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BOEING-VERTOL VR-7 AIRFOIL (vr7-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: BOEING-VERTOL VR-7 AIRFOIL (vr7-il)
Reynolds number: 50,000
Max Cl/Cd: 32.11 at α=8.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-vr7-il-50000-n5.txt
Download as CSV file: xf-vr7-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: BOEING-VERTOL VR-7 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  -0.3788   0.10875   0.10187  -0.0255   1.0000   0.1427
  -9.500  -0.4025   0.10695   0.10024  -0.0301   1.0000   0.1492
  -9.250  -0.4120   0.09277   0.08602  -0.0418   1.0000   0.0683
  -9.000  -0.4008   0.08963   0.08292  -0.0405   1.0000   0.0673
  -8.750  -0.3982   0.08596   0.07932  -0.0411   1.0000   0.0659
  -8.500  -0.4023   0.08181   0.07526  -0.0431   1.0000   0.0642
  -8.000  -0.4495   0.07136   0.06472  -0.0483   1.0000   0.0575
  -7.750  -0.4499   0.06829   0.06168  -0.0473   1.0000   0.0571
  -7.500  -0.4538   0.06529   0.05869  -0.0459   1.0000   0.0567
  -7.250  -0.4594   0.06257   0.05596  -0.0440   1.0000   0.0562
  -7.000  -0.4676   0.06030   0.05366  -0.0413   1.0000   0.0556
  -6.750  -0.4693   0.05755   0.05078  -0.0400   0.9960   0.0550
  -6.500  -0.4450   0.05282   0.04564  -0.0439   0.9804   0.0540
  -6.250  -0.4197   0.04857   0.04089  -0.0468   0.9660   0.0533
  -6.000  -0.3921   0.04476   0.03655  -0.0492   0.9532   0.0532
  -5.750  -0.3612   0.04148   0.03268  -0.0515   0.9421   0.0547
  -5.500  -0.3319   0.03875   0.02936  -0.0528   0.9300   0.0559
  -5.250  -0.3002   0.03627   0.02631  -0.0539   0.9192   0.0568
  -5.000  -0.2639   0.03398   0.02349  -0.0555   0.9108   0.0574
  -4.750  -0.2334   0.03205   0.02134  -0.0561   0.8995   0.0586
  -4.500  -0.2006   0.03050   0.01966  -0.0571   0.8898   0.0616
  -4.250  -0.1659   0.02914   0.01803  -0.0580   0.8809   0.0657
  -4.000  -0.1343   0.02802   0.01666  -0.0581   0.8708   0.0684
  -3.750  -0.1002   0.02673   0.01535  -0.0589   0.8631   0.0728
  -3.500  -0.0735   0.02601   0.01440  -0.0585   0.8522   0.0795
  -3.250  -0.0460   0.02509   0.01347  -0.0585   0.8431   0.0869
  -3.000  -0.0188   0.02430   0.01262  -0.0584   0.8339   0.0993
  -2.750   0.0046   0.02352   0.01192  -0.0577   0.8241   0.1234
  -2.500   0.0204   0.02129   0.01132  -0.0563   0.8161   0.3944
  -2.250   0.0343   0.02048   0.01189  -0.0507   0.8070   0.7567
  -2.000   0.1596   0.02083   0.01189  -0.0630   0.8046   0.9567
  -1.750   0.2099   0.02062   0.01131  -0.0676   0.7951   0.9753
  -1.500   0.2564   0.02040   0.01075  -0.0718   0.7853   0.9928
  -1.250   0.2834   0.02037   0.01051  -0.0726   0.7744   1.0000
  -1.000   0.3002   0.02042   0.01037  -0.0712   0.7648   1.0000
  -0.750   0.3165   0.02055   0.01032  -0.0696   0.7548   1.0000
  -0.500   0.3335   0.02074   0.01036  -0.0682   0.7452   1.0000
  -0.250   0.3540   0.02089   0.01033  -0.0671   0.7370   1.0000
   0.000   0.3717   0.02119   0.01051  -0.0658   0.7272   1.0000
   0.250   0.3944   0.02134   0.01049  -0.0649   0.7198   1.0000
   0.500   0.4119   0.02173   0.01079  -0.0635   0.7098   1.0000
   0.750   0.4340   0.02197   0.01090  -0.0625   0.7022   1.0000
   1.000   0.4534   0.02233   0.01118  -0.0613   0.6928   1.0000
   1.250   0.4748   0.02264   0.01141  -0.0602   0.6848   1.0000
   1.500   0.4956   0.02299   0.01168  -0.0591   0.6762   1.0000
   1.750   0.5163   0.02337   0.01201  -0.0579   0.6677   1.0000
   2.000   0.5383   0.02369   0.01227  -0.0569   0.6596   1.0000
   2.250   0.5582   0.02414   0.01270  -0.0557   0.6508   1.0000
   2.500   0.5814   0.02445   0.01295  -0.0548   0.6431   1.0000
