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BOEING-VERTOL VR-5 AIRFOIL (vr5-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: BOEING-VERTOL VR-5 AIRFOIL (vr5-il)
Reynolds number: 100,000
Max Cl/Cd: 55.23 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-vr5-il-100000.txt
Download as CSV file: xf-vr5-il-100000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2906   0.09866   0.09459  -0.0326   1.0000   0.0911
  -9.500  -0.3056   0.09552   0.09152  -0.0380   1.0000   0.0927
  -9.250  -0.3218   0.09222   0.08829  -0.0434   1.0000   0.0932
  -9.000  -0.2845   0.08702   0.08309  -0.0377   1.0000   0.0981
  -8.750  -0.2923   0.08537   0.08153  -0.0364   1.0000   0.1003
  -8.500  -0.2989   0.08287   0.07908  -0.0372   0.9961   0.1031
  -8.250  -0.3089   0.07710   0.07333  -0.0476   0.9868   0.1073
  -8.000  -0.4499   0.08665   0.08241  -0.0497   0.9903   0.0934
  -7.750  -0.4089   0.08178   0.07789  -0.0388   0.9946   0.0997
  -7.500  -0.3994   0.07590   0.07147  -0.0608   0.9758   0.1083
  -7.250  -0.3667   0.06924   0.06510  -0.0601   0.9736   0.1123
  -7.000  -0.3515   0.06629   0.06150  -0.0713   0.9593   0.1242
  -6.750  -0.3249   0.06047   0.05606  -0.0702   0.9525   0.1286
  -6.500  -0.3096   0.05695   0.05220  -0.0748   0.9402   0.1413
  -6.250  -0.2907   0.05421   0.04919  -0.0771   0.9301   0.1559
  -6.000  -0.2717   0.05087   0.04601  -0.0762   0.9199   0.1649
  -5.750  -0.2600   0.04836   0.04330  -0.0768   0.9086   0.1882
  -5.500  -0.2428   0.04593   0.04092  -0.0758   0.9005   0.2095
  -5.250  -0.2300   0.04387   0.03884  -0.0746   0.8902   0.2395
  -5.000  -0.2178   0.04244   0.03724  -0.0738   0.8803   0.2796
  -4.750  -0.2006   0.03996   0.03489  -0.0716   0.8730   0.3051
  -4.500  -0.1534   0.03508   0.02847  -0.0771   0.8634   0.1895
  -4.250  -0.1072   0.03086   0.02254  -0.0749   0.8579   0.0920
  -4.000  -0.0822   0.02898   0.02040  -0.0744   0.8495   0.0907
  -3.750  -0.0555   0.02805   0.01904  -0.0734   0.8434   0.0932
  -3.500  -0.0298   0.02651   0.01731  -0.0730   0.8355   0.0943
  -3.250  -0.0041   0.02519   0.01598  -0.0724   0.8294   0.0987
  -3.000   0.0219   0.02448   0.01519  -0.0720   0.8226   0.1036
  -2.750   0.0484   0.02380   0.01439  -0.0714   0.8163   0.1071
  -2.500   0.0731   0.02291   0.01359  -0.0703   0.8119   0.1144
  -2.250   0.0977   0.02263   0.01332  -0.0702   0.8037   0.1228
  -2.000   0.1214   0.02199   0.01276  -0.0692   0.7988   0.1341
  -1.750   0.1452   0.02156   0.01240  -0.0688   0.7929   0.1603
  -1.500   0.1458   0.01934   0.01277  -0.0627   0.7868   0.7780
  -1.250   0.1525   0.01958   0.01312  -0.0546   0.7828   0.8927
  -1.000   0.3028   0.01919   0.01223  -0.0727   0.7825   1.0000
  -0.750   0.3240   0.01953   0.01248  -0.0732   0.7752   1.0000
  -0.500   0.3429   0.01966   0.01249  -0.0724   0.7696   1.0000
  -0.250   0.3614   0.01987   0.01261  -0.0717   0.7644   1.0000
   0.000   0.3786   0.02031   0.01299  -0.0713   0.7572   1.0000
   0.250   0.3962   0.02042   0.01299  -0.0699   0.7529   1.0000
   0.500   0.4106   0.02107   0.01361  -0.0691   0.7459   1.0000
   0.750   0.4268   0.02145   0.01391  -0.0679   0.7403   1.0000
   1.000   0.4470   0.02154   0.01390  -0.0664   0.7368   1.0000
   1.250   0.4614   0.02255   0.01489  -0.0661   0.7286   1.0000
   1.500   0.4845   0.02286   0.01514  -0.0656   0.7241   1.0000
   1.750   0.5110   0.02293   0.01512  -0.0649   0.7211   1.0000
   2.000   0.5284   0.02419   0.01639  -0.0654   0.7120   1.0000
