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BOEING-VERTOL VR-1 AIRFOIL (vr1-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: BOEING-VERTOL VR-1 AIRFOIL (vr1-il)
Reynolds number: 100,000
Max Cl/Cd: 46.95 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-vr1-il-100000.txt
Download as CSV file: xf-vr1-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.5260   0.09168   0.08654  -0.0392   1.0000   0.1544
  -9.000  -0.4804   0.08898   0.08377  -0.0325   1.0000   0.1593
  -8.750  -0.4787   0.08607   0.08091  -0.0325   1.0000   0.1652
  -8.500  -0.5490   0.08166   0.07669  -0.0384   1.0000   0.1699
  -8.250  -0.5040   0.07850   0.07354  -0.0346   1.0000   0.1754
  -8.000  -0.5128   0.07565   0.07077  -0.0338   1.0000   0.1804
  -6.250  -0.6403   0.04068   0.03299  -0.0189   1.0000   0.0827
  -6.000  -0.6279   0.03707   0.02939  -0.0174   1.0000   0.0802
  -5.750  -0.6155   0.03436   0.02637  -0.0152   1.0000   0.0773
  -5.500  -0.6015   0.03162   0.02302  -0.0128   1.0000   0.0736
  -5.250  -0.5846   0.03006   0.02093  -0.0106   1.0000   0.0716
  -5.000  -0.5661   0.02856   0.01918  -0.0091   1.0000   0.0716
  -4.750  -0.5468   0.02702   0.01754  -0.0079   1.0000   0.0728
  -4.500  -0.5273   0.02588   0.01631  -0.0067   1.0000   0.0742
  -4.250  -0.5071   0.02481   0.01514  -0.0054   1.0000   0.0750
  -4.000  -0.4868   0.02383   0.01409  -0.0041   1.0000   0.0758
  -3.750  -0.4669   0.02298   0.01320  -0.0028   1.0000   0.0771
  -3.500  -0.4476   0.02225   0.01244  -0.0014   1.0000   0.0790
  -3.250  -0.4167   0.02163   0.01179  -0.0023   0.9965   0.0819
  -3.000  -0.3832   0.02095   0.01124  -0.0039   0.9913   0.0890
  -2.750  -0.3489   0.02046   0.01079  -0.0055   0.9858   0.1002
  -2.500  -0.3177   0.01974   0.01029  -0.0064   0.9801   0.1307
  -2.250  -0.3040   0.01705   0.01030  -0.0040   0.9752   0.6273
  -2.000  -0.2733   0.01720   0.01115  -0.0021   0.9710   0.8338
  -1.750  -0.1911   0.01836   0.01228  -0.0096   0.9721   0.9500
  -1.500  -0.0501   0.01940   0.01294  -0.0298   0.9820   1.0000
  -1.250  -0.0159   0.01937   0.01276  -0.0328   0.9738   1.0000
  -1.000   0.0126   0.01936   0.01264  -0.0345   0.9651   1.0000
  -0.750   0.0505   0.01948   0.01264  -0.0377   0.9584   1.0000
  -0.500   0.0721   0.01953   0.01262  -0.0378   0.9486   1.0000
  -0.250   0.1126   0.01971   0.01271  -0.0411   0.9428   1.0000
   0.000   0.1286   0.01984   0.01279  -0.0400   0.9324   1.0000
   0.250   0.1711   0.02004   0.01294  -0.0434   0.9269   1.0000
   0.500   0.1846   0.02025   0.01311  -0.0416   0.9161   1.0000
   0.750   0.2283   0.02045   0.01329  -0.0451   0.9107   1.0000
   1.000   0.2408   0.02073   0.01354  -0.0429   0.8998   1.0000
   1.250   0.2864   0.02089   0.01372  -0.0465   0.8944   1.0000
   1.500   0.2993   0.02121   0.01404  -0.0443   0.8831   1.0000
   1.750   0.3499   0.02128   0.01417  -0.0486   0.8778   1.0000
   2.000   0.3632   0.02162   0.01451  -0.0463   0.8659   1.0000
   2.250   0.4281   0.02112   0.01414  -0.0522   0.8559   1.0000
   2.500   0.4989   0.01962   0.01278  -0.0574   0.8380   1.0000
   2.750   0.5538   0.01792   0.01117  -0.0589   0.8153   1.0000
   3.000   0.5909   0.01679   0.01007  -0.0580   0.7948   1.0000
   3.250   0.6109   0.01635   0.00970  -0.0551   0.7737   1.0000
   3.500   0.6328   0.01579   0.00917  -0.0523   0.7494   1.0000
   3.750   0.6525   0.01526   0.00866  -0.0491   0.7189   1.0000
   4.000   0.6699   0.01477   0.00816  -0.0454   0.6749   1.0000
   4.250   0.6803   0.01449   0.00760  -0.0402   0.5774   1.0000
   4.500   0.6653   0.01632   0.00760  -0.0315   0.2824   1.0000
   4.750   0.6634   0.01817   0.00860  -0.0266   0.1918   1.0000
   5.000   0.6729   0.01931   0.00947  -0.0233   0.1628   1.0000
   5.250   0.6854   0.02040   0.01034  -0.0206   0.1445   1.0000
   5.500   0.7023   0.02149   0.01131  -0.0186   0.1311   1.0000
   5.750   0.7232   0.02269   0.01242  -0.0173   0.1207   1.0000
   6.000   0.7480   0.02422   0.01372  -0.0169   0.1119   1.0000
   6.250   0.7732   0.02536   0.01499  -0.0161   0.1061   1.0000
   6.500   0.7989   0.02675   0.01632  -0.0157   0.1005   1.0000
   6.750   0.8253   0.02852   0.01816  -0.0154   0.0959   1.0000
   7.000   0.8497   0.03007   0.01993  -0.0146   0.0932   1.0000
   7.250   0.8733   0.03183   0.02190  -0.0137   0.0910   1.0000
   7.500   0.8956   0.03359   0.02380  -0.0128   0.0886   1.0000
   7.750   0.9174   0.03570   0.02596  -0.0122   0.0860   1.0000
   8.000   0.9364   0.03897   0.02941  -0.0113   0.0846   1.0000
   8.250   0.9518   0.04144   0.03224  -0.0094   0.0843   1.0000
   8.500   0.9667   0.04458   0.03567  -0.0078   0.0845   1.0000
   8.750   0.9805   0.04710   0.03853  -0.0058   0.0852   1.0000
   9.000   0.9756   0.04968   0.04195  -0.0009   0.0880   1.0000
   9.250   0.9664   0.05446   0.04734   0.0030   0.0921   1.0000
   9.500   0.9635   0.05862   0.05179   0.0056   0.0946   1.0000
   9.750   0.8530   0.05618   0.05038   0.0155   0.1081   1.0000
  10.000   0.7267   0.09502   0.08959  -0.0023   0.2066   1.0000
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