Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

BOEING-VERTOL VR-5 AIRFOIL (vr5-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: BOEING-VERTOL VR-5 AIRFOIL (vr5-il)
Reynolds number: 1,000,000
Max Cl/Cd: 117.32 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-vr5-il-1000000-n5.txt
Download as CSV file: xf-vr5-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: BOEING-VERTOL VR-5 AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.8958   0.02704   0.02338  -0.0408   0.7985   0.0071
 -10.750  -0.8777   0.02472   0.02076  -0.0407   0.7901   0.0072
 -10.500  -0.8568   0.02307   0.01886  -0.0405   0.7804   0.0073
 -10.250  -0.8341   0.02176   0.01735  -0.0404   0.7699   0.0073
 -10.000  -0.8125   0.02010   0.01543  -0.0403   0.7596   0.0075
  -9.750  -0.7890   0.01889   0.01402  -0.0402   0.7493   0.0077
  -9.500  -0.7640   0.01805   0.01303  -0.0402   0.7397   0.0079
  -9.250  -0.7383   0.01736   0.01222  -0.0401   0.7312   0.0081
  -9.000  -0.7122   0.01672   0.01146  -0.0401   0.7228   0.0084
  -8.750  -0.6860   0.01608   0.01070  -0.0401   0.7154   0.0086
  -8.500  -0.6596   0.01545   0.00993  -0.0401   0.7078   0.0087
  -8.250  -0.6330   0.01485   0.00921  -0.0402   0.7013   0.0089
  -8.000  -0.6061   0.01429   0.00853  -0.0402   0.6950   0.0091
  -7.750  -0.5791   0.01378   0.00791  -0.0402   0.6892   0.0093
  -7.500  -0.5518   0.01329   0.00733  -0.0402   0.6841   0.0095
  -7.250  -0.5244   0.01286   0.00681  -0.0403   0.6785   0.0097
  -7.000  -0.4970   0.01237   0.00622  -0.0404   0.6732   0.0100
  -6.750  -0.4694   0.01197   0.00578  -0.0404   0.6683   0.0105
  -6.500  -0.4414   0.01166   0.00542  -0.0406   0.6628   0.0110
  -6.000  -0.3853   0.01106   0.00471  -0.0408   0.6517   0.0118
  -5.750  -0.3571   0.01078   0.00436  -0.0409   0.6456   0.0123
  -5.500  -0.3289   0.01051   0.00405  -0.0411   0.6402   0.0129
  -5.250  -0.3004   0.01029   0.00382  -0.0413   0.6347   0.0138
  -5.000  -0.2719   0.01011   0.00359  -0.0414   0.6288   0.0150
  -4.750  -0.2433   0.00992   0.00337  -0.0416   0.6236   0.0161
  -4.500  -0.2146   0.00979   0.00323  -0.0418   0.6178   0.0176
  -4.250  -0.1858   0.00967   0.00308  -0.0420   0.6119   0.0190
  -4.000  -0.1571   0.00954   0.00291  -0.0423   0.6063   0.0201
  -3.750  -0.1283   0.00940   0.00277  -0.0425   0.6000   0.0214
  -3.500  -0.0995   0.00930   0.00264  -0.0427   0.5945   0.0226
  -3.250  -0.0706   0.00918   0.00249  -0.0430   0.5893   0.0236
  -3.000  -0.0417   0.00907   0.00234  -0.0432   0.5842   0.0243
  -2.750  -0.0128   0.00895   0.00219  -0.0435   0.5796   0.0252
  -2.500   0.0161   0.00879   0.00201  -0.0437   0.5750   0.0267
  -2.250   0.0450   0.00869   0.00189  -0.0440   0.5703   0.0279
  -2.000   0.0740   0.00862   0.00179  -0.0443   0.5654   0.0293
  -1.750   0.1031   0.00853   0.00169  -0.0446   0.5606   0.0304
  -1.500   0.1321   0.00846   0.00159  -0.0448   0.5557   0.0311
  -1.250   0.1611   0.00837   0.00147  -0.0451   0.5521   0.0330
  -1.000   0.1902   0.00829   0.00140  -0.0454   0.5492   0.0358
  -0.750   0.2193   0.00822   0.00134  -0.0457   0.5457   0.0388
  -0.500   0.2484   0.00817   0.00128  -0.0460   0.5410   0.0450
  -0.250   0.2773   0.00807   0.00124  -0.0463   0.5364   0.0696
   0.000   0.3062   0.00790   0.00122  -0.0467   0.5333   0.1269
   0.250   0.3344   0.00724   0.00115  -0.0473   0.5302   0.3496
   0.500   0.3620   0.00652   0.00112  -0.0478   0.5270   0.5795
   1.000   0.4194   0.00637   0.00118  -0.0483   0.5201   0.6693
   1.250   0.4481   0.00628   0.00122  -0.0486   0.5168   0.7089
   1.500   0.4764   0.00620   0.00129  -0.0487   0.5127   0.7564
   1.750   0.5051   0.00620   0.00133  -0.0489   0.5090   0.7769
   2.000   0.5340   0.00624   0.00138  -0.0492   0.5057   0.7872
   2.250   0.5630   0.00626   0.00143  -0.0494   0.5026   0.7965
   2.500   0.5920   0.00629   0.00147  -0.0497   0.4978   0.8058
   2.750   0.6207   0.00632   0.00153  -0.0500   0.4918   0.8154
   3.000   0.6494   0.00636   0.00159  -0.0502   0.4868   0.8257
   3.250   0.6780   0.00639   0.00166  -0.0504   0.4807   0.8383
   3.750   0.7341   0.00648   0.00182  -0.0507   0.4638   0.8692
