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BOEING-VERTOL VR-7 AIRFOIL WITH TAB (vr7b-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: BOEING-VERTOL VR-7 AIRFOIL WITH TAB (vr7b-il)
Reynolds number: 200,000
Max Cl/Cd: 72.92 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-vr7b-il-200000.txt
Download as CSV file: xf-vr7b-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: BOEING-VERTOL VR-7 AIRFOIL WITH TAB             
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4953   0.08791   0.08505  -0.0205   1.0000   0.0478
  -8.500  -0.5054   0.08040   0.07737  -0.0333   1.0000   0.0480
  -8.250  -0.5054   0.07555   0.07221  -0.0395   0.9710   0.0482
  -8.000  -0.4945   0.07000   0.06694  -0.0369   0.9577   0.0496
  -7.750  -0.4918   0.06810   0.06504  -0.0346   0.9399   0.0504
  -7.500  -0.4899   0.06569   0.06257  -0.0335   0.9240   0.0514
  -7.250  -0.4858   0.06257   0.05935  -0.0335   0.9102   0.0530
  -7.000  -0.4789   0.05880   0.05539  -0.0347   0.8974   0.0559
  -6.750  -0.4763   0.05319   0.04909  -0.0372   0.8856   0.0606
  -6.500  -0.4625   0.05034   0.04636  -0.0361   0.8764   0.0623
  -6.250  -0.4480   0.04798   0.04394  -0.0352   0.8669   0.0650
  -5.750  -0.4166   0.04144   0.03668  -0.0348   0.8502   0.0752
  -5.500  -0.3953   0.03914   0.03433  -0.0347   0.8410   0.0788
  -5.250  -0.3768   0.03660   0.03133  -0.0340   0.8343   0.0887
  -5.000  -0.3531   0.03453   0.02923  -0.0340   0.8251   0.0940
  -4.750  -0.3328   0.03249   0.02696  -0.0333   0.8185   0.1058
  -4.500  -0.3081   0.03081   0.02516  -0.0337   0.8096   0.1211
  -4.250  -0.2652   0.02418   0.01662  -0.0300   0.8045   0.0488
  -4.000  -0.2372   0.02235   0.01463  -0.0297   0.7967   0.0474
  -3.750  -0.2107   0.02071   0.01276  -0.0289   0.7892   0.0470
  -3.500  -0.1826   0.01955   0.01142  -0.0285   0.7806   0.0474
  -3.250  -0.1561   0.01835   0.01006  -0.0278   0.7729   0.0492
  -3.000  -0.1284   0.01717   0.00890  -0.0277   0.7645   0.0510
  -2.750  -0.1014   0.01636   0.00805  -0.0272   0.7575   0.0528
  -2.500  -0.0729   0.01569   0.00736  -0.0272   0.7500   0.0557
  -2.250  -0.0448   0.01517   0.00677  -0.0271   0.7430   0.0599
  -2.000  -0.0164   0.01445   0.00606  -0.0273   0.7361   0.0683
  -1.750   0.0127   0.01383   0.00539  -0.0275   0.7286   0.0850
  -1.500   0.0338   0.01106   0.00508  -0.0271   0.7228   0.6701
  -1.250   0.0532   0.01076   0.00522  -0.0242   0.7153   0.8056
  -1.000   0.0689   0.01072   0.00525  -0.0203   0.7096   0.8749
  -0.750   0.0867   0.01072   0.00527  -0.0170   0.7021   0.9329
  -0.500   0.1296   0.01064   0.00506  -0.0187   0.6952   0.9824
  -0.250   0.1873   0.01073   0.00499  -0.0247   0.6871   1.0000
   0.000   0.2101   0.01070   0.00482  -0.0242   0.6801   1.0000
   0.250   0.2343   0.01075   0.00475  -0.0240   0.6728   1.0000
   0.500   0.2599   0.01081   0.00469  -0.0238   0.6655   1.0000
   0.750   0.2869   0.01091   0.00468  -0.0239   0.6587   1.0000
   1.000   0.3155   0.01101   0.00469  -0.0243   0.6508   1.0000
   1.250   0.3436   0.01114   0.00469  -0.0244   0.6445   1.0000
   1.500   0.3734   0.01124   0.00476  -0.0250   0.6361   1.0000
   1.750   0.4016   0.01137   0.00476  -0.0251   0.6300   1.0000
   2.000   0.4319   0.01149   0.00489  -0.0258   0.6213   1.0000
   2.250   0.4606   0.01161   0.00489  -0.0260   0.6149   1.0000
   2.500   0.4907   0.01174   0.00504  -0.0267   0.6064   1.0000
   2.750   0.5196   0.01185   0.00507  -0.0269   0.5996   1.0000
   3.000   0.5495   0.01199   0.00522  -0.0275   0.5911   1.0000
   3.250   0.5784   0.01210   0.00526  -0.0277   0.5841   1.0000
   3.500   0.6083   0.01222   0.00540  -0.0283   0.5748   1.0000
   3.750   0.6369   0.01230   0.00539  -0.0283   0.5674   1.0000
