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BOEING-VERTOL VR-5 AIRFOIL (vr5-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: BOEING-VERTOL VR-5 AIRFOIL (vr5-il)
Reynolds number: 1,000,000
Max Cl/Cd: 136.12 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-vr5-il-1000000.txt
Download as CSV file: xf-vr5-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5007   0.09435   0.09243  -0.0030   0.8182   0.0134
  -9.250  -0.4973   0.09090   0.08895  -0.0049   0.8105   0.0135
  -9.000  -0.4933   0.08749   0.08553  -0.0069   0.8015   0.0137
  -8.750  -0.4905   0.08364   0.08166  -0.0096   0.7924   0.0138
  -8.500  -0.4892   0.07917   0.07716  -0.0136   0.7821   0.0140
  -8.250  -0.4928   0.07207   0.07003  -0.0237   0.7711   0.0141
  -8.000  -0.4884   0.06664   0.06450  -0.0292   0.7616   0.0143
  -7.750  -0.5706   0.02020   0.01576  -0.0406   0.7616   0.0120
  -7.500  -0.5476   0.01793   0.01309  -0.0404   0.7526   0.0124
  -7.250  -0.5222   0.01655   0.01146  -0.0403   0.7440   0.0128
  -7.000  -0.4958   0.01563   0.01031  -0.0403   0.7357   0.0130
  -6.750  -0.4707   0.01403   0.00845  -0.0401   0.7280   0.0135
  -6.500  -0.4437   0.01341   0.00772  -0.0401   0.7206   0.0140
  -6.250  -0.4156   0.01310   0.00737  -0.0403   0.7138   0.0145
  -6.000  -0.3877   0.01276   0.00695  -0.0403   0.7071   0.0152
  -5.750  -0.3597   0.01237   0.00648  -0.0404   0.7010   0.0159
  -5.500  -0.3313   0.01215   0.00617  -0.0406   0.6946   0.0166
  -5.250  -0.3042   0.01149   0.00544  -0.0406   0.6888   0.0177
  -5.000  -0.2756   0.01134   0.00528  -0.0408   0.6826   0.0186
  -4.750  -0.2472   0.01115   0.00502  -0.0409   0.6764   0.0197
  -4.500  -0.2184   0.01099   0.00482  -0.0411   0.6704   0.0208
  -4.250  -0.1909   0.01043   0.00421  -0.0412   0.6640   0.0224
  -4.000  -0.1621   0.01033   0.00409  -0.0414   0.6582   0.0238
  -3.750  -0.1332   0.01022   0.00396  -0.0416   0.6521   0.0254
  -3.500  -0.1049   0.00994   0.00362  -0.0418   0.6462   0.0270
  -3.250  -0.0766   0.00961   0.00328  -0.0420   0.6403   0.0288
  -3.000  -0.0478   0.00944   0.00309  -0.0422   0.6340   0.0304
  -2.750  -0.0190   0.00932   0.00292  -0.0424   0.6283   0.0319
  -2.500   0.0101   0.00924   0.00283  -0.0427   0.6227   0.0330
  -2.250   0.0384   0.00880   0.00233  -0.0429   0.6171   0.0354
  -2.000   0.0672   0.00863   0.00213  -0.0432   0.6116   0.0372
  -1.750   0.0963   0.00849   0.00197  -0.0434   0.6057   0.0390
  -1.500   0.1252   0.00840   0.00182  -0.0437   0.6003   0.0407
  -1.250   0.1543   0.00830   0.00170  -0.0440   0.5959   0.0420
  -1.000   0.1834   0.00812   0.00152  -0.0442   0.5914   0.0475
  -0.750   0.2125   0.00802   0.00141  -0.0445   0.5869   0.0575
  -0.500   0.2408   0.00752   0.00133  -0.0450   0.5825   0.2004
  -0.250   0.2668   0.00617   0.00122  -0.0456   0.5782   0.6158
   0.000   0.2953   0.00605   0.00123  -0.0458   0.5737   0.6700
   0.250   0.3239   0.00601   0.00125  -0.0460   0.5692   0.7061
   0.500   0.3525   0.00594   0.00129  -0.0461   0.5654   0.7421
   0.750   0.3811   0.00592   0.00133  -0.0462   0.5615   0.7724
   1.000   0.4096   0.00592   0.00136  -0.0464   0.5576   0.7925
   1.250   0.4376   0.00593   0.00141  -0.0464   0.5538   0.8197
   1.500   0.4653   0.00588   0.00147  -0.0463   0.5511   0.8469
   2.000   0.5212   0.00588   0.00157  -0.0463   0.5442   0.8823
   2.250   0.5488   0.00593   0.00163  -0.0462   0.5406   0.8979
   2.500   0.5764   0.00597   0.00169  -0.0461   0.5370   0.9131
   2.750   0.6038   0.00597   0.00174  -0.0460   0.5330   0.9278
   3.000   0.6304   0.00598   0.00178  -0.0457   0.5283   0.9432
   3.250   0.6574   0.00603   0.00182  -0.0455   0.5230   0.9606
   3.500   0.6902   0.00601   0.00185  -0.0466   0.5185   0.9795
   3.750   0.7244   0.00606   0.00190  -0.0481   0.5135   1.0000
