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BOEING-VERTOL VR-1 AIRFOIL (vr1-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: BOEING-VERTOL VR-1 AIRFOIL (vr1-il)
Reynolds number: 50,000
Max Cl/Cd: 30.02 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-vr1-il-50000-n5.txt
Download as CSV file: xf-vr1-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.5356   0.08837   0.08047  -0.0460   1.0000   0.0579
 -10.000  -0.5393   0.08383   0.07597  -0.0480   1.0000   0.0574
  -9.750  -0.5504   0.07886   0.07104  -0.0505   1.0000   0.0568
  -9.500  -0.5658   0.07441   0.06659  -0.0519   1.0000   0.0563
  -9.250  -0.5845   0.07067   0.06285  -0.0514   1.0000   0.0558
  -9.000  -0.6014   0.06702   0.05913  -0.0502   1.0000   0.0554
  -8.750  -0.6153   0.06347   0.05546  -0.0486   1.0000   0.0550
  -8.500  -0.6261   0.06011   0.05195  -0.0465   1.0000   0.0546
  -8.250  -0.6341   0.05687   0.04850  -0.0441   1.0000   0.0543
  -8.000  -0.6392   0.05376   0.04515  -0.0416   1.0000   0.0541
  -7.750  -0.6407   0.05090   0.04201  -0.0389   1.0000   0.0539
  -7.500  -0.6399   0.04821   0.03903  -0.0362   1.0000   0.0538
  -7.250  -0.6366   0.04575   0.03626  -0.0334   1.0000   0.0541
  -7.000  -0.6309   0.04348   0.03368  -0.0308   1.0000   0.0547
  -6.750  -0.6232   0.04135   0.03121  -0.0283   1.0000   0.0556
  -6.500  -0.6132   0.03934   0.02884  -0.0258   1.0000   0.0564
  -6.250  -0.6010   0.03749   0.02664  -0.0236   1.0000   0.0571
  -6.000  -0.5866   0.03576   0.02457  -0.0216   1.0000   0.0577
  -5.750  -0.5706   0.03420   0.02275  -0.0197   1.0000   0.0581
  -5.500  -0.5537   0.03269   0.02115  -0.0181   1.0000   0.0590
  -5.250  -0.5364   0.03143   0.01981  -0.0165   1.0000   0.0600
  -5.000  -0.5187   0.03035   0.01863  -0.0149   1.0000   0.0613
  -4.750  -0.5011   0.02940   0.01760  -0.0132   1.0000   0.0637
  -4.500  -0.4831   0.02857   0.01663  -0.0116   1.0000   0.0664
  -4.250  -0.4651   0.02780   0.01574  -0.0099   1.0000   0.0691
  -4.000  -0.4452   0.02699   0.01492  -0.0089   0.9989   0.0722
  -3.750  -0.4129   0.02623   0.01406  -0.0101   0.9932   0.0769
  -3.500  -0.3814   0.02547   0.01325  -0.0113   0.9872   0.0845
  -3.250  -0.3492   0.02471   0.01252  -0.0127   0.9816   0.1015
  -3.000  -0.3205   0.02344   0.01172  -0.0137   0.9754   0.1687
  -2.750  -0.2967   0.02181   0.01142  -0.0141   0.9702   0.4023
  -2.500  -0.2829   0.02093   0.01210  -0.0096   0.9638   0.6949
  -2.250  -0.2389   0.02158   0.01311  -0.0087   0.9618   0.8704
  -2.000  -0.1684   0.02223   0.01344  -0.0154   0.9620   0.9325
  -1.750  -0.1014   0.02248   0.01334  -0.0230   0.9608   0.9609
  -1.500  -0.0420   0.02254   0.01312  -0.0299   0.9580   0.9804
  -1.250   0.0195   0.02256   0.01291  -0.0374   0.9561   1.0000
  -1.000   0.0428   0.02254   0.01276  -0.0379   0.9462   1.0000
  -0.750   0.0743   0.02260   0.01268  -0.0397   0.9387   1.0000
  -0.500   0.0968   0.02267   0.01265  -0.0397   0.9290   1.0000
  -0.250   0.1255   0.02279   0.01267  -0.0407   0.9212   1.0000
   0.000   0.1497   0.02293   0.01273  -0.0409   0.9122   1.0000
