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BOEING-VERTOL VR-7 AIRFOIL WITH TAB (vr7b-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: BOEING-VERTOL VR-7 AIRFOIL WITH TAB (vr7b-il)
Reynolds number: 50,000
Max Cl/Cd: 33.25 at α=8.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-vr7b-il-50000-n5.txt
Download as CSV file: xf-vr7b-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: BOEING-VERTOL VR-7 AIRFOIL WITH TAB             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.4902   0.13401   0.12773   0.0110   1.0000   0.1181
 -10.500  -0.4853   0.13047   0.12422   0.0089   1.0000   0.1226
 -10.250  -0.5030   0.12843   0.12229   0.0020   1.0000   0.1270
 -10.000  -0.4853   0.12297   0.11685   0.0026   1.0000   0.1290
  -9.750  -0.4707   0.11883   0.11270   0.0026   1.0000   0.1324
  -9.500  -0.4648   0.11513   0.10903   0.0005   1.0000   0.1367
  -9.250  -0.3611   0.09334   0.08754  -0.0253   1.0000   0.0723
  -9.000  -0.3526   0.08929   0.08351  -0.0259   1.0000   0.0706
  -8.750  -0.3515   0.08468   0.07894  -0.0280   1.0000   0.0689
  -8.500  -0.4688   0.08695   0.08092  -0.0272   1.0000   0.0610
  -8.250  -0.4645   0.08254   0.07655  -0.0301   1.0000   0.0599
  -8.000  -0.4620   0.07766   0.07165  -0.0341   1.0000   0.0589
  -7.750  -0.4604   0.07280   0.06672  -0.0379   1.0000   0.0581
  -7.500  -0.4588   0.06820   0.06201  -0.0410   1.0000   0.0574
  -7.250  -0.4580   0.06408   0.05775  -0.0428   1.0000   0.0569
  -7.000  -0.4608   0.06076   0.05428  -0.0428   1.0000   0.0564
  -6.750  -0.4441   0.05591   0.04903  -0.0465   0.9863   0.0556
  -6.500  -0.4184   0.05070   0.04324  -0.0508   0.9739   0.0542
  -6.250  -0.3904   0.04628   0.03818  -0.0540   0.9627   0.0533
  -6.000  -0.3607   0.04274   0.03405  -0.0563   0.9522   0.0530
  -5.750  -0.3317   0.04004   0.03094  -0.0578   0.9414   0.0537
  -5.500  -0.3047   0.03799   0.02851  -0.0586   0.9297   0.0558
  -5.250  -0.2790   0.03610   0.02621  -0.0587   0.9174   0.0577
  -5.000  -0.2529   0.03433   0.02403  -0.0585   0.9054   0.0588
  -4.750  -0.2258   0.03273   0.02205  -0.0582   0.8947   0.0598
  -4.500  -0.1992   0.03137   0.02036  -0.0576   0.8836   0.0610
  -4.250  -0.1734   0.03010   0.01898  -0.0571   0.8730   0.0639
  -4.000  -0.1474   0.02909   0.01788  -0.0564   0.8639   0.0681
  -3.750  -0.1215   0.02820   0.01679  -0.0555   0.8540   0.0717
  -3.500  -0.0966   0.02727   0.01578  -0.0547   0.8448   0.0755
  -3.250  -0.0717   0.02651   0.01491  -0.0540   0.8363   0.0830
  -3.000  -0.0471   0.02575   0.01412  -0.0535   0.8269   0.0920
  -2.750  -0.0226   0.02498   0.01332  -0.0528   0.8192   0.1078
  -2.500   0.0016   0.02388   0.01260  -0.0527   0.8098   0.1623
  -2.250   0.0101   0.02157   0.01260  -0.0485   0.8030   0.6335
  -2.000   0.0219   0.02156   0.01322  -0.0411   0.7940   0.8497
  -1.750   0.1173   0.02147   0.01264  -0.0495   0.7889   0.9863
  -1.500   0.1561   0.02133   0.01218  -0.0524   0.7790   1.0000
  -1.250   0.1732   0.02123   0.01183  -0.0509   0.7707   1.0000
  -1.000   0.1925   0.02133   0.01170  -0.0503   0.7599   1.0000
  -0.750   0.2117   0.02139   0.01155  -0.0493   0.7513   1.0000
  -0.500   0.2316   0.02151   0.01147  -0.0483   0.7424   1.0000
  -0.250   0.2524   0.02169   0.01146  -0.0475   0.7335   1.0000
   0.000   0.2743   0.02181   0.01139  -0.0466   0.7259   1.0000
   0.250   0.2975   0.02208   0.01151  -0.0462   0.7170   1.0000
   0.500   0.3211   0.02221   0.01147  -0.0454   0.7098   1.0000
   0.750   0.3455   0.02254   0.01167  -0.0453   0.7008   1.0000
   1.000   0.3702   0.02270   0.01169  -0.0446   0.6939   1.0000
   1.250   0.3953   0.02308   0.01198  -0.0446   0.6847   1.0000
   1.500   0.4206   0.02325   0.01204  -0.0440   0.6778   1.0000
