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BOEING-VERTOL VR-1 AIRFOIL (vr1-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: BOEING-VERTOL VR-1 AIRFOIL (vr1-il)
Reynolds number: 200,000
Max Cl/Cd: 63.46 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-vr1-il-200000.txt
Download as CSV file: xf-vr1-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: BOEING-VERTOL VR-1 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.4871   0.10416   0.10019  -0.0309   1.0000   0.0672
 -10.500  -0.5139   0.09669   0.09281  -0.0399   1.0000   0.0704
 -10.250  -0.5620   0.08658   0.08270  -0.0526   1.0000   0.0708
 -10.000  -0.5195   0.08722   0.08342  -0.0424   1.0000   0.0725
  -9.750  -0.5083   0.08553   0.08173  -0.0406   1.0000   0.0738
  -9.500  -0.5069   0.08234   0.07857  -0.0412   1.0000   0.0754
  -9.250  -0.5151   0.07765   0.07394  -0.0440   1.0000   0.0772
  -9.000  -0.5418   0.07115   0.06746  -0.0493   1.0000   0.0782
  -8.750  -0.5719   0.06730   0.06359  -0.0483   1.0000   0.0791
  -8.500  -0.6266   0.06428   0.06025  -0.0450   1.0000   0.0821
  -8.000  -0.6516   0.05724   0.05313  -0.0386   1.0000   0.0845
  -7.750  -0.6477   0.05532   0.05128  -0.0358   1.0000   0.0856
  -7.500  -0.6489   0.05365   0.04961  -0.0325   1.0000   0.0872
  -7.250  -0.6526   0.05192   0.04782  -0.0291   1.0000   0.0894
  -7.000  -0.6666   0.04922   0.04456  -0.0261   0.9985   0.0971
  -6.750  -0.6370   0.04594   0.04142  -0.0282   0.9953   0.0997
  -6.500  -0.6140   0.04337   0.03836  -0.0302   0.9889   0.1113
  -6.250  -0.5894   0.02960   0.02253  -0.0276   0.9845   0.0501
  -6.000  -0.5612   0.02692   0.01962  -0.0282   0.9797   0.0492
  -5.750  -0.5286   0.02464   0.01706  -0.0294   0.9756   0.0478
  -5.500  -0.4924   0.02276   0.01490  -0.0310   0.9728   0.0466
  -5.250  -0.4611   0.02142   0.01338  -0.0316   0.9680   0.0462
  -5.000  -0.4276   0.02026   0.01210  -0.0327   0.9634   0.0463
  -4.750  -0.3907   0.01922   0.01102  -0.0345   0.9602   0.0468
  -4.500  -0.3517   0.01837   0.01014  -0.0368   0.9578   0.0484
  -4.250  -0.3256   0.01778   0.00951  -0.0365   0.9505   0.0498
  -4.000  -0.2909   0.01696   0.00870  -0.0379   0.9464   0.0513
  -3.750  -0.2539   0.01607   0.00787  -0.0400   0.9436   0.0537
  -3.500  -0.2255   0.01559   0.00738  -0.0403   0.9375   0.0567
  -3.250  -0.1927   0.01510   0.00686  -0.0413   0.9323   0.0616
  -3.000  -0.1568   0.01437   0.00630  -0.0430   0.9289   0.0853
  -2.750  -0.1424   0.01252   0.00592  -0.0414   0.9219   0.3902
  -2.500  -0.1240   0.01168   0.00589  -0.0394   0.9150   0.5792
  -2.250  -0.0954   0.01124   0.00596  -0.0388   0.9114   0.7123
  -2.000  -0.0727   0.01121   0.00614  -0.0369   0.9045   0.7815
  -1.750  -0.0446   0.01123   0.00625  -0.0360   0.8990   0.8291
  -1.500  -0.0103   0.01126   0.00628  -0.0364   0.8954   0.8616
  -1.250   0.0223   0.01146   0.00648  -0.0363   0.8909   0.8925
  -1.000   0.0621   0.01179   0.00680  -0.0375   0.8860   0.9173
  -0.750   0.1075   0.01193   0.00689  -0.0403   0.8823   0.9310
  -0.500   0.1558   0.01197   0.00687  -0.0441   0.8792   0.9393
  -0.250   0.2009   0.01197   0.00682  -0.0474   0.8752   0.9459