   0.250   0.1780   0.02310   0.01283  -0.0416   0.9045   1.0000
   0.500   0.2018   0.02329   0.01298  -0.0415   0.8956   1.0000
   0.750   0.2323   0.02349   0.01314  -0.0425   0.8884   1.0000
   1.000   0.2539   0.02373   0.01337  -0.0419   0.8790   1.0000
   1.250   0.2849   0.02394   0.01358  -0.0429   0.8720   1.0000
   1.500   0.3052   0.02422   0.01386  -0.0419   0.8621   1.0000
   1.750   0.3335   0.02446   0.01413  -0.0423   0.8543   1.0000
   2.000   0.3561   0.02474   0.01445  -0.0416   0.8446   1.0000
   2.250   0.3802   0.02502   0.01478  -0.0412   0.8354   1.0000
   2.500   0.4084   0.02523   0.01507  -0.0413   0.8265   1.0000
   2.750   0.4281   0.02555   0.01548  -0.0400   0.8155   1.0000
   3.000   0.4659   0.02556   0.01563  -0.0413   0.8075   1.0000
   3.250   0.4950   0.02540   0.01559  -0.0407   0.7917   1.0000
   3.500   0.5278   0.02449   0.01480  -0.0391   0.7635   1.0000
   3.750   0.5687   0.02275   0.01313  -0.0374   0.7234   1.0000
   4.000   0.5879   0.02217   0.01261  -0.0340   0.6876   1.0000
   4.250   0.6058   0.02185   0.01237  -0.0308   0.6507   1.0000
   4.500   0.6227   0.02156   0.01209  -0.0273   0.5994   1.0000
   4.750   0.6403   0.02133   0.01155  -0.0236   0.4906   1.0000
   5.000   0.6437   0.02259   0.01143  -0.0184   0.2948   1.0000
   5.500   0.6512   0.02580   0.01350  -0.0116   0.1740   1.0000
   5.750   0.6623   0.02703   0.01454  -0.0092   0.1524   1.0000
   6.000   0.6757   0.02819   0.01559  -0.0072   0.1371   1.0000
   6.250   0.6918   0.02932   0.01668  -0.0054   0.1250   1.0000
   6.500   0.7111   0.03049   0.01778  -0.0042   0.1155   1.0000
   6.750   0.7348   0.03161   0.01893  -0.0035   0.1064   1.0000
   7.000   0.7649   0.03290   0.02026  -0.0036   0.0993   1.0000
   7.250   0.7939   0.03419   0.02163  -0.0036   0.0930   1.0000
   7.500   0.8236   0.03575   0.02317  -0.0039   0.0878   1.0000
   7.750   0.8525   0.03746   0.02515  -0.0039   0.0839   1.0000
   8.000   0.8776   0.03921   0.02706  -0.0036   0.0805   1.0000
   8.250   0.9005   0.04098   0.02886  -0.0032   0.0775   1.0000
   8.500   0.9198   0.04307   0.03120  -0.0023   0.0750   1.0000
   8.750   0.9359   0.04535   0.03390  -0.0009   0.0730   1.0000
   9.000   0.9497   0.04787   0.03678   0.0007   0.0716   1.0000
   9.250   0.9603   0.05047   0.03972   0.0024   0.0705   1.0000
   9.500   0.9680   0.05306   0.04261   0.0043   0.0693   1.0000
   9.750   0.9742   0.05555   0.04534   0.0061   0.0680   1.0000
  10.000   0.9812   0.05796   0.04791   0.0077   0.0667   1.0000
  10.250   0.9875   0.06051   0.05057   0.0092   0.0654   1.0000
  10.500   0.9846   0.06359   0.05385   0.0113   0.0648   1.0000
  10.750   0.9712   0.06675   0.05733   0.0143   0.0645   1.0000
  11.000   0.9542   0.07003   0.06085   0.0171   0.0644   1.0000
  11.250   0.9363   0.07363   0.06465   0.0189   0.0644   1.0000
  11.500   0.9158   0.07772   0.06894   0.0198   0.0645   1.0000
  11.750   0.8943   0.08237   0.07375   0.0195   0.0646   1.0000
  12.000   0.8717   0.08772   0.07924   0.0181   0.0648   1.0000
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