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BOEING-VERTOL VR-7 AIRFOIL (vr7-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: BOEING-VERTOL VR-7 AIRFOIL (vr7-il)
Reynolds number: 500,000
Max Cl/Cd: 103.05 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-vr7-il-500000.txt
Download as CSV file: xf-vr7-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3993   0.08619   0.08398  -0.0337   1.0000   0.0220
  -9.250  -0.4008   0.08207   0.07989  -0.0359   1.0000   0.0227
  -9.000  -0.4056   0.07732   0.07518  -0.0387   1.0000   0.0230
  -8.750  -0.4147   0.07170   0.06961  -0.0432   1.0000   0.0235
  -8.000  -0.4577   0.04836   0.04549  -0.0587   0.9645   0.0250
  -7.750  -0.4276   0.04358   0.04066  -0.0639   0.9387   0.0255
  -7.500  -0.4013   0.04108   0.03798  -0.0665   0.8967   0.0261
  -7.250  -0.3891   0.03893   0.03555  -0.0655   0.8551   0.0267
  -7.000  -0.3774   0.03680   0.03312  -0.0640   0.8260   0.0279
  -6.750  -0.3629   0.03622   0.03182  -0.0611   0.8038   0.0306
  -6.500  -0.3576   0.03056   0.02586  -0.0597   0.7885   0.0317
  -6.250  -0.3382   0.02892   0.02414  -0.0590   0.7751   0.0324
  -6.000  -0.3184   0.02744   0.02248  -0.0582   0.7638   0.0335
  -5.750  -0.2965   0.02656   0.02132  -0.0570   0.7539   0.0365
  -5.500  -0.2819   0.01962   0.01342  -0.0535   0.7461   0.0261
  -5.250  -0.2575   0.02044   0.01429  -0.0536   0.7373   0.0324
  -5.000  -0.2315   0.01733   0.01058  -0.0516   0.7293   0.0247
  -4.750  -0.2066   0.01603   0.00907  -0.0509   0.7217   0.0249
  -4.500  -0.1821   0.01455   0.00756  -0.0504   0.7138   0.0259
  -4.250  -0.1567   0.01392   0.00685  -0.0499   0.7071   0.0267
  -4.000  -0.1311   0.01326   0.00614  -0.0493   0.7004   0.0273
  -3.750  -0.1058   0.01272   0.00554  -0.0487   0.6941   0.0281
  -3.500  -0.0805   0.01226   0.00501  -0.0481   0.6881   0.0290
  -3.250  -0.0549   0.01185   0.00456  -0.0475   0.6819   0.0300
  -3.000  -0.0302   0.01139   0.00402  -0.0468   0.6763   0.0315
  -2.750  -0.0048   0.01100   0.00363  -0.0463   0.6707   0.0338
  -2.500   0.0213   0.01073   0.00333  -0.0459   0.6649   0.0363
  -2.000   0.0736   0.01020   0.00271  -0.0450   0.6535   0.0464
  -1.750   0.0980   0.00966   0.00239  -0.0443   0.6479   0.1090
  -1.500   0.1129   0.00815   0.00218  -0.0426   0.6429   0.4928
  -1.250   0.1362   0.00780   0.00217  -0.0416   0.6368   0.5982
  -1.000   0.1599   0.00757   0.00214  -0.0406   0.6312   0.6702
  -0.750   0.1840   0.00740   0.00214  -0.0396   0.6257   0.7278
  -0.500   0.2072   0.00717   0.00217  -0.0383   0.6196   0.8004
   0.000   0.2676   0.00704   0.00230  -0.0383   0.6079   0.9265
   0.250   0.3090   0.00711   0.00233  -0.0409   0.6012   0.9500
   0.500   0.3497   0.00722   0.00236  -0.0435   0.5950   0.9635
   0.750   0.3918   0.00729   0.00240  -0.0464   0.5877   0.9735
   1.000   0.4316   0.00739   0.00240  -0.0489   0.5813   0.9801
   1.250   0.4711   0.00741   0.00241  -0.0514   0.5736   0.9858
   1.500   0.5112   0.00748   0.00238  -0.0541   0.5664   0.9909
   1.750   0.5511   0.00749   0.00238  -0.0567   0.5571   0.9957
   2.000   0.5919   0.00753   0.00236  -0.0596   0.5491   0.9999
   2.250   0.6155   0.00756   0.00237  -0.0589   0.5412   1.0000
   2.500   0.6385   0.00762   0.00239  -0.0579   0.5339   1.0000
   2.750   0.6618   0.00768   0.00243  -0.0571   0.5254   1.0000
   3.000   0.6851   0.00776   0.00248  -0.0562   0.5177   1.0000
   3.250   0.7085   0.00785   0.00254  -0.0554   0.5085   1.0000
   3.500   0.7321   0.00793   0.00261  -0.0545   0.4987   1.0000
   3.750   0.7554   0.00806   0.00269  -0.0537   0.4898   1.0000
   4.000   0.7791   0.00816   0.00278  -0.0529   0.4793   1.0000
   4.250   0.8028   0.00828   0.00289  -0.0521   0.4693   1.0000
   4.500   0.8262   0.00843   0.00301  -0.0512   0.4596   1.0000