   2.750   0.6005   0.02498   0.01351  -0.0536   0.6340   1.0000
   3.000   0.6246   0.02526   0.01375  -0.0528   0.6267   1.0000
   3.250   0.6427   0.02587   0.01440  -0.0515   0.6172   1.0000
   3.500   0.6678   0.02612   0.01464  -0.0508   0.6103   1.0000
   3.750   0.6849   0.02681   0.01540  -0.0495   0.6004   1.0000
   4.000   0.7111   0.02701   0.01559  -0.0488   0.5939   1.0000
   4.250   0.7271   0.02778   0.01645  -0.0474   0.5836   1.0000
   4.500   0.7534   0.02797   0.01668  -0.0468   0.5772   1.0000
   4.750   0.7695   0.02874   0.01755  -0.0455   0.5669   1.0000
   5.000   0.7911   0.02921   0.01810  -0.0445   0.5588   1.0000
   5.250   0.8127   0.02964   0.01863  -0.0435   0.5501   1.0000
   5.500   0.8306   0.03025   0.01934  -0.0421   0.5398   1.0000
   5.750   0.8599   0.03008   0.01921  -0.0415   0.5321   1.0000
   6.000   0.8753   0.03073   0.01999  -0.0399   0.5200   1.0000
   6.250   0.8938   0.03122   0.02061  -0.0385   0.5090   1.0000
   6.500   0.9234   0.03103   0.02050  -0.0380   0.5014   1.0000
   6.750   0.9368   0.03191   0.02154  -0.0363   0.4897   1.0000
   7.000   0.9546   0.03242   0.02219  -0.0348   0.4784   1.0000
   7.250   0.9777   0.03249   0.02240  -0.0336   0.4672   1.0000
   7.500   1.0036   0.03233   0.02234  -0.0326   0.4557   1.0000
   7.750   1.0177   0.03298   0.02316  -0.0308   0.4424   1.0000
   8.000   1.0330   0.03352   0.02389  -0.0290   0.4291   1.0000
   8.250   1.0506   0.03366   0.02414  -0.0272   0.4136   1.0000
   8.500   1.0710   0.03335   0.02386  -0.0253   0.3954   1.0000
   8.750   1.0783   0.03394   0.02455  -0.0226   0.3757   1.0000
   9.000   1.0861   0.03454   0.02526  -0.0200   0.3558   1.0000
   9.250   1.0933   0.03518   0.02594  -0.0173   0.3365   1.0000
   9.500   1.0967   0.03610   0.02692  -0.0145   0.3178   1.0000
   9.750   1.0976   0.03738   0.02827  -0.0120   0.2984   1.0000
  10.000   1.1002   0.03866   0.02957  -0.0098   0.2787   1.0000
  10.250   1.1015   0.04019   0.03107  -0.0079   0.2587   1.0000
  10.500   1.0999   0.04216   0.03304  -0.0063   0.2379   1.0000
  10.750   1.0981   0.04425   0.03502  -0.0049   0.2181   1.0000
  11.000   1.0951   0.04670   0.03740  -0.0039   0.1996   1.0000
  11.250   1.0923   0.04928   0.03989  -0.0030   0.1832   1.0000
  11.500   1.0897   0.05200   0.04255  -0.0023   0.1684   1.0000
  11.750   1.0877   0.05479   0.04532  -0.0018   0.1551   1.0000
  12.000   1.0858   0.05766   0.04817  -0.0014   0.1432   1.0000
  12.250   1.0851   0.06042   0.05088  -0.0011   0.1333   1.0000
  12.500   1.0841   0.06346   0.05401  -0.0010   0.1235   1.0000
  12.750   1.0842   0.06638   0.05697  -0.0009   0.1154   1.0000
  13.000   1.0845   0.06931   0.05996  -0.0009   0.1079   1.0000
  13.250   1.0846   0.07249   0.06325  -0.0010   0.1013   1.0000
  13.500   1.0858   0.07541   0.06620  -0.0012   0.0954   1.0000
  13.750   1.0863   0.07870   0.06963  -0.0014   0.0903   1.0000
  14.000   1.0854   0.08225   0.07335  -0.0020   0.0857   1.0000
  14.250   1.0940   0.08423   0.07519  -0.0015   0.0812   1.0000
  14.500   1.0864   0.08923   0.08056  -0.0029   0.0784   1.0000
  14.750   1.0789   0.09428   0.08589  -0.0045   0.0758   1.0000
  15.000   1.0723   0.09918   0.09099  -0.0061   0.0734   1.0000
  15.250   1.0787   0.10163   0.09341  -0.0063   0.0701   1.0000
  15.500   1.0686   0.10742   0.09938  -0.0086   0.0687   1.0000
  15.750   1.0454   0.11606   0.10830  -0.0131   0.0681   1.0000
  16.000   1.0168   0.12659   0.11903  -0.0190   0.0681   1.0000
  16.250   0.9795   0.14036   0.13295  -0.0269   0.0682   1.0000
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