   4.000   0.7616   0.00657   0.00192  -0.0507   0.4495   0.8860
   4.250   0.7884   0.00672   0.00204  -0.0506   0.4282   0.9039
   4.500   0.8144   0.00700   0.00221  -0.0505   0.3955   0.9212
   4.750   0.8400   0.00731   0.00242  -0.0503   0.3651   0.9376
   5.000   0.8650   0.00779   0.00271  -0.0502   0.3160   0.9558
   5.250   0.8944   0.00843   0.00310  -0.0512   0.2635   0.9847
   5.500   0.9219   0.00888   0.00342  -0.0517   0.2350   1.0000
   5.750   0.9488   0.00924   0.00368  -0.0519   0.2145   1.0000
   6.000   0.9738   0.00986   0.00408  -0.0521   0.1695   1.0000
   6.250   0.9974   0.01064   0.00461  -0.0521   0.1240   1.0000
   6.500   1.0232   0.01108   0.00497  -0.0522   0.1060   1.0000
   6.750   1.0474   0.01169   0.00543  -0.0522   0.0780   1.0000
   7.000   1.0721   0.01220   0.00585  -0.0522   0.0623   1.0000
   7.250   1.0971   0.01264   0.00624  -0.0522   0.0521   1.0000
   7.500   1.1218   0.01309   0.00665  -0.0522   0.0425   1.0000
   7.750   1.1462   0.01355   0.00707  -0.0521   0.0352   1.0000
   8.000   1.1705   0.01398   0.00749  -0.0520   0.0299   1.0000
   8.250   1.1943   0.01446   0.00794  -0.0519   0.0255   1.0000
   8.500   1.2177   0.01493   0.00841  -0.0517   0.0217   1.0000
   8.750   1.2406   0.01543   0.00891  -0.0515   0.0183   1.0000
   9.000   1.2626   0.01597   0.00945  -0.0512   0.0156   1.0000
   9.250   1.2844   0.01650   0.01000  -0.0508   0.0141   1.0000
   9.500   1.3052   0.01708   0.01059  -0.0504   0.0130   1.0000
   9.750   1.3251   0.01769   0.01123  -0.0499   0.0123   1.0000
  10.000   1.3440   0.01831   0.01189  -0.0492   0.0118   1.0000
  10.250   1.3603   0.01903   0.01265  -0.0484   0.0114   1.0000
  10.500   1.3757   0.01983   0.01350  -0.0475   0.0111   1.0000
  10.750   1.3903   0.02073   0.01445  -0.0467   0.0109   1.0000
  11.000   1.4041   0.02173   0.01549  -0.0459   0.0106   1.0000
  11.250   1.4169   0.02283   0.01665  -0.0451   0.0103   1.0000
  11.500   1.4284   0.02406   0.01793  -0.0443   0.0100   1.0000
  11.750   1.4381   0.02547   0.01940  -0.0434   0.0096   1.0000
  12.000   1.4490   0.02682   0.02081  -0.0427   0.0094   1.0000
  12.250   1.4597   0.02821   0.02227  -0.0421   0.0093   1.0000
  12.500   1.4695   0.02970   0.02383  -0.0415   0.0092   1.0000
  12.750   1.4785   0.03130   0.02550  -0.0410   0.0091   1.0000
  13.000   1.4868   0.03298   0.02726  -0.0404   0.0089   1.0000
  13.250   1.4941   0.03478   0.02913  -0.0399   0.0088   1.0000
  13.500   1.5010   0.03664   0.03105  -0.0395   0.0086   1.0000
  13.750   1.5069   0.03861   0.03309  -0.0390   0.0084   1.0000
  14.000   1.5118   0.04070   0.03526  -0.0386   0.0083   1.0000
  14.250   1.5157   0.04290   0.03754  -0.0382   0.0081   1.0000
  14.500   1.5185   0.04524   0.03995  -0.0378   0.0080   1.0000
  14.750   1.5208   0.04773   0.04251  -0.0376   0.0079   1.0000
  15.000   1.5222   0.05038   0.04525  -0.0375   0.0077   1.0000
  15.250   1.5222   0.05324   0.04819  -0.0374   0.0076   1.0000
  15.500   1.5206   0.05637   0.05140  -0.0375   0.0074   1.0000
  15.750   1.5165   0.05988   0.05501  -0.0377   0.0073   1.0000
  16.000   1.5113   0.06357   0.05879  -0.0380   0.0071   1.0000
  16.250   1.5129   0.06647   0.06178  -0.0383   0.0071   1.0000
  16.500   1.5135   0.06956   0.06496  -0.0387   0.0070   1.0000
  16.750   1.5134   0.07279   0.06828  -0.0392   0.0069   1.0000
  17.000   1.5121   0.07619   0.07177  -0.0398   0.0068   1.0000
  17.250   1.5098   0.07980   0.07547  -0.0404   0.0067   1.0000
  17.500   1.5063   0.08363   0.07940  -0.0413   0.0066   1.0000
  17.750   1.5020   0.08766   0.08352  -0.0422   0.0065   1.0000
  18.000   1.4966   0.09186   0.08783  -0.0433   0.0065   1.0000
  18.250   1.4905   0.09626   0.09233  -0.0445   0.0064   1.0000
  18.500   1.4840   0.10080   0.09698  -0.0459   0.0063   1.0000
  18.750   1.4772   0.10547   0.10174  -0.0474   0.0062   1.0000
  19.000   1.4690   0.11042   0.10680  -0.0492   0.0061   1.0000
  19.250   1.4607   0.11541   0.11189  -0.0510   0.0060   1.0000
<< Back to BOEING-VERTOL VR-5 AIRFOIL (vr5-il)

Polar data table (+)

Polar graphs


<< Back to BOEING-VERTOL VR-5 AIRFOIL (vr5-il)