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BOEING-VERTOL VR-5 AIRFOIL (vr5-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: BOEING-VERTOL VR-5 AIRFOIL (vr5-il)
Reynolds number: 50,000
Max Cl/Cd: 31.68 at α=9.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-vr5-il-50000.txt
Download as CSV file: xf-vr5-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3966   0.10941   0.10332  -0.0150   1.0000   0.2205
  -9.000  -0.4082   0.10787   0.10190  -0.0184   1.0000   0.2318
  -8.750  -0.4011   0.10446   0.09854  -0.0189   1.0000   0.2474
  -8.500  -0.3790   0.09974   0.09385  -0.0173   1.0000   0.2666
  -8.250  -0.3654   0.09639   0.09052  -0.0168   1.0000   0.2872
  -8.000  -0.3704   0.09437   0.08861  -0.0178   1.0000   0.3078
  -7.750  -0.3505   0.09075   0.08502  -0.0162   1.0000   0.3338
  -7.500  -0.3414   0.08802   0.08236  -0.0149   1.0000   0.3613
  -7.250  -0.3573   0.08742   0.08191  -0.0128   1.0000   0.3849
  -7.000  -0.3528   0.08554   0.08010  -0.0087   1.0000   0.4158
  -6.750  -0.3202   0.08220   0.07673  -0.0048   1.0000   0.4725
  -6.500  -0.3126   0.08076   0.07535   0.0000   1.0000   0.5193
  -6.250  -0.3045   0.07924   0.07388   0.0046   1.0000   0.5667
  -6.000  -0.3234   0.07968   0.07444   0.0111   1.0000   0.6011
  -5.750  -0.2732   0.07511   0.06981   0.0115   1.0000   0.6781
  -4.250  -0.3531   0.06736   0.06255   0.0279   0.9957   0.6869
  -4.000  -0.3491   0.04580   0.03800  -0.0450   0.9774   0.1826
  -3.750  -0.3012   0.04249   0.03387  -0.0491   0.9722   0.1596
  -3.500  -0.2655   0.04084   0.03146  -0.0508   0.9661   0.1537
  -3.250  -0.2238   0.03859   0.02882  -0.0536   0.9606   0.1501
  -3.000  -0.1903   0.03727   0.02706  -0.0549   0.9550   0.1516
  -2.750  -0.1544   0.03632   0.02561  -0.0565   0.9493   0.1545
  -2.500  -0.1156   0.03503   0.02421  -0.0585   0.9442   0.1585
  -2.250  -0.0895   0.03443   0.02351  -0.0584   0.9385   0.1675
  -2.000  -0.0547   0.03378   0.02283  -0.0594   0.9332   0.1767
  -1.750  -0.0250   0.03338   0.02237  -0.0600   0.9281   0.1902
  -1.500   0.0014   0.03295   0.02199  -0.0604   0.9227   0.2148
  -1.250   0.0334   0.03029   0.02191  -0.0615   0.9182   0.6575
  -1.000   0.0461   0.03032   0.02217  -0.0542   0.9132   1.0000
  -0.750   0.0673   0.03098   0.02233  -0.0543   0.9076   1.0000
  -0.500   0.1033   0.03189   0.02282  -0.0569   0.9017   1.0000
  -0.250   0.1174   0.03257   0.02325  -0.0562   0.8967   1.0000
   0.000   0.1420   0.03341   0.02383  -0.0571   0.8910   1.0000
   0.250   0.1732   0.03441   0.02458  -0.0590   0.8855   1.0000
   0.500   0.1875   0.03523   0.02523  -0.0583   0.8807   1.0000
   0.750   0.2133   0.03622   0.02604  -0.0594   0.8752   1.0000
   1.000   0.2395   0.03731   0.02697  -0.0606   0.8699   1.0000
   1.250   0.2540   0.03827   0.02782  -0.0601   0.8654   1.0000
   1.500   0.2786   0.03940   0.02884  -0.0611   0.8602   1.0000
   1.750   0.3030   0.04061   0.02996  -0.0620   0.8548   1.0000
   2.000   0.3163   0.04172   0.03099  -0.0615   0.8504   1.0000
   2.250   0.3408   0.04299   0.03220  -0.0625   0.8450   1.0000
   2.500   0.3615   0.04431   0.03346  -0.0630   0.8389   1.0000