   2.250   0.5550   0.02438   0.01655  -0.0650   0.7079   1.0000
   2.500   0.5765   0.02522   0.01739  -0.0651   0.7009   1.0000
   2.750   0.6024   0.02536   0.01750  -0.0646   0.6940   1.0000
   3.000   0.6290   0.02533   0.01745  -0.0638   0.6872   1.0000
   3.250   0.6541   0.02544   0.01757  -0.0631   0.6785   1.0000
   3.500   0.6853   0.02487   0.01695  -0.0620   0.6749   1.0000
   3.750   0.7038   0.02609   0.01826  -0.0623   0.6640   1.0000
   4.000   0.7340   0.02579   0.01796  -0.0616   0.6603   1.0000
   4.250   0.7528   0.02698   0.01926  -0.0617   0.6499   1.0000
   4.500   0.7832   0.02663   0.01893  -0.0610   0.6457   1.0000
   4.750   0.8029   0.02764   0.02004  -0.0609   0.6354   1.0000
   5.000   0.8336   0.02724   0.01970  -0.0602   0.6307   1.0000
   5.250   0.8532   0.02823   0.02082  -0.0600   0.6204   1.0000
   5.500   0.8846   0.02774   0.02038  -0.0593   0.6156   1.0000
   5.750   0.9052   0.02850   0.02127  -0.0589   0.6047   1.0000
   6.000   0.9398   0.02743   0.02026  -0.0579   0.5997   1.0000
   6.250   0.9627   0.02766   0.02063  -0.0571   0.5877   1.0000
   6.500   0.9897   0.02721   0.02028  -0.0561   0.5765   1.0000
   6.750   1.0229   0.02577   0.01890  -0.0546   0.5657   1.0000
   7.000   1.0541   0.02441   0.01756  -0.0532   0.5518   1.0000
   7.250   1.0812   0.02361   0.01685  -0.0519   0.5354   1.0000
   7.500   1.1070   0.02298   0.01634  -0.0507   0.5170   1.0000
   7.750   1.1330   0.02225   0.01569  -0.0494   0.4967   1.0000
   8.000   1.1555   0.02188   0.01546  -0.0482   0.4723   1.0000
   8.250   1.1765   0.02163   0.01536  -0.0468   0.4416   1.0000
   8.500   1.1941   0.02162   0.01533  -0.0451   0.3974   1.0000
   8.750   1.2013   0.02254   0.01586  -0.0425   0.3231   1.0000
   9.000   1.1917   0.02499   0.01762  -0.0390   0.2380   1.0000
   9.250   1.1760   0.02797   0.02003  -0.0357   0.1711   1.0000
   9.500   1.1646   0.03102   0.02266  -0.0332   0.1386   1.0000
   9.750   1.1577   0.03387   0.02524  -0.0311   0.1198   1.0000
  10.000   1.1572   0.03633   0.02753  -0.0291   0.1048   1.0000
  10.250   1.1615   0.03846   0.02958  -0.0275   0.0927   1.0000
  10.500   1.1713   0.04028   0.03144  -0.0258   0.0833   1.0000
  10.750   1.1866   0.04197   0.03307  -0.0241   0.0756   1.0000
  11.000   1.2060   0.04359   0.03453  -0.0227   0.0686   1.0000
  11.250   1.2333   0.04542   0.03652  -0.0214   0.0641   1.0000
  11.500   1.2592   0.04746   0.03875  -0.0206   0.0608   1.0000
  11.750   1.2890   0.04991   0.04120  -0.0203   0.0575   1.0000
  12.000   1.3098   0.05348   0.04500  -0.0198   0.0552   1.0000
  12.250   1.3109   0.05615   0.04804  -0.0182   0.0542   1.0000
  12.500   1.3119   0.05938   0.05162  -0.0167   0.0537   1.0000
  12.750   1.3083   0.06290   0.05547  -0.0154   0.0534   1.0000
  13.000   1.3005   0.06669   0.05959  -0.0142   0.0533   1.0000
  13.250   1.2891   0.07079   0.06399  -0.0134   0.0533   1.0000
  13.500   1.2747   0.07522   0.06871  -0.0129   0.0535   1.0000
  13.750   1.2576   0.08002   0.07378  -0.0129   0.0537   1.0000
  14.000   1.2384   0.08521   0.07923  -0.0135   0.0540   1.0000
  14.250   1.2174   0.09084   0.08508  -0.0147   0.0543   1.0000
  14.500   1.1954   0.09691   0.09135  -0.0164   0.0547   1.0000
  14.750   1.1731   0.10345   0.09807  -0.0187   0.0551   1.0000
  15.000   1.1522   0.11041   0.10518  -0.0214   0.0556   1.0000
  15.250   1.1369   0.11743   0.11235  -0.0240   0.0562   1.0000
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