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BOEING-VERTOL VR-7 AIRFOIL WITH TAB (vr7b-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: BOEING-VERTOL VR-7 AIRFOIL WITH TAB (vr7b-il)
Reynolds number: 50,000
Max Cl/Cd: 30.75 at α=10°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-vr7b-il-50000.txt
Download as CSV file: xf-vr7b-il-50000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4261   0.10266   0.09687   0.0077   1.0000   0.3091
  -8.000  -0.4172   0.09932   0.09356   0.0072   1.0000   0.3267
  -7.750  -0.4157   0.09667   0.09098   0.0063   1.0000   0.3471
  -7.500  -0.4025   0.09299   0.08735   0.0065   1.0000   0.3682
  -7.250  -0.4021   0.09099   0.08543   0.0064   1.0000   0.3956
  -7.000  -0.3799   0.08733   0.08179   0.0077   1.0000   0.4258
  -6.750  -0.3566   0.08355   0.07803   0.0084   1.0000   0.4540
  -6.500  -0.3405   0.08028   0.07480   0.0087   1.0000   0.4811
  -6.250  -0.3291   0.07747   0.07204   0.0091   1.0000   0.5096
  -6.000  -0.3229   0.07522   0.06986   0.0101   1.0000   0.5390
  -5.000  -0.4612   0.05109   0.04413  -0.0309   1.0000   0.1758
  -4.750  -0.4421   0.04707   0.03971  -0.0314   1.0000   0.1587
  -4.500  -0.4199   0.04372   0.03561  -0.0320   1.0000   0.1441
  -4.250  -0.3997   0.04081   0.03254  -0.0321   1.0000   0.1385
  -4.000  -0.3732   0.03868   0.02940  -0.0323   1.0000   0.1296
  -3.750  -0.3496   0.03649   0.02700  -0.0325   1.0000   0.1278
  -3.500  -0.3079   0.03456   0.02457  -0.0354   0.9946   0.1287
  -3.250  -0.2624   0.03266   0.02236  -0.0389   0.9867   0.1320
  -3.000  -0.2170   0.03124   0.02078  -0.0421   0.9784   0.1357
  -2.750  -0.1687   0.03029   0.01962  -0.0454   0.9699   0.1456
  -2.500  -0.1268   0.02944   0.01878  -0.0478   0.9606   0.1613
  -2.250  -0.0855   0.02859   0.01809  -0.0506   0.9509   0.1929
  -2.000  -0.0164   0.02539   0.01810  -0.0496   0.9475   1.0000
  -1.750   0.0171   0.02591   0.01809  -0.0521   0.9354   1.0000
  -1.500   0.0473   0.02648   0.01828  -0.0541   0.9235   1.0000
  -1.250   0.0730   0.02708   0.01856  -0.0552   0.9116   1.0000
  -1.000   0.0966   0.02771   0.01890  -0.0558   0.9002   1.0000
  -0.750   0.1249   0.02839   0.01931  -0.0571   0.8892   1.0000
  -0.500   0.1658   0.02910   0.01976  -0.0603   0.8794   1.0000
  -0.250   0.1848   0.02979   0.02027  -0.0600   0.8678   1.0000
   0.000   0.2076   0.03055   0.02085  -0.0603   0.8570   1.0000
   0.250   0.2429   0.03132   0.02144  -0.0623   0.8472   1.0000
   0.500   0.2676   0.03210   0.02208  -0.0628   0.8362   1.0000
   0.750   0.2871   0.03298   0.02285  -0.0625   0.8254   1.0000
   1.000   0.3193   0.03381   0.02356  -0.0639   0.8157   1.0000
   1.250   0.3432   0.03469   0.02435  -0.0642   0.8049   1.0000
   1.500   0.3607   0.03574   0.02532  -0.0638   0.7944   1.0000
   1.750   0.3936   0.03658   0.02610  -0.0650   0.7850   1.0000
   2.000   0.4113   0.03769   0.02716  -0.0647   0.7745   1.0000
   2.250   0.4290   0.03888   0.02831  -0.0644   0.7644   1.0000
