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BOEING-VERTOL VR-7 AIRFOIL (vr7-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: BOEING-VERTOL VR-7 AIRFOIL (vr7-il)
Reynolds number: 1,000,000
Max Cl/Cd: 125.01 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-vr7-il-1000000.txt
Download as CSV file: xf-vr7-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4182   0.08187   0.08032  -0.0341   1.0000   0.0140
  -9.250  -0.4216   0.07721   0.07568  -0.0369   1.0000   0.0144
  -9.000  -0.4307   0.07140   0.06990  -0.0411   1.0000   0.0145
  -8.750  -0.4439   0.06198   0.06045  -0.0537   0.9728   0.0144
  -8.250  -0.4314   0.03054   0.02783  -0.0615   0.7809   0.0159
  -8.000  -0.4560   0.02289   0.01980  -0.0592   0.7653   0.0164
  -7.750  -0.4457   0.02073   0.01748  -0.0581   0.7513   0.0165
  -7.500  -0.4290   0.01977   0.01644  -0.0575   0.7388   0.0168
  -7.250  -0.4389   0.02580   0.02165  -0.0581   0.7494   0.0150
  -6.750  -0.4142   0.01806   0.01287  -0.0535   0.7281   0.0145
  -6.500  -0.3920   0.01671   0.01126  -0.0524   0.7190   0.0149
  -6.250  -0.3676   0.01598   0.01035  -0.0518   0.7099   0.0155
  -6.000  -0.3425   0.01542   0.00962  -0.0511   0.7020   0.0158
  -5.750  -0.3188   0.01417   0.00817  -0.0504   0.6945   0.0161
  -5.500  -0.2953   0.01299   0.00690  -0.0496   0.6881   0.0166
  -5.250  -0.2703   0.01239   0.00624  -0.0491   0.6814   0.0169
  -4.750  -0.2193   0.01151   0.00526  -0.0481   0.6694   0.0178
  -4.500  -0.1936   0.01113   0.00482  -0.0476   0.6635   0.0183
  -4.250  -0.1678   0.01080   0.00444  -0.0471   0.6582   0.0190
  -4.000  -0.1411   0.01055   0.00416  -0.0468   0.6532   0.0196
  -3.750  -0.1149   0.01028   0.00382  -0.0464   0.6483   0.0200
  -3.500  -0.0911   0.00969   0.00316  -0.0456   0.6435   0.0210
  -3.250  -0.0645   0.00941   0.00288  -0.0453   0.6387   0.0218
  -3.000  -0.0377   0.00921   0.00265  -0.0450   0.6336   0.0229
  -2.750  -0.0111   0.00906   0.00243  -0.0446   0.6284   0.0240
  -2.500   0.0160   0.00883   0.00219  -0.0444   0.6238   0.0256
  -2.250   0.0430   0.00865   0.00200  -0.0441   0.6185   0.0284
  -2.000   0.0700   0.00854   0.00185  -0.0439   0.6132   0.0313
  -1.750   0.0972   0.00833   0.00167  -0.0436   0.6081   0.0409
  -1.500   0.1232   0.00801   0.00152  -0.0433   0.6026   0.0918
  -1.250   0.1454   0.00730   0.00137  -0.0425   0.5972   0.2784
  -1.000   0.1664   0.00647   0.00128  -0.0415   0.5920   0.5057
  -0.750   0.1923   0.00629   0.00126  -0.0410   0.5861   0.5697
  -0.500   0.2183   0.00617   0.00124  -0.0406   0.5805   0.6167
  -0.250   0.2443   0.00601   0.00123  -0.0401   0.5744   0.6657
   0.000   0.2684   0.00582   0.00124  -0.0392   0.5683   0.7349
   0.250   0.2923   0.00563   0.00126  -0.0382   0.5624   0.8007
   0.500   0.3166   0.00550   0.00129  -0.0372   0.5557   0.8607
   0.750   0.3439   0.00544   0.00135  -0.0368   0.5484   0.9150
   1.000   0.3775   0.00547   0.00139  -0.0378   0.5402   0.9430
   1.250   0.4146   0.00555   0.00144  -0.0398   0.5329   0.9589
   1.500   0.4520   0.00564   0.00149  -0.0418   0.5252   0.9715
   1.750   0.4921   0.00574   0.00154  -0.0444   0.5176   0.9772
   2.000   0.5248   0.00583   0.00160  -0.0454   0.5092   0.9834
   2.250   0.5628   0.00591   0.00164  -0.0477   0.5008   0.9859
   2.500   0.5994   0.00602   0.00168  -0.0496   0.4904   0.9892
   2.750   0.6348   0.00611   0.00174  -0.0513   0.4798   0.9927
   3.000   0.6710   0.00620   0.00179  -0.0532   0.4702   0.9954
   3.250   0.7078   0.00630   0.00184  -0.0553   0.4607   0.9979
   3.500   0.7443   0.00639   0.00190  -0.0573   0.4485   0.9999
   3.750   0.7685   0.00648   0.00197  -0.0566   0.4379   1.0000
   4.000   0.7919   0.00660   0.00204  -0.0558   0.4280   1.0000
   4.500   0.8390   0.00684   0.00223  -0.0542   0.4064   1.0000
   4.750   0.8625   0.00699   0.00234  -0.0533   0.3960   1.0000