   4.000   0.7535   0.00616   0.00198  -0.0486   0.5075   1.0000
   4.250   0.7829   0.00620   0.00205  -0.0490   0.5024   1.0000
   4.500   0.8119   0.00629   0.00213  -0.0495   0.4963   1.0000
   4.750   0.8410   0.00637   0.00221  -0.0499   0.4868   1.0000
   5.000   0.8697   0.00647   0.00229  -0.0502   0.4745   1.0000
   5.250   0.8984   0.00660   0.00239  -0.0506   0.4586   1.0000
   5.500   0.9264   0.00682   0.00252  -0.0510   0.4342   1.0000
   5.750   0.9538   0.00715   0.00272  -0.0513   0.4000   1.0000
   6.000   0.9803   0.00761   0.00301  -0.0515   0.3630   1.0000
   6.250   1.0048   0.00839   0.00347  -0.0516   0.2979   1.0000
   6.500   1.0298   0.00903   0.00391  -0.0517   0.2585   1.0000
   6.750   1.0557   0.00949   0.00426  -0.0519   0.2334   1.0000
   7.000   1.0809   0.01004   0.00466  -0.0520   0.2019   1.0000
   7.250   1.1017   0.01114   0.00537  -0.0518   0.1335   1.0000
   7.500   1.1248   0.01186   0.00594  -0.0517   0.1043   1.0000
   7.750   1.1473   0.01261   0.00651  -0.0515   0.0746   1.0000
   8.000   1.1704   0.01323   0.00705  -0.0513   0.0591   1.0000
   8.250   1.1936   0.01380   0.00757  -0.0512   0.0473   1.0000
   8.500   1.2161   0.01440   0.00811  -0.0509   0.0368   1.0000
   8.750   1.2380   0.01503   0.00870  -0.0506   0.0288   1.0000
   9.000   1.2588   0.01574   0.00937  -0.0501   0.0226   1.0000
   9.250   1.2800   0.01635   0.01000  -0.0497   0.0196   1.0000
   9.500   1.2992   0.01710   0.01077  -0.0491   0.0175   1.0000
   9.750   1.3192   0.01772   0.01144  -0.0485   0.0165   1.0000
  10.000   1.3372   0.01842   0.01218  -0.0478   0.0156   1.0000
  10.250   1.3511   0.01931   0.01310  -0.0467   0.0147   1.0000
  10.500   1.3608   0.02059   0.01445  -0.0454   0.0139   1.0000
  10.750   1.3738   0.02164   0.01557  -0.0445   0.0136   1.0000
  11.000   1.3868   0.02273   0.01672  -0.0437   0.0133   1.0000
  11.250   1.3986   0.02394   0.01800  -0.0429   0.0130   1.0000
  11.500   1.4094   0.02527   0.01940  -0.0421   0.0127   1.0000
  11.750   1.4192   0.02672   0.02092  -0.0413   0.0124   1.0000
  12.000   1.4281   0.02829   0.02255  -0.0406   0.0121   1.0000
  12.250   1.4361   0.02996   0.02429  -0.0399   0.0118   1.0000
  12.500   1.4427   0.03180   0.02620  -0.0393   0.0115   1.0000
  12.750   1.4459   0.03400   0.02846  -0.0386   0.0112   1.0000
  13.000   1.4449   0.03665   0.03120  -0.0378   0.0109   1.0000
  13.250   1.4393   0.03976   0.03443  -0.0369   0.0106   1.0000
  13.500   1.4388   0.04242   0.03719  -0.0363   0.0105   1.0000
  13.750   1.4437   0.04456   0.03941  -0.0360   0.0104   1.0000
  14.000   1.4469   0.04690   0.04183  -0.0356   0.0103   1.0000
  14.250   1.4499   0.04934   0.04436  -0.0354   0.0102   1.0000
  14.500   1.4519   0.05195   0.04705  -0.0352   0.0101   1.0000
  14.750   1.4534   0.05467   0.04986  -0.0352   0.0099   1.0000
  15.000   1.4549   0.05746   0.05274  -0.0352   0.0097   1.0000
  15.250   1.4557   0.06039   0.05575  -0.0354   0.0096   1.0000
  15.500   1.4567   0.06332   0.05877  -0.0356   0.0094   1.0000
  15.750   1.4568   0.06642   0.06195  -0.0359   0.0092   1.0000
  16.000   1.4562   0.06970   0.06531  -0.0363   0.0090   1.0000
  16.250   1.4546   0.07314   0.06883  -0.0369   0.0089   1.0000
  16.500   1.4519   0.07675   0.07254  -0.0375   0.0088   1.0000
  16.750   1.4484   0.08054   0.07641  -0.0382   0.0086   1.0000
  17.000   1.4441   0.08452   0.08047  -0.0391   0.0085   1.0000
  17.250   1.4385   0.08872   0.08476  -0.0400   0.0084   1.0000
  17.500   1.4310   0.09321   0.08934  -0.0411   0.0083   1.0000
  17.750   1.4215   0.09804   0.09428  -0.0423   0.0082   1.0000
  18.000   1.4096   0.10329   0.09964  -0.0437   0.0081   1.0000
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