   2.500   0.4655   0.03968   0.02908  -0.0658   0.7557   1.0000
   2.750   0.4717   0.04121   0.03058  -0.0646   0.7450   1.0000
   3.000   0.4940   0.04242   0.03179  -0.0647   0.7356   1.0000
   3.250   0.5200   0.04355   0.03292  -0.0652   0.7263   1.0000
   3.500   0.5280   0.04521   0.03458  -0.0642   0.7164   1.0000
   3.750   0.5604   0.04624   0.03564  -0.0651   0.7074   1.0000
   4.000   0.5677   0.04803   0.03745  -0.0642   0.6975   1.0000
   4.250   0.5835   0.04965   0.03911  -0.0640   0.6881   1.0000
   4.500   0.6145   0.05076   0.04028  -0.0647   0.6786   1.0000
   4.750   0.6151   0.05298   0.04252  -0.0635   0.6682   1.0000
   5.000   0.6366   0.05440   0.04400  -0.0634   0.6570   1.0000
   5.250   0.6685   0.05523   0.04493  -0.0635   0.6442   1.0000
   5.500   0.6893   0.05648   0.04626  -0.0630   0.6311   1.0000
   5.750   0.6945   0.05857   0.04841  -0.0621   0.6182   1.0000
   6.000   0.7062   0.06050   0.05041  -0.0616   0.6060   1.0000
   6.250   0.7263   0.06200   0.05203  -0.0612   0.5936   1.0000
   6.500   0.7546   0.06300   0.05316  -0.0609   0.5811   1.0000
   6.750   0.7852   0.06361   0.05393  -0.0603   0.5675   1.0000
   7.000   0.7996   0.06516   0.05558  -0.0593   0.5526   1.0000
   7.250   0.8207   0.06614   0.05672  -0.0583   0.5372   1.0000
   7.500   0.8401   0.06723   0.05795  -0.0572   0.5218   1.0000
   7.750   0.8586   0.06839   0.05926  -0.0560   0.5065   1.0000
   8.000   0.8779   0.06945   0.06047  -0.0548   0.4911   1.0000
   8.250   0.8874   0.07136   0.06252  -0.0537   0.4748   1.0000
   8.500   0.8896   0.07400   0.06526  -0.0529   0.4579   1.0000
   8.750   0.8960   0.07599   0.06736  -0.0517   0.4394   1.0000
   9.000   1.0944   0.04970   0.04191  -0.0375   0.4127   1.0000
   9.250   1.1587   0.04302   0.03530  -0.0331   0.3823   1.0000
   9.500   1.1880   0.04095   0.03321  -0.0300   0.3455   1.0000
   9.750   1.2105   0.03987   0.03189  -0.0270   0.3045   1.0000
  10.000   1.2278   0.03993   0.03148  -0.0245   0.2651   1.0000
  10.250   1.2354   0.04164   0.03299  -0.0224   0.2346   1.0000
  10.500   1.2434   0.04364   0.03484  -0.0205   0.2094   1.0000
  10.750   1.2525   0.04611   0.03727  -0.0190   0.1888   1.0000
  11.000   1.2618   0.04878   0.03994  -0.0175   0.1716   1.0000
  11.250   1.2717   0.05167   0.04288  -0.0163   0.1578   1.0000
  11.500   1.2832   0.05471   0.04599  -0.0152   0.1467   1.0000
  11.750   1.3034   0.05777   0.04896  -0.0146   0.1361   1.0000
  12.000   1.2875   0.06150   0.05318  -0.0126   0.1333   1.0000
  12.250   1.2725   0.06544   0.05746  -0.0112   0.1304   1.0000
  12.500   1.3001   0.06897   0.06087  -0.0109   0.1227   1.0000
  12.750   1.2770   0.07348   0.06573  -0.0099   0.1223   1.0000
  13.000   1.2516   0.07868   0.07121  -0.0098   0.1222   1.0000
  13.250   1.2243   0.08463   0.07741  -0.0109   0.1224   1.0000
  13.500   1.1959   0.09142   0.08440  -0.0128   0.1229   1.0000
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