   4.750   0.8502   0.00855   0.00314  -0.0505   0.4502   1.0000
   5.000   0.8740   0.00870   0.00328  -0.0498   0.4407   1.0000
   5.250   0.8973   0.00887   0.00342  -0.0489   0.4298   1.0000
   5.500   0.9208   0.00903   0.00358  -0.0481   0.4173   1.0000
   5.750   0.9444   0.00920   0.00375  -0.0474   0.4059   1.0000
   6.000   0.9676   0.00939   0.00393  -0.0466   0.3942   1.0000
   6.250   0.9906   0.00962   0.00415  -0.0457   0.3838   1.0000
   6.500   1.0133   0.00986   0.00437  -0.0448   0.3722   1.0000
   6.750   1.0359   0.01010   0.00460  -0.0440   0.3578   1.0000
   7.000   1.0579   0.01037   0.00485  -0.0430   0.3378   1.0000
   7.250   1.0786   0.01073   0.00512  -0.0418   0.3126   1.0000
   7.500   1.0988   0.01113   0.00544  -0.0406   0.2864   1.0000
   7.750   1.1176   0.01163   0.00583  -0.0393   0.2572   1.0000
   8.000   1.1344   0.01227   0.00631  -0.0376   0.2235   1.0000
   8.250   1.1500   0.01299   0.00686  -0.0358   0.1911   1.0000
   8.500   1.1655   0.01369   0.00744  -0.0341   0.1677   1.0000
   9.000   1.1950   0.01512   0.00865  -0.0304   0.1177   1.0000
   9.250   1.2073   0.01592   0.00933  -0.0282   0.0952   1.0000
   9.500   1.2190   0.01670   0.01003  -0.0259   0.0808   1.0000
   9.750   1.2305   0.01739   0.01070  -0.0236   0.0716   1.0000
  10.000   1.2380   0.01812   0.01143  -0.0206   0.0640   1.0000
  10.250   1.2447   0.01893   0.01224  -0.0176   0.0569   1.0000
  10.500   1.2531   0.01974   0.01308  -0.0152   0.0502   1.0000
  10.750   1.2574   0.02084   0.01418  -0.0125   0.0442   1.0000
  11.000   1.2649   0.02186   0.01522  -0.0105   0.0394   1.0000
  11.250   1.2682   0.02326   0.01664  -0.0084   0.0359   1.0000
  11.500   1.2757   0.02449   0.01794  -0.0069   0.0334   1.0000
  11.750   1.2794   0.02611   0.01958  -0.0055   0.0311   1.0000
  12.000   1.2795   0.02815   0.02170  -0.0041   0.0295   1.0000
  12.250   1.2862   0.02977   0.02341  -0.0033   0.0284   1.0000
  12.500   1.2915   0.03156   0.02529  -0.0026   0.0272   1.0000
  12.750   1.2952   0.03356   0.02736  -0.0020   0.0261   1.0000
  13.000   1.2948   0.03600   0.02985  -0.0014   0.0251   1.0000
  13.250   1.2899   0.03894   0.03286  -0.0008   0.0242   1.0000
  13.500   1.2876   0.04167   0.03569  -0.0004   0.0236   1.0000
  13.750   1.2928   0.04372   0.03784  -0.0002   0.0230   1.0000
  14.000   1.2944   0.04617   0.04039  -0.0001   0.0223   1.0000
  14.250   1.2941   0.04885   0.04316   0.0000   0.0218   1.0000
  14.500   1.2951   0.05148   0.04587  -0.0001   0.0210   1.0000
  14.750   1.2945   0.05437   0.04882  -0.0003   0.0206   1.0000
  15.000   1.2915   0.05758   0.05210  -0.0006   0.0199   1.0000
  15.250   1.2868   0.06104   0.05562  -0.0009   0.0195   1.0000
  15.500   1.2808   0.06462   0.05928  -0.0011   0.0189   1.0000
  15.750   1.2832   0.06753   0.06230  -0.0018   0.0185   1.0000
  16.000   1.2829   0.07073   0.06562  -0.0024   0.0182   1.0000
  16.250   1.2824   0.07401   0.06900  -0.0032   0.0179   1.0000
  16.500   1.2816   0.07746   0.07255  -0.0042   0.0173   1.0000
  16.750   1.2802   0.08098   0.07616  -0.0051   0.0169   1.0000
  17.000   1.2787   0.08464   0.07990  -0.0063   0.0165   1.0000
  17.250   1.2760   0.08847   0.08379  -0.0076   0.0160   1.0000
  17.500   1.2741   0.09217   0.08757  -0.0088   0.0158   1.0000
  17.750   1.2699   0.09608   0.09154  -0.0099   0.0154   1.0000
  18.000   1.2643   0.10003   0.09558  -0.0106   0.0150   1.0000
  18.250   1.2608   0.10435   0.10004  -0.0125   0.0149   1.0000
  18.500   1.2559   0.10901   0.10484  -0.0146   0.0147   1.0000
  18.750   1.2502   0.11390   0.10986  -0.0169   0.0144   1.0000
  19.000   1.2445   0.11874   0.11484  -0.0192   0.0142   1.0000
  19.250   1.2381   0.12378   0.12000  -0.0216   0.0140   1.0000
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