   2.750   0.3765   0.04556   0.03468  -0.0627   0.8333   1.0000
   3.000   0.4034   0.04693   0.03602  -0.0638   0.8235   1.0000
   3.250   0.4373   0.04829   0.03736  -0.0656   0.8111   1.0000
   3.500   0.4516   0.04945   0.03852  -0.0650   0.8000   1.0000
   3.750   0.4715   0.05074   0.03983  -0.0650   0.7879   1.0000
   4.000   0.4954   0.05206   0.04116  -0.0654   0.7751   1.0000
   4.250   0.5211   0.05340   0.04253  -0.0660   0.7622   1.0000
   4.500   0.5486   0.05474   0.04392  -0.0666   0.7490   1.0000
   4.750   0.5782   0.05605   0.04531  -0.0674   0.7354   1.0000
   5.000   0.5941   0.05751   0.04683  -0.0671   0.7229   1.0000
   5.250   0.6086   0.05906   0.04844  -0.0665   0.7096   1.0000
   5.500   0.6257   0.06065   0.05011  -0.0663   0.6961   1.0000
   5.750   0.6448   0.06224   0.05181  -0.0661   0.6821   1.0000
   6.000   0.6640   0.06390   0.05356  -0.0660   0.6685   1.0000
   6.250   0.6849   0.06559   0.05535  -0.0661   0.6553   1.0000
   6.500   0.7078   0.06718   0.05706  -0.0661   0.6417   1.0000
   6.750   0.7376   0.06857   0.05863  -0.0665   0.6287   1.0000
   7.000   0.7325   0.07131   0.06144  -0.0655   0.6172   1.0000
   7.250   0.7405   0.07363   0.06386  -0.0650   0.6050   1.0000
   7.500   0.7544   0.07575   0.06610  -0.0648   0.5928   1.0000
   7.750   0.7724   0.07726   0.06775  -0.0641   0.5765   1.0000
   8.000   0.8188   0.07654   0.06730  -0.0632   0.5549   1.0000
   8.250   0.8362   0.07755   0.06847  -0.0619   0.5366   1.0000
   8.500   0.8488   0.07910   0.07018  -0.0609   0.5200   1.0000
   8.750   0.8625   0.08044   0.07171  -0.0597   0.5021   1.0000
   9.000   0.9189   0.07643   0.06808  -0.0564   0.4763   1.0000
   9.250   1.1485   0.04135   0.03437  -0.0397   0.4183   1.0000
   9.500   1.1681   0.03687   0.02938  -0.0326   0.3314   1.0000
   9.750   1.1569   0.03907   0.03068  -0.0281   0.2636   1.0000
  10.000   1.1517   0.04198   0.03300  -0.0251   0.2188   1.0000
  10.250   1.1538   0.04453   0.03518  -0.0229   0.1879   1.0000
  10.500   1.1610   0.04693   0.03745  -0.0211   0.1643   1.0000
  10.750   1.1860   0.04902   0.03931  -0.0195   0.1421   1.0000
  11.000   1.2232   0.05173   0.04201  -0.0188   0.1248   1.0000
  11.250   1.2531   0.05518   0.04560  -0.0185   0.1144   1.0000
  11.500   1.2746   0.05883   0.04954  -0.0179   0.1090   1.0000
  11.750   1.2983   0.06346   0.05432  -0.0181   0.1044   1.0000
  12.000   1.2870   0.06682   0.05811  -0.0157   0.1033   1.0000
  12.250   1.2728   0.07055   0.06221  -0.0139   0.1025   1.0000
  12.500   1.2556   0.07467   0.06666  -0.0127   0.1020   1.0000
  12.750   1.2356   0.07926   0.07155  -0.0121   0.1020   1.0000
  13.000   1.2128   0.08439   0.07695  -0.0122   0.1023   1.0000
  13.250   1.1882   0.09015   0.08293  -0.0132   0.1029   1.0000
  13.500   1.1631   0.09651   0.08948  -0.0148   0.1036   1.0000
  13.750   1.1391   0.10343   0.09655  -0.0171   0.1044   1.0000
  14.000   1.1177   0.11077   0.10397  -0.0198   0.1051   1.0000
  14.250   1.0082   0.13490   0.12825  -0.0372   0.1191   1.0000
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