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


Details Polar file
Airfoil: BOEING-VERTOL VR-5 AIRFOIL (vr5-il)
Reynolds number: 50,000
Max Cl/Cd: 29.49 at α=8.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-vr5-il-50000-n5.txt
Download as CSV file: xf-vr5-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3980   0.11251   0.10620  -0.0198   1.0000   0.1138
  -9.500  -0.3995   0.10937   0.10314  -0.0235   1.0000   0.1189
  -9.250  -0.4156   0.10676   0.10067  -0.0313   1.0000   0.1211
  -9.000  -0.3891   0.10160   0.09550  -0.0276   1.0000   0.1255
  -8.750  -0.3821   0.09817   0.09211  -0.0292   1.0000   0.1307
  -8.500  -0.4016   0.09536   0.08949  -0.0370   1.0000   0.1363
  -8.250  -0.3967   0.09128   0.08549  -0.0376   1.0000   0.1388
  -8.000  -0.3879   0.08815   0.08240  -0.0365   1.0000   0.1420
  -7.500  -0.3909   0.07104   0.06462  -0.0593   0.9683   0.0622
  -7.250  -0.3691   0.06644   0.05998  -0.0621   0.9584   0.0605
  -7.000  -0.3508   0.06190   0.05522  -0.0656   0.9468   0.0589
  -6.750  -0.3343   0.05769   0.05071  -0.0683   0.9344   0.0576
  -6.500  -0.3173   0.05382   0.04650  -0.0702   0.9228   0.0568
  -6.250  -0.2985   0.05042   0.04270  -0.0716   0.9122   0.0576
  -6.000  -0.2781   0.04729   0.03911  -0.0725   0.9024   0.0589
  -5.750  -0.2591   0.04450   0.03585  -0.0725   0.8916   0.0597
  -5.500  -0.2373   0.04180   0.03266  -0.0725   0.8825   0.0600
  -5.250  -0.2138   0.03946   0.02973  -0.0723   0.8737   0.0615
  -5.000  -0.1917   0.03736   0.02730  -0.0720   0.8646   0.0641
  -4.750  -0.1662   0.03554   0.02525  -0.0719   0.8573   0.0664
  -4.500  -0.1423   0.03404   0.02345  -0.0714   0.8482   0.0691
  -4.250  -0.1147   0.03263   0.02161  -0.0710   0.8418   0.0734
  -4.000  -0.0892   0.03140   0.02001  -0.0703   0.8330   0.0756
  -3.750  -0.0620   0.03009   0.01867  -0.0699   0.8270   0.0796
  -3.500  -0.0372   0.02932   0.01779  -0.0692   0.8186   0.0853
  -3.250  -0.0096   0.02849   0.01671  -0.0684   0.8126   0.0893
  -3.000   0.0145   0.02778   0.01598  -0.0677   0.8052   0.0943
  -2.750   0.0395   0.02726   0.01533  -0.0671   0.7987   0.1033
  -2.500   0.0627   0.02671   0.01473  -0.0665   0.7922   0.1116
  -2.250   0.0862   0.02624   0.01416  -0.0659   0.7852   0.1239
  -2.000   0.1111   0.02552   0.01350  -0.0655   0.7805   0.1541
  -1.750   0.1178   0.02328   0.01362  -0.0626   0.7729   0.6114
  -1.500   0.1286   0.02325   0.01401  -0.0559   0.7679   0.8225
  -1.250   0.2599   0.02289   0.01317  -0.0705   0.7675   1.0000
  -1.000   0.2767   0.02313   0.01323  -0.0697   0.7603   1.0000
  -0.750   0.2939   0.02332   0.01324  -0.0687   0.7540   1.0000
  -0.500   0.3111   0.02353   0.01328  -0.0675   0.7483   1.0000
  -0.250   0.3262   0.02389   0.01352  -0.0663   0.7410   1.0000
   0.000   0.3453   0.02405   0.01351  -0.0651   0.7362   1.0000
   0.250   0.3600   0.02457   0.01391  -0.0640   0.7290   1.0000
   0.500   0.3797   0.02488   0.01408  -0.0631   0.7233   1.0000
   0.750   0.4023   0.02511   0.01417  -0.0624   0.7189   1.0000
   1.000   0.4198   0.02577   0.01475  -0.0618   0.7111   1.0000
   1.250   0.4440   0.02605   0.01492  -0.0614   0.7064   1.0000
   1.500   0.4656   0.02658   0.01538  -0.0610   0.7004   1.0000
   1.750   0.4873   0.02713   0.01588  -0.0607   0.6938   1.0000
   2.000   0.5137   0.02739   0.01606  -0.0605   0.6897   1.0000
   2.250   0.5331   0.02821   0.01686  -0.0602   0.6823   1.0000
   2.500   0.5571   0.02868   0.01731  -0.0600   0.6767   1.0000
   2.750   0.5849   0.02890   0.01751  -0.0598   0.6730   1.0000
