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BOEING-VERTOL VR-7 AIRFOIL (vr7-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: BOEING-VERTOL VR-7 AIRFOIL (vr7-il)
Reynolds number: 200,000
Max Cl/Cd: 72.35 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-vr7-il-200000-n5.txt
Download as CSV file: xf-vr7-il-200000-n5.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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3219   0.08938   0.08610  -0.0377   1.0000   0.0310
 -10.000  -0.3239   0.08462   0.08137  -0.0393   1.0000   0.0310
  -9.500  -0.4162   0.08020   0.07672  -0.0408   1.0000   0.0202
  -9.250  -0.4182   0.07625   0.07282  -0.0427   1.0000   0.0200
  -9.000  -0.4241   0.07150   0.06813  -0.0459   1.0000   0.0198
  -8.750  -0.4377   0.06635   0.06301  -0.0500   1.0000   0.0196
  -8.500  -0.4535   0.06247   0.05911  -0.0501   1.0000   0.0194
  -8.250  -0.4573   0.05705   0.05357  -0.0530   0.9847   0.0191
  -8.000  -0.4475   0.04996   0.04614  -0.0585   0.9468   0.0189
  -7.750  -0.4328   0.04381   0.03955  -0.0621   0.9148   0.0189
  -7.500  -0.4222   0.03787   0.03295  -0.0629   0.8840   0.0197
  -7.250  -0.4111   0.03329   0.02764  -0.0619   0.8574   0.0202
  -7.000  -0.3956   0.03034   0.02414  -0.0607   0.8354   0.0203
  -6.750  -0.3782   0.02801   0.02146  -0.0596   0.8172   0.0205
  -6.500  -0.3585   0.02628   0.01942  -0.0586   0.8016   0.0209
  -6.250  -0.3373   0.02484   0.01772  -0.0577   0.7881   0.0212
  -6.000  -0.3150   0.02362   0.01625  -0.0569   0.7763   0.0218
  -5.750  -0.2919   0.02256   0.01492  -0.0561   0.7659   0.0228
  -5.500  -0.2681   0.02137   0.01344  -0.0553   0.7558   0.0237
  -5.250  -0.2436   0.02016   0.01193  -0.0545   0.7472   0.0242
  -5.000  -0.2185   0.01911   0.01064  -0.0538   0.7392   0.0247
  -4.750  -0.1932   0.01820   0.00955  -0.0532   0.7319   0.0252
  -4.500  -0.1686   0.01730   0.00860  -0.0526   0.7243   0.0258
  -4.250  -0.1438   0.01666   0.00790  -0.0520   0.7174   0.0267
  -4.000  -0.1187   0.01618   0.00737  -0.0515   0.7095   0.0282
  -3.750  -0.0937   0.01571   0.00679  -0.0508   0.7025   0.0299
  -3.500  -0.0689   0.01520   0.00621  -0.0502   0.6944   0.0309
  -3.250  -0.0451   0.01465   0.00561  -0.0494   0.6875   0.0323
  -3.000  -0.0202   0.01426   0.00519  -0.0488   0.6800   0.0341
  -2.750   0.0052   0.01395   0.00478  -0.0482   0.6740   0.0368
  -2.500   0.0306   0.01363   0.00442  -0.0478   0.6677   0.0415
  -2.250   0.0564   0.01336   0.00409  -0.0473   0.6615   0.0487
  -2.000   0.0819   0.01307   0.00379  -0.0467   0.6566   0.0664
  -1.750   0.1029   0.01212   0.00352  -0.0459   0.6504   0.2304
  -1.500   0.1185   0.01095   0.00345  -0.0440   0.6448   0.5306
  -1.250   0.1403   0.01062   0.00344  -0.0425   0.6395   0.6338
  -1.000   0.1622   0.01031   0.00348  -0.0408   0.6331   0.7269
  -0.750   0.1874   0.01012   0.00353  -0.0396   0.6276   0.8110
  -0.500   0.2219   0.01010   0.00358  -0.0403   0.6217   0.8722
  -0.250   0.2602   0.01014   0.00358  -0.0421   0.6148   0.9064
   0.000   0.3002   0.01022   0.00355  -0.0444   0.6089   0.9298
   0.250   0.3384   0.01027   0.00355  -0.0465   0.6015   0.9460
   0.500   0.3748   0.01033   0.00351  -0.0483   0.5949   0.9589
   0.750   0.4110   0.01039   0.00351  -0.0500   0.5878   0.9705
   1.000   0.4492   0.01044   0.00348  -0.0523   0.5807   0.9794
   1.250   0.4864   0.01049   0.00348  -0.0543   0.5735   0.9882
   1.500   0.5238   0.01054   0.00347  -0.0565   0.5660   0.9963
   1.750   0.5550   0.01060   0.00348  -0.0573   0.5590   1.0000
   2.000   0.5781   0.01067   0.00352  -0.0565   0.5519   1.0000
   2.250   0.6013   0.01076   0.00356  -0.0556   0.5452   1.0000
   2.500   0.6248   0.01086   0.00364  -0.0548   0.5373   1.0000
   2.750   0.6482   0.01096   0.00370  -0.0540   0.5299   1.0000
   3.000   0.6718   0.01107   0.00379  -0.0532   0.5213   1.0000
   3.250   0.6954   0.01119   0.00389  -0.0524   0.5127   1.0000
   3.500   0.7190   0.01133   0.00400  -0.0516   0.5043   1.0000
   3.750   0.7427   0.01146   0.00413  -0.0508   0.4957   1.0000