   1.750   0.4460   0.02369   0.01243  -0.0441   0.6685   1.0000
   2.000   0.4717   0.02388   0.01253  -0.0436   0.6615   1.0000
   2.250   0.4972   0.02437   0.01300  -0.0437   0.6521   1.0000
   2.500   0.5232   0.02459   0.01315  -0.0432   0.6451   1.0000
   2.750   0.5485   0.02513   0.01370  -0.0434   0.6355   1.0000
   3.000   0.5748   0.02535   0.01389  -0.0429   0.6287   1.0000
   3.250   0.5998   0.02597   0.01455  -0.0432   0.6188   1.0000
   3.500   0.6263   0.02617   0.01473  -0.0427   0.6121   1.0000
   3.750   0.6508   0.02688   0.01552  -0.0430   0.6021   1.0000
   4.000   0.6776   0.02704   0.01568  -0.0424   0.5956   1.0000
   4.250   0.7015   0.02783   0.01656  -0.0428   0.5852   1.0000
   4.500   0.7288   0.02792   0.01665  -0.0421   0.5791   1.0000
   4.750   0.7518   0.02878   0.01767  -0.0424   0.5681   1.0000
   5.000   0.7776   0.02914   0.01808  -0.0421   0.5605   1.0000
   5.250   0.8019   0.02968   0.01873  -0.0419   0.5510   1.0000
   5.500   0.8256   0.03026   0.01945  -0.0417   0.5409   1.0000
   5.750   0.8532   0.03014   0.01938  -0.0408   0.5328   1.0000
   6.000   0.8755   0.03076   0.02014  -0.0406   0.5204   1.0000
   6.250   0.8991   0.03119   0.02069  -0.0401   0.5095   1.0000
   6.500   0.9270   0.03108   0.02069  -0.0393   0.5014   1.0000
   6.750   0.9481   0.03185   0.02165  -0.0391   0.4892   1.0000
   7.000   0.9708   0.03231   0.02226  -0.0385   0.4772   1.0000
   7.250   0.9958   0.03241   0.02251  -0.0377   0.4657   1.0000
   7.500   1.0223   0.03227   0.02247  -0.0368   0.4542   1.0000
   7.750   1.0431   0.03283   0.02323  -0.0362   0.4401   1.0000
   8.000   1.0647   0.03312   0.02369  -0.0353   0.4248   1.0000
   8.250   1.0858   0.03317   0.02386  -0.0341   0.4063   1.0000
   8.500   1.1023   0.03357   0.02438  -0.0329   0.3843   1.0000
   8.750   1.1210   0.03371   0.02454  -0.0315   0.3623   1.0000
   9.000   1.1328   0.03473   0.02573  -0.0304   0.3398   1.0000
   9.250   1.1454   0.03563   0.02672  -0.0292   0.3180   1.0000
   9.500   1.1548   0.03682   0.02800  -0.0280   0.2955   1.0000
   9.750   1.1605   0.03820   0.02937  -0.0265   0.2724   1.0000
  10.000   1.1616   0.04002   0.03117  -0.0251   0.2491   1.0000
  10.250   1.1620   0.04208   0.03314  -0.0239   0.2269   1.0000
  10.500   1.1609   0.04457   0.03559  -0.0231   0.2059   1.0000
  10.750   1.1588   0.04727   0.03818  -0.0224   0.1875   1.0000
  11.000   1.1569   0.05012   0.04096  -0.0219   0.1715   1.0000
  11.250   1.1552   0.05310   0.04391  -0.0215   0.1569   1.0000
  11.500   1.1539   0.05612   0.04694  -0.0213   0.1441   1.0000
  11.750   1.1533   0.05912   0.04994  -0.0211   0.1335   1.0000
  12.000   1.1527   0.06207   0.05279  -0.0209   0.1244   1.0000
  12.250   1.1528   0.06522   0.05609  -0.0209   0.1152   1.0000
  12.500   1.1534   0.06826   0.05919  -0.0208   0.1078   1.0000
  12.750   1.1536   0.07139   0.06239  -0.0209   0.1008   1.0000
  13.000   1.1550   0.07448   0.06557  -0.0208   0.0951   1.0000
  13.250   1.1556   0.07773   0.06896  -0.0210   0.0897   1.0000
  13.500   1.1596   0.08036   0.07154  -0.0207   0.0850   1.0000
  13.750   1.1575   0.08443   0.07593  -0.0213   0.0812   1.0000
  14.000   1.1564   0.08821   0.07989  -0.0219   0.0776   1.0000
  14.250   1.1640   0.09038   0.08198  -0.0214   0.0738   1.0000
  14.500   1.1555   0.09567   0.08756  -0.0230   0.0716   1.0000
  14.750   1.1429   0.10184   0.09405  -0.0254   0.0699   1.0000
  15.000   1.1281   0.10867   0.10114  -0.0284   0.0686   1.0000
  15.250   1.1089   0.11672   0.10945  -0.0323   0.0679   1.0000
  15.500   1.0808   0.12744   0.12040  -0.0383   0.0677   1.0000
  15.750   1.0347   0.14417   0.13729  -0.0483   0.0686   1.0000
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