   3.000   0.6015   0.03001   0.01865  -0.0596   0.6642   1.0000
   3.250   0.6277   0.03037   0.01902  -0.0594   0.6594   1.0000
   3.500   0.6479   0.03122   0.01992  -0.0592   0.6523   1.0000
   3.750   0.6714   0.03174   0.02048  -0.0589   0.6454   1.0000
   4.000   0.6953   0.03213   0.02091  -0.0584   0.6379   1.0000
   4.250   0.7196   0.03239   0.02122  -0.0577   0.6292   1.0000
   4.500   0.7406   0.03292   0.02184  -0.0570   0.6194   1.0000
   4.750   0.7689   0.03287   0.02185  -0.0565   0.6128   1.0000
   5.000   0.7865   0.03379   0.02288  -0.0559   0.6026   1.0000
   5.250   0.8160   0.03369   0.02291  -0.0554   0.5970   1.0000
   5.500   0.8319   0.03477   0.02411  -0.0548   0.5862   1.0000
   5.750   0.8633   0.03450   0.02396  -0.0543   0.5813   1.0000
   6.000   0.8776   0.03570   0.02532  -0.0536   0.5697   1.0000
   6.250   0.8980   0.03637   0.02617  -0.0530   0.5605   1.0000
   6.500   0.9243   0.03649   0.02645  -0.0523   0.5529   1.0000
   6.750   0.9396   0.03755   0.02770  -0.0515   0.5414   1.0000
   7.000   0.9732   0.03698   0.02734  -0.0509   0.5357   1.0000
   7.250   0.9874   0.03795   0.02851  -0.0498   0.5223   1.0000
   7.500   1.0047   0.03846   0.02922  -0.0485   0.5087   1.0000
   7.750   1.0256   0.03834   0.02929  -0.0471   0.4939   1.0000
   8.000   1.0514   0.03727   0.02843  -0.0452   0.4763   1.0000
   8.250   1.0627   0.03745   0.02877  -0.0431   0.4538   1.0000
   8.500   1.0822   0.03670   0.02815  -0.0410   0.4303   1.0000
   8.750   1.0875   0.03767   0.02927  -0.0391   0.4057   1.0000
   9.000   1.1018   0.03783   0.02953  -0.0373   0.3770   1.0000
   9.250   1.1145   0.03809   0.02971  -0.0352   0.3406   1.0000
   9.500   1.1191   0.03936   0.03081  -0.0333   0.2989   1.0000
   9.750   1.1190   0.04127   0.03243  -0.0315   0.2578   1.0000
  10.000   1.1141   0.04400   0.03493  -0.0302   0.2194   1.0000
  10.250   1.1078   0.04713   0.03787  -0.0293   0.1823   1.0000
  10.500   1.1007   0.05044   0.04091  -0.0285   0.1553   1.0000
  10.750   1.0945   0.05377   0.04401  -0.0278   0.1373   1.0000
  11.000   1.0904   0.05697   0.04705  -0.0271   0.1234   1.0000
  11.250   1.0887   0.05996   0.04996  -0.0263   0.1119   1.0000
  11.500   1.0904   0.06270   0.05274  -0.0256   0.1009   1.0000
  11.750   1.0933   0.06533   0.05542  -0.0249   0.0920   1.0000
  12.000   1.0961   0.06793   0.05795  -0.0242   0.0852   1.0000
  12.250   1.1012   0.07046   0.06065  -0.0236   0.0780   1.0000
  12.500   1.1072   0.07275   0.06289  -0.0228   0.0728   1.0000
  12.750   1.1156   0.07509   0.06553  -0.0220   0.0675   1.0000
  13.000   1.1253   0.07715   0.06763  -0.0211   0.0635   1.0000
  13.250   1.1373   0.07926   0.06988  -0.0200   0.0599   1.0000
  13.500   1.1421   0.08239   0.07333  -0.0198   0.0569   1.0000
  13.750   1.1459   0.08557   0.07673  -0.0196   0.0545   1.0000
  14.000   1.1505   0.08873   0.08007  -0.0195   0.0528   1.0000
  14.250   1.1573   0.09173   0.08317  -0.0191   0.0513   1.0000
  14.500   1.1562   0.09595   0.08762  -0.0196   0.0504   1.0000
  14.750   1.1431   0.10171   0.09370  -0.0215   0.0500   1.0000
  15.000   1.1272   0.10815   0.10043  -0.0242   0.0498   1.0000
  15.250   1.1089   0.11536   0.10787  -0.0277   0.0497   1.0000
  15.500   1.0886   0.12346   0.11619  -0.0320   0.0498   1.0000
  15.750   1.0668   0.13260   0.12552  -0.0374   0.0499   1.0000
  16.000   1.0444   0.14284   0.13590  -0.0437   0.0502   1.0000
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