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BOEING-VERTOL VR-8 AIRFOIL (vr8-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: BOEING-VERTOL VR-8 AIRFOIL (vr8-il)
Reynolds number: 1,000,000
Max Cl/Cd: 123.19 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-vr8-il-1000000.txt
Download as CSV file: xf-vr8-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: BOEING-VERTOL VR-8 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.4682   0.11061   0.10907   0.0031   1.0000   0.0084
 -10.500  -0.4673   0.10606   0.10453   0.0013   1.0000   0.0089
  -6.250  -0.5444   0.02960   0.02659  -0.0230   1.0000   0.0093
  -6.000  -0.5333   0.02554   0.02217  -0.0205   1.0000   0.0093
  -5.750  -0.5214   0.02166   0.01790  -0.0180   1.0000   0.0089
  -5.500  -0.4999   0.01766   0.01336  -0.0167   0.9988   0.0092
  -5.250  -0.4517   0.01507   0.01029  -0.0213   0.9890   0.0104
  -5.000  -0.4122   0.01422   0.00946  -0.0243   0.9742   0.0111
  -4.750  -0.3753   0.01330   0.00842  -0.0263   0.9471   0.0119
  -4.500  -0.3469   0.01261   0.00746  -0.0261   0.8934   0.0129
  -4.250  -0.3234   0.01320   0.00770  -0.0248   0.8226   0.0141
  -4.000  -0.3021   0.01157   0.00590  -0.0239   0.7754   0.0167
  -3.750  -0.2769   0.01164   0.00573  -0.0234   0.7308   0.0207
  -3.500  -0.2525   0.01075   0.00464  -0.0226   0.6946   0.0207
  -3.250  -0.2286   0.00992   0.00363  -0.0218   0.6582   0.0214
  -3.000  -0.2043   0.00956   0.00302  -0.0212   0.6027   0.0228
  -2.750  -0.1805   0.00963   0.00260  -0.0205   0.4782   0.0234
  -2.500  -0.1600   0.01072   0.00245  -0.0198   0.0459   0.0231
  -2.250  -0.1330   0.01050   0.00214  -0.0196   0.0396   0.0233
  -2.000  -0.1058   0.01033   0.00190  -0.0194   0.0362   0.0229
  -1.750  -0.0784   0.01019   0.00169  -0.0193   0.0359   0.0225
  -1.500  -0.0510   0.01007   0.00151  -0.0192   0.0355   0.0223
  -1.250  -0.0234   0.00998   0.00136  -0.0192   0.0352   0.0225
  -1.000   0.0042   0.00992   0.00123  -0.0191   0.0351   0.0233
  -0.750   0.0318   0.00988   0.00115  -0.0190   0.0350   0.0242
  -0.500   0.0593   0.00983   0.00109  -0.0190   0.0350   0.0265
  -0.250   0.0870   0.00981   0.00107  -0.0190   0.0339   0.0269
   0.000   0.1146   0.00980   0.00104  -0.0190   0.0325   0.0341
   0.250   0.1422   0.00981   0.00098  -0.0189   0.0284   0.0366
   0.500   0.1693   0.00996   0.00096  -0.0188   0.0276   0.0409
   0.750   0.1973   0.00988   0.00102  -0.0189   0.0251   0.0406
   1.000   0.2249   0.00990   0.00105  -0.0189   0.0245   0.0416
   1.250   0.2525   0.00993   0.00110  -0.0189   0.0243   0.0449
   1.500   0.2772   0.00868   0.00110  -0.0192   0.0241   0.5062
   1.750   0.3036   0.00832   0.00120  -0.0192   0.0238   0.6484
   2.000   0.3267   0.00777   0.00133  -0.0182   0.0234   0.8439
   2.250   0.3377   0.00768   0.00153  -0.0138   0.0233   0.9407
   2.500   0.3581   0.00785   0.00172  -0.0119   0.0230   0.9783
   2.750   0.3969   0.00796   0.00185  -0.0143   0.0229   0.9890
   3.000   0.4724   0.00809   0.00197  -0.0249   0.0232   0.9994
   3.250   0.5000   0.00825   0.00214  -0.0249   0.0233   1.0000
   3.500   0.5239   0.00843   0.00237  -0.0241   0.0237   1.0000
   3.750   0.5479   0.00864   0.00260  -0.0234   0.0241   1.0000
   4.000   0.5719   0.00885   0.00286  -0.0226   0.0245   1.0000
   4.250   0.5957   0.00910   0.00315  -0.0218   0.0251   1.0000
   4.500   0.6192   0.00938   0.00349  -0.0209   0.0256   1.0000
   4.750   0.6424   0.00971   0.00387  -0.0200   0.0256   1.0000
   5.000   0.6651   0.01010   0.00431  -0.0190   0.0252   1.0000
   5.250   0.6876   0.01052   0.00478  -0.0180   0.0255   1.0000
   5.500   0.7096   0.01101   0.00532  -0.0169   0.0255   1.0000
   5.750   0.7308   0.01159   0.00597  -0.0157   0.0251   1.0000
   6.000   0.7476   0.01282   0.00728  -0.0138   0.0236   1.0000
   6.250   0.7687   0.01354   0.00806  -0.0126   0.0213   1.0000
   6.500   0.7828   0.01734   0.01176  -0.0108   0.0183   1.0000
   6.750   0.8081   0.01596   0.01042  -0.0105   0.0153   1.0000
   7.000   0.8061   0.00693   0.00158  -0.0081   0.0131   1.0000
   7.250   0.8303   0.00674   0.00158  -0.0076   0.0118   1.0000
   7.500   0.8530   0.00706   0.00196  -0.0072   0.0107   1.0000
   7.750   0.8757   0.00748   0.00235  -0.0069   0.0101   1.0000
   8.000   0.8975   0.00901   0.00380  -0.0066   0.0096   1.0000
   8.250   0.9182   0.00911   0.00433  -0.0054   0.0083   1.0000
   8.500   0.9397   0.00985   0.00523  -0.0048   0.0076   1.0000
   8.750   0.9606   0.01047   0.00595  -0.0042   0.0072   1.0000
   9.000   0.9827   0.01075   0.00628  -0.0039   0.0069   1.0000
   9.250   0.9986   0.01229   0.00802  -0.0029   0.0065   1.0000
   9.500   1.0141   0.01406   0.01001  -0.0017   0.0062   1.0000
   9.750   1.0258   0.01656   0.01281  -0.0002   0.0056   1.0000
  10.000   1.0371   0.01865   0.01512   0.0010   0.0052   1.0000
  10.250   1.0441   0.02081   0.01750   0.0027   0.0050   1.0000
  10.500   1.0502   0.02283   0.01970   0.0042   0.0048   1.0000
  10.750   1.0410   0.02589   0.02301   0.0072   0.0047   1.0000
  11.000   1.0098   0.03017   0.02760   0.0108   0.0048   1.0000
  11.250   0.9875   0.03402   0.03165   0.0116   0.0047   1.0000
  11.500   0.9443   0.04164   0.03955   0.0102   0.0048   1.0000
  11.750   0.9066   0.05035   0.04847   0.0068   0.0049   1.0000
  12.000   0.8762   0.05962   0.05790   0.0021   0.0050   1.0000
  12.250   0.8367   0.07163   0.07005  -0.0041   0.0052   1.0000
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