   0.000   0.2449   0.01202   0.00685  -0.0506   0.8689   0.9526
   0.250   0.2883   0.01199   0.00679  -0.0536   0.8639   0.9607
   0.500   0.3356   0.01192   0.00670  -0.0574   0.8597   0.9670
   0.750   0.3751   0.01186   0.00665  -0.0597   0.8498   0.9751
   1.000   0.4166   0.01165   0.00641  -0.0621   0.8391   0.9823
   1.250   0.4600   0.01134   0.00606  -0.0648   0.8272   0.9887
   1.500   0.5021   0.01104   0.00575  -0.0674   0.8119   0.9962
   1.750   0.5332   0.01075   0.00540  -0.0678   0.7937   1.0000
   2.000   0.5496   0.01059   0.00521  -0.0653   0.7735   1.0000
   2.250   0.5673   0.01046   0.00505  -0.0631   0.7541   1.0000
   2.500   0.5858   0.01036   0.00493  -0.0610   0.7350   1.0000
   2.750   0.6046   0.01028   0.00479  -0.0590   0.7136   1.0000
   3.000   0.6224   0.01024   0.00474  -0.0568   0.6874   1.0000
   3.250   0.6396   0.01023   0.00465  -0.0543   0.6535   1.0000
   3.500   0.6549   0.01032   0.00457  -0.0515   0.6015   1.0000
   3.750   0.6625   0.01081   0.00452  -0.0473   0.4851   1.0000
   4.000   0.6540   0.01243   0.00500  -0.0409   0.2723   1.0000
   4.500   0.6646   0.01465   0.00624  -0.0333   0.1279   1.0000
   4.750   0.6764   0.01536   0.00685  -0.0304   0.1114   1.0000
   5.000   0.6898   0.01603   0.00744  -0.0278   0.0997   1.0000
   5.250   0.7048   0.01665   0.00806  -0.0254   0.0909   1.0000
   5.500   0.7175   0.01757   0.00886  -0.0228   0.0841   1.0000
   5.750   0.7357   0.01807   0.00941  -0.0210   0.0784   1.0000
   6.000   0.7522   0.01885   0.01010  -0.0191   0.0737   1.0000
   6.250   0.7713   0.01977   0.01104  -0.0175   0.0703   1.0000
   6.500   0.7920   0.02052   0.01181  -0.0162   0.0672   1.0000
   6.750   0.8129   0.02128   0.01255  -0.0151   0.0643   1.0000
   7.000   0.8374   0.02284   0.01401  -0.0148   0.0614   1.0000
   7.250   0.8596   0.02359   0.01491  -0.0137   0.0597   1.0000
   7.500   0.8832   0.02467   0.01610  -0.0129   0.0580   1.0000
   7.750   0.9070   0.02587   0.01740  -0.0123   0.0564   1.0000
   8.000   0.9301   0.02711   0.01874  -0.0116   0.0552   1.0000
   8.250   0.9523   0.02837   0.02003  -0.0109   0.0538   1.0000
   8.500   0.9767   0.03091   0.02262  -0.0109   0.0523   1.0000
   8.750   0.9942   0.03258   0.02457  -0.0093   0.0516   1.0000
   9.000   1.0104   0.03451   0.02681  -0.0076   0.0512   1.0000
   9.250   1.0248   0.03691   0.02951  -0.0058   0.0509   1.0000
   9.500   1.0362   0.03961   0.03253  -0.0038   0.0509   1.0000
   9.750   1.0443   0.04250   0.03573  -0.0014   0.0510   1.0000
  10.000   1.0483   0.04551   0.03907   0.0012   0.0509   1.0000
  10.250   1.0490   0.04870   0.04257   0.0040   0.0510   1.0000
  10.500   1.0473   0.05214   0.04628   0.0068   0.0512   1.0000
  10.750   1.0581   0.05698   0.05118   0.0073   0.0523   1.0000
  11.000   0.9584   0.08257   0.07801   0.0137   0.0846   1.0000
  11.250   0.9281   0.08487   0.08046   0.0175   0.0845   1.0000
  11.500   0.8963   0.08803   0.08375   0.0191   0.0844   1.0000
  11.750   0.8588   0.09243   0.08828   0.0184   0.0843   1.0000
  12.000   0.8194   0.09893   0.09487   0.0148   0.0842   1.0000
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