   4.000   0.6667   0.01241   0.00557  -0.0289   0.5573   1.0000
   4.250   0.6958   0.01253   0.00566  -0.0292   0.5494   1.0000
   4.500   0.7251   0.01265   0.00579  -0.0296   0.5403   1.0000
   4.750   0.7543   0.01280   0.00594  -0.0300   0.5312   1.0000
   5.000   0.7830   0.01290   0.00601  -0.0302   0.5222   1.0000
   5.250   0.8123   0.01306   0.00623  -0.0307   0.5117   1.0000
   5.500   0.8411   0.01324   0.00641  -0.0310   0.5031   1.0000
   5.750   0.8699   0.01338   0.00658  -0.0314   0.4929   1.0000
   6.000   0.8987   0.01352   0.00677  -0.0317   0.4808   1.0000
   6.250   0.9272   0.01366   0.00693  -0.0321   0.4679   1.0000
   6.500   0.9555   0.01382   0.00712  -0.0323   0.4547   1.0000
   6.750   0.9837   0.01402   0.00734  -0.0326   0.4423   1.0000
   7.000   1.0118   0.01423   0.00758  -0.0329   0.4293   1.0000
   7.250   1.0396   0.01445   0.00786  -0.0332   0.4148   1.0000
   7.500   1.0672   0.01471   0.00817  -0.0335   0.3990   1.0000
   7.750   1.0944   0.01501   0.00853  -0.0338   0.3810   1.0000
   8.000   1.1208   0.01537   0.00891  -0.0341   0.3586   1.0000
   8.250   1.1465   0.01579   0.00935  -0.0344   0.3308   1.0000
   8.500   1.1709   0.01637   0.00986  -0.0346   0.2970   1.0000
   8.750   1.1932   0.01720   0.01056  -0.0347   0.2563   1.0000
   9.000   1.2124   0.01837   0.01153  -0.0346   0.2111   1.0000
   9.250   1.2280   0.01984   0.01277  -0.0342   0.1719   1.0000
   9.500   1.2415   0.02141   0.01415  -0.0337   0.1373   1.0000
   9.750   1.2532   0.02300   0.01562  -0.0329   0.1132   1.0000
  10.000   1.2615   0.02475   0.01727  -0.0319   0.0969   1.0000
  10.250   1.2652   0.02652   0.01901  -0.0304   0.0856   1.0000
  10.500   1.2692   0.02839   0.02092  -0.0290   0.0762   1.0000
  10.750   1.2701   0.03066   0.02320  -0.0278   0.0693   1.0000
  11.000   1.2733   0.03283   0.02541  -0.0269   0.0635   1.0000
  11.250   1.2737   0.03534   0.02793  -0.0258   0.0592   1.0000
  11.500   1.2800   0.03736   0.03005  -0.0252   0.0552   1.0000
  11.750   1.2833   0.03967   0.03236  -0.0246   0.0520   1.0000
  12.000   1.2873   0.04194   0.03466  -0.0234   0.0492   1.0000
  12.250   1.2948   0.04393   0.03681  -0.0229   0.0469   1.0000
  12.500   1.3016   0.04598   0.03893  -0.0223   0.0448   1.0000
  12.750   1.3078   0.04808   0.04104  -0.0217   0.0429   1.0000
  13.000   1.3162   0.05007   0.04301  -0.0201   0.0408   1.0000
  13.250   1.3220   0.05232   0.04546  -0.0198   0.0395   1.0000
  13.500   1.3279   0.05460   0.04790  -0.0193   0.0381   1.0000
  13.750   1.3336   0.05695   0.05037  -0.0189   0.0369   1.0000
  14.000   1.3383   0.05937   0.05290  -0.0186   0.0357   1.0000
  14.250   1.3439   0.06169   0.05526  -0.0182   0.0345   1.0000
  14.500   1.3508   0.06444   0.05807  -0.0168   0.0331   1.0000
  14.750   1.3470   0.06788   0.06176  -0.0173   0.0326   1.0000
  15.000   1.3425   0.07154   0.06566  -0.0177   0.0320   1.0000
  15.250   1.3369   0.07552   0.06986  -0.0183   0.0314   1.0000
  15.500   1.3296   0.07985   0.07442  -0.0191   0.0310   1.0000
  15.750   1.3202   0.08458   0.07937  -0.0203   0.0306   1.0000
  16.000   1.3091   0.08974   0.08474  -0.0220   0.0302   1.0000
  16.250   1.2960   0.09537   0.09059  -0.0241   0.0300   1.0000
  16.500   1.2807   0.10156   0.09700  -0.0268   0.0298   1.0000
  16.750   1.2625   0.10857   0.10423  -0.0302   0.0297   1.0000
  17.000   1.2399   0.11684   0.11274  -0.0347   0.0297   1.0000
  17.250   1.2106   0.12703   0.12319  -0.0408   0.0300   1.0000
  17.500   1.1735   0.13985   0.13627  -0.0490   0.0307   1.0000
  17.750   1.1303   0.15567   0.15232  -0.0594   0.0317   1.0000
  18.000   1.0820   0.17513   0.17188  -0.0717   0.0329   1.0000
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