.0000
   1.500   0.4846   0.01207   0.00572  -0.0505   0.6617   1.0000
   1.750   0.5077   0.01221   0.00581  -0.0501   0.6574   1.0000
   2.000   0.5323   0.01234   0.00593  -0.0499   0.6511   1.0000
   2.250   0.5583   0.01239   0.00589  -0.0497   0.6460   1.0000
   2.500   0.5853   0.01255   0.00603  -0.0499   0.6403   1.0000
   2.750   0.6128   0.01268   0.00616  -0.0501   0.6347   1.0000
   3.000   0.6405   0.01277   0.00619  -0.0501   0.6303   1.0000
   3.250   0.6682   0.01294   0.00639  -0.0504   0.6242   1.0000
   3.500   0.6960   0.01304   0.00649  -0.0505   0.6183   1.0000
   3.750   0.7241   0.01313   0.00652  -0.0505   0.6141   1.0000
   4.000   0.7518   0.01336   0.00686  -0.0509   0.6079   1.0000
   4.250   0.7797   0.01349   0.00701  -0.0511   0.6028   1.0000
   4.500   0.8080   0.01361   0.00709  -0.0511   0.5987   1.0000
   4.750   0.8353   0.01383   0.00745  -0.0514   0.5913   1.0000
   5.000   0.8634   0.01385   0.00745  -0.0514   0.5853   1.0000
   5.250   0.8906   0.01397   0.00766  -0.0514   0.5768   1.0000
   5.500   0.9187   0.01394   0.00760  -0.0513   0.5694   1.0000
   5.750   0.9455   0.01398   0.00774  -0.0512   0.5585   1.0000
   6.000   0.9726   0.01399   0.00780  -0.0511   0.5479   1.0000
   6.250   0.9999   0.01397   0.00777  -0.0509   0.5372   1.0000
   6.500   1.0264   0.01392   0.00777  -0.0506   0.5228   1.0000
   6.750   1.0523   0.01390   0.00784  -0.0504   0.5058   1.0000
   7.000   1.0782   0.01392   0.00797  -0.0502   0.4874   1.0000
   7.250   1.1039   0.01398   0.00812  -0.0499   0.4672   1.0000
   7.500   1.1286   0.01412   0.00829  -0.0496   0.4392   1.0000
   7.750   1.1505   0.01449   0.00851  -0.0490   0.3942   1.0000
   8.000   1.1678   0.01538   0.00910  -0.0480   0.3339   1.0000
   8.250   1.1801   0.01677   0.01011  -0.0467   0.2691   1.0000
   8.500   1.1890   0.01844   0.01142  -0.0452   0.2021   1.0000
   8.750   1.1881   0.02083   0.01323  -0.0430   0.1245   1.0000
   9.000   1.1894   0.02280   0.01500  -0.0409   0.0941   1.0000
   9.250   1.1913   0.02472   0.01682  -0.0390   0.0771   1.0000
   9.500   1.1918   0.02686   0.01891  -0.0374   0.0664   1.0000
   9.750   1.1952   0.02887   0.02095  -0.0361   0.0584   1.0000
  10.000   1.1969   0.03108   0.02323  -0.0347   0.0529   1.0000
  10.250   1.2018   0.03307   0.02525  -0.0336   0.0485   1.0000
  10.500   1.2006   0.03561   0.02775  -0.0319   0.0455   1.0000
  10.750   1.2100   0.03727   0.02954  -0.0309   0.0429   1.0000
  11.000   1.2182   0.03902   0.03135  -0.0300   0.0404   1.0000
  11.250   1.2255   0.04086   0.03319  -0.0290   0.0383   1.0000
  11.500   1.2352   0.04267   0.03497  -0.0269   0.0364   1.0000
  11.750   1.2480   0.04419   0.03663  -0.0258   0.0354   1.0000
  12.000   1.2616   0.04575   0.03833  -0.0245   0.0343   1.0000
  12.250   1.2758   0.04738   0.04007  -0.0233   0.0332   1.0000
  12.500   1.2886   0.04918   0.04200  -0.0222   0.0323   1.0000
  12.750   1.2993   0.05109   0.04401  -0.0213   0.0313   1.0000
  13.000   1.3110   0.05305   0.04602  -0.0204   0.0302   1.0000
  13.250   1.3319   0.05633   0.04944  -0.0188   0.0291   1.0000
  13.500   1.3320   0.05918   0.05254  -0.0180   0.0289   1.0000
  13.750   1.3298   0.06238   0.05601  -0.0174   0.0287   1.0000
  14.000   1.3250   0.06596   0.05984  -0.0168   0.0286   1.0000
  14.250   1.3172   0.06991   0.06406  -0.0166   0.0285   1.0000
  14.500   1.3065   0.07423   0.06864  -0.0166   0.0284   1.0000
  14.750   1.2931   0.07895   0.07361  -0.0170   0.0284   1.0000
  15.000   1.2774   0.08403   0.07892  -0.0178   0.0285   1.0000
  15.250   1.2599   0.08950   0.08462  -0.0191   0.0285   1.0000
  15.500   1.2409   0.09543   0.09077  -0.0209   0.0286   1.0000
  15.750   1.2212   0.10184   0.09738  -0.0233   0.0287   1.0000
  16.000   1.2007   0.10879   0.10452  -0.0263   0.0288   1.0000
  16.250   1.1805   0.11623   0.11213  -0.0296   0.0290   1.0000
  16.500   1.1632   0.12336   0.11943  -0.0334   0.0292   1.0000
  16.750   1.1447   0.13109   0.12735  -0.0387   0.0294   1.0000
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