   5.000   0.8856   0.00716   0.00247  -0.0525   0.3846   1.0000
   5.250   0.9092   0.00731   0.00261  -0.0517   0.3747   1.0000
   5.500   0.9329   0.00747   0.00275  -0.0509   0.3645   1.0000
   5.750   0.9563   0.00765   0.00291  -0.0501   0.3546   1.0000
   6.000   0.9797   0.00784   0.00307  -0.0494   0.3420   1.0000
   6.250   1.0024   0.00808   0.00325  -0.0485   0.3206   1.0000
   6.500   1.0237   0.00842   0.00347  -0.0474   0.2960   1.0000
   6.750   1.0443   0.00881   0.00374  -0.0462   0.2686   1.0000
   7.000   1.0641   0.00927   0.00406  -0.0449   0.2378   1.0000
   7.250   1.0825   0.00982   0.00444  -0.0434   0.2031   1.0000
   7.500   1.1014   0.01032   0.00482  -0.0420   0.1800   1.0000
   7.750   1.1215   0.01074   0.00517  -0.0407   0.1617   1.0000
   8.000   1.1397   0.01128   0.00559  -0.0393   0.1372   1.0000
   8.250   1.1572   0.01185   0.00604  -0.0377   0.1151   1.0000
   8.500   1.1738   0.01248   0.00653  -0.0360   0.0913   1.0000
   8.750   1.1911   0.01303   0.00700  -0.0344   0.0766   1.0000
   9.000   1.2095   0.01351   0.00745  -0.0330   0.0679   1.0000
   9.250   1.2280   0.01395   0.00789  -0.0317   0.0611   1.0000
   9.500   1.2452   0.01446   0.00837  -0.0301   0.0543   1.0000
   9.750   1.2624   0.01493   0.00884  -0.0286   0.0481   1.0000
  10.000   1.2780   0.01546   0.00935  -0.0268   0.0408   1.0000
  10.250   1.2897   0.01609   0.00994  -0.0245   0.0336   1.0000
  10.500   1.2981   0.01672   0.01056  -0.0215   0.0291   1.0000
  10.750   1.3081   0.01733   0.01118  -0.0189   0.0266   1.0000
  11.000   1.3147   0.01817   0.01204  -0.0160   0.0238   1.0000
  11.250   1.3264   0.01882   0.01275  -0.0141   0.0229   1.0000
  11.500   1.3368   0.01960   0.01358  -0.0122   0.0216   1.0000
  11.750   1.3454   0.02056   0.01458  -0.0104   0.0206   1.0000
  12.000   1.3501   0.02188   0.01595  -0.0084   0.0194   1.0000
  12.250   1.3593   0.02301   0.01714  -0.0071   0.0187   1.0000
  12.500   1.3691   0.02418   0.01838  -0.0061   0.0181   1.0000
  12.750   1.3779   0.02551   0.01978  -0.0052   0.0175   1.0000
  13.000   1.3854   0.02704   0.02137  -0.0045   0.0168   1.0000
  13.250   1.3914   0.02877   0.02316  -0.0038   0.0162   1.0000
  13.500   1.3928   0.03100   0.02546  -0.0032   0.0156   1.0000
  13.750   1.3930   0.03341   0.02796  -0.0027   0.0149   1.0000
  14.000   1.4004   0.03516   0.02978  -0.0024   0.0146   1.0000
  14.250   1.4053   0.03719   0.03189  -0.0022   0.0143   1.0000
  14.500   1.4086   0.03940   0.03418  -0.0020   0.0140   1.0000
  14.750   1.4108   0.04173   0.03659  -0.0018   0.0137   1.0000
  15.000   1.4127   0.04413   0.03906  -0.0017   0.0132   1.0000
  15.250   1.4122   0.04685   0.04185  -0.0017   0.0129   1.0000
  15.500   1.4098   0.04983   0.04491  -0.0019   0.0126   1.0000
  15.750   1.4046   0.05329   0.04845  -0.0023   0.0123   1.0000
  16.000   1.3944   0.05742   0.05268  -0.0028   0.0120   1.0000
  16.250   1.3838   0.06173   0.05710  -0.0035   0.0118   1.0000
  16.500   1.3819   0.06508   0.06053  -0.0042   0.0116   1.0000
  16.750   1.3823   0.06815   0.06369  -0.0049   0.0114   1.0000
  17.000   1.3787   0.07181   0.06744  -0.0057   0.0112   1.0000
  17.250   1.3772   0.07526   0.07098  -0.0066   0.0109   1.0000
  17.500   1.3728   0.07914   0.07495  -0.0077   0.0108   1.0000
  17.750   1.3658   0.08343   0.07933  -0.0089   0.0106   1.0000
  18.000   1.3637   0.08712   0.08309  -0.0101   0.0103   1.0000
  18.250   1.3563   0.09163   0.08769  -0.0116   0.0102   1.0000
  18.500   1.3494   0.09614   0.09229  -0.0132   0.0100   1.0000
  18.750   1.3418   0.10080   0.09703  -0.0149   0.0098   1.0000
  19.000   1.3331   0.10574   0.10205  -0.0169   0.0096   1.0000
  19.250   1.3226   0.11107   0.10746  -0.0190   0.0095   1.0000
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