   4.000   0.7662   0.01162   0.00426  -0.0500   0.4869   1.0000
   4.250   0.7897   0.01177   0.00441  -0.0492   0.4761   1.0000
   4.500   0.8131   0.01194   0.00457  -0.0483   0.4666   1.0000
   4.750   0.8365   0.01212   0.00476  -0.0475   0.4577   1.0000
   5.000   0.8601   0.01231   0.00497  -0.0468   0.4484   1.0000
   5.250   0.8832   0.01251   0.00516  -0.0459   0.4388   1.0000
   5.500   0.9063   0.01271   0.00538  -0.0451   0.4270   1.0000
   5.750   0.9291   0.01293   0.00562  -0.0442   0.4145   1.0000
   6.000   0.9514   0.01317   0.00585  -0.0433   0.4007   1.0000
   6.250   0.9731   0.01345   0.00610  -0.0422   0.3857   1.0000
   6.500   0.9947   0.01375   0.00640  -0.0412   0.3708   1.0000
   6.750   1.0164   0.01406   0.00673  -0.0402   0.3567   1.0000
   7.000   1.0380   0.01437   0.00707  -0.0392   0.3427   1.0000
   7.250   1.0593   0.01471   0.00743  -0.0382   0.3276   1.0000
   7.500   1.0793   0.01510   0.00782  -0.0370   0.3089   1.0000
   7.750   1.0975   0.01558   0.00825  -0.0356   0.2854   1.0000
   8.000   1.1136   0.01618   0.00875  -0.0339   0.2572   1.0000
   8.250   1.1276   0.01691   0.00935  -0.0320   0.2256   1.0000
   8.500   1.1387   0.01779   0.01008  -0.0298   0.1939   1.0000
   8.750   1.1493   0.01869   0.01086  -0.0275   0.1705   1.0000
   9.000   1.1599   0.01955   0.01165  -0.0252   0.1469   1.0000
   9.250   1.1681   0.02046   0.01247  -0.0227   0.1275   1.0000
   9.500   1.1745   0.02134   0.01333  -0.0198   0.1118   1.0000
   9.750   1.1798   0.02233   0.01427  -0.0170   0.0971   1.0000
  10.000   1.1849   0.02341   0.01533  -0.0145   0.0866   1.0000
  10.250   1.1902   0.02458   0.01651  -0.0123   0.0787   1.0000
  10.500   1.1955   0.02585   0.01780  -0.0103   0.0718   1.0000
  10.750   1.2010   0.02720   0.01921  -0.0087   0.0666   1.0000
  11.000   1.2061   0.02869   0.02077  -0.0073   0.0616   1.0000
  11.250   1.2091   0.03044   0.02255  -0.0060   0.0576   1.0000
  11.500   1.2151   0.03204   0.02427  -0.0050   0.0535   1.0000
  11.750   1.2176   0.03402   0.02629  -0.0041   0.0497   1.0000
  12.000   1.2210   0.03601   0.02836  -0.0034   0.0464   1.0000
  12.250   1.2254   0.03796   0.03041  -0.0028   0.0433   1.0000
  12.500   1.2268   0.04026   0.03276  -0.0023   0.0406   1.0000
  12.750   1.2273   0.04268   0.03527  -0.0019   0.0387   1.0000
  13.000   1.2296   0.04499   0.03769  -0.0016   0.0369   1.0000
  13.250   1.2310   0.04745   0.04024  -0.0014   0.0352   1.0000
  13.500   1.2306   0.05014   0.04299  -0.0014   0.0338   1.0000
  13.750   1.2272   0.05323   0.04612  -0.0015   0.0324   1.0000
  14.000   1.2275   0.05598   0.04899  -0.0016   0.0313   1.0000
  14.250   1.2281   0.05879   0.05192  -0.0018   0.0302   1.0000
  14.500   1.2279   0.06177   0.05501  -0.0021   0.0291   1.0000
  14.750   1.2274   0.06488   0.05822  -0.0026   0.0282   1.0000
  15.000   1.2263   0.06814   0.06158  -0.0033   0.0274   1.0000
  15.250   1.2234   0.07171   0.06521  -0.0041   0.0265   1.0000
  15.500   1.2207   0.07527   0.06884  -0.0049   0.0259   1.0000
  15.750   1.2210   0.07856   0.07227  -0.0057   0.0251   1.0000
  16.000   1.2206   0.08201   0.07586  -0.0067   0.0243   1.0000
  16.250   1.2193   0.08565   0.07963  -0.0077   0.0236   1.0000
  16.500   1.2175   0.08945   0.08354  -0.0090   0.0229   1.0000
  16.750   1.2152   0.09334   0.08753  -0.0104   0.0224   1.0000
  17.000   1.2119   0.09751   0.09179  -0.0120   0.0217   1.0000
  17.250   1.2085   0.10170   0.09605  -0.0137   0.0212   1.0000
  17.500   1.2061   0.10565   0.10006  -0.0151   0.0208   1.0000
  17.750   1.2018   0.11025   0.10487  -0.0171   0.0203   1.0000
  18.000   1.1976   0.11485   0.10963  -0.0192   0.0198   1.0000
  18.250   1.1927   0.11965   0.11458  -0.0214   0.0194   1.0000
  18.500   1.1875   0.12456   0.11964  -0.0238   0.0190   1.0000
  18.750   1.1812   0.12984   0.12505  -0.0266   0.0185   1.0000
  19.000   1.1750   0.13514   0.13047  -0.0294   0.0181   1.0000
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