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BOEING-VERTOL VR-7 AIRFOIL (vr7-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: BOEING-VERTOL VR-7 AIRFOIL (vr7-il)
Reynolds number: 100,000
Max Cl/Cd: 53.45 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-vr7-il-100000-n5.txt
Download as CSV file: xf-vr7-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4254   0.07434   0.06961  -0.0498   1.0000   0.0380
  -8.500  -0.4279   0.07146   0.06678  -0.0491   1.0000   0.0375
  -8.250  -0.4327   0.06827   0.06363  -0.0487   1.0000   0.0369
  -8.000  -0.4409   0.06480   0.06016  -0.0483   1.0000   0.0363
  -7.750  -0.4499   0.06153   0.05689  -0.0472   1.0000   0.0355
  -7.500  -0.4446   0.05594   0.05108  -0.0503   0.9825   0.0340
  -7.000  -0.4134   0.04262   0.03628  -0.0568   0.9377   0.0309
  -6.750  -0.3899   0.03894   0.03214  -0.0582   0.9201   0.0312
  -6.500  -0.3628   0.03672   0.02987  -0.0598   0.9041   0.0325
  -6.250  -0.3376   0.03452   0.02735  -0.0605   0.8875   0.0338
  -6.000  -0.3138   0.03205   0.02442  -0.0603   0.8718   0.0343
  -5.750  -0.2898   0.02980   0.02170  -0.0598   0.8572   0.0345
  -5.500  -0.2652   0.02790   0.01939  -0.0592   0.8441   0.0348
  -5.250  -0.2399   0.02624   0.01734  -0.0586   0.8322   0.0353
  -5.000  -0.2146   0.02487   0.01565  -0.0578   0.8202   0.0365
  -4.750  -0.1884   0.02389   0.01427  -0.0571   0.8096   0.0383
  -4.500  -0.1625   0.02252   0.01283  -0.0568   0.8002   0.0396
  -4.250  -0.1367   0.02150   0.01173  -0.0563   0.7902   0.0408
  -4.000  -0.1105   0.02062   0.01075  -0.0558   0.7820   0.0422
  -3.750  -0.0854   0.01984   0.00991  -0.0551   0.7729   0.0440
  -3.500  -0.0602   0.01926   0.00918  -0.0544   0.7650   0.0471
  -3.250  -0.0370   0.01859   0.00852  -0.0536   0.7565   0.0508
  -3.000  -0.0128   0.01810   0.00793  -0.0527   0.7488   0.0548
  -2.750   0.0111   0.01763   0.00737  -0.0518   0.7399   0.0606
  -2.500   0.0352   0.01716   0.00682  -0.0510   0.7314   0.0726
  -2.250   0.0580   0.01645   0.00631  -0.0500   0.7230   0.1131
  -2.000   0.0708   0.01452   0.00617  -0.0478   0.7156   0.5382
  -1.750   0.0912   0.01404   0.00626  -0.0454   0.7083   0.7052
  -1.500   0.1211   0.01388   0.00642  -0.0440   0.7018   0.8299
  -1.250   0.1678   0.01402   0.00653  -0.0462   0.6942   0.9022
  -1.000   0.2115   0.01411   0.00639  -0.0489   0.6879   0.9304
  -0.750   0.2519   0.01417   0.00630  -0.0515   0.6799   0.9471
  -0.500   0.2923   0.01420   0.00612  -0.0540   0.6734   0.9611
  -0.250   0.3326   0.01424   0.00604  -0.0568   0.6654   0.9751
   0.000   0.3734   0.01426   0.00589  -0.0596   0.6585   0.9881
   0.250   0.4139   0.01428   0.00581  -0.0626   0.6508   1.0000
   0.500   0.4346   0.01436   0.00577  -0.0615   0.6437   1.0000
   0.750   0.4558   0.01446   0.00580  -0.0604   0.6366   1.0000
   1.000   0.4774   0.01457   0.00584  -0.0594   0.6293   1.0000
   1.250   0.4998   0.01470   0.00587  -0.0585   0.6226   1.0000
   1.500   0.5218   0.01484   0.00598  -0.0575   0.6146   1.0000
   1.750   0.5451   0.01497   0.00601  -0.0566   0.6085   1.0000
   2.000   0.5671   0.01514   0.00619  -0.0557   0.6001   1.0000
   2.250   0.5908   0.01527   0.00624  -0.0548   0.5938   1.0000
   2.500   0.6132   0.01547   0.00647  -0.0539   0.5855   1.0000
   2.750   0.6370   0.01561   0.00655  -0.0531   0.5788   1.0000
   3.000   0.6596   0.01582   0.00678  -0.0522   0.5707   1.0000
   3.250   0.6835   0.01596   0.00691  -0.0514   0.5638   1.0000
   3.500   0.7063   0.01618   0.00716  -0.0506   0.5556   1.0000
   3.750   0.7303   0.01634   0.00729  -0.0498   0.5486   1.0000
   4.000   0.7530   0.01656   0.00755  -0.0489   0.5397   1.0000
   4.250   0.7773   0.01669   0.00767  -0.0481   0.5323   1.0000
   4.500   0.7997   0.01693   0.00798  -0.0472   0.5224   1.0000
   4.750   0.8232   0.01710   0.00815  -0.0464   0.5136   1.0000
   5.000   0.8463   0.01729   0.00839  -0.0455   0.5038   1.0000
   5.250   0.8691   0.01752   0.00868  -0.0446   0.4940   1.0000
   5.500   0.8929   0.01771   0.00886  -0.0438   0.4853   1.0000
   5.750   0.9152   0.01797   0.00923  -0.0429   0.4747   1.0000
   6.000   0.9377   0.01822   0.00954  -0.0419   0.4641   1.0000
   6.250   0.9605   0.01844   0.00979  -0.0410   0.4537   1.0000
   6.500   0.9826   0.01874   0.01018  -0.0401   0.4429   1.0000
   6.750   1.0041   0.01903   0.01058  -0.0390   0.4308   1.0000
   7.000   1.0245   0.01928   0.01087  -0.0378   0.4150   1.0000
   7.250   1.0439   0.01953   0.01111  -0.0363   0.3966   1.0000
   7.500   1.0624   0.01989   0.01149  -0.0348   0.3776   1.0000
   7.750   1.0810   0.02031   0.01196  -0.0334   0.3608   1.0000
   8.000   1.0992   0.02077   0.01251  -0.0320   0.3444   1.0000
   8.250   1.1162   0.02127   0.01308  -0.0305   0.3262   1.0000
   8.500   1.1312   0.02184   0.01367  -0.0286   0.3054   1.0000
   8.750   1.1438   0.02252   0.01435  -0.0266   0.2801   1.0000
   9.000   1.1532   0.02335   0.01512  -0.0242   0.2527   1.0000
   9.250   1.1594   0.02436   0.01603  -0.0215   0.2253   1.0000
   9.500   1.1609   0.02551   0.01706  -0.0183   0.2004   1.0000
   9.750   1.1600   0.02683   0.01829  -0.0150   0.1805   1.0000
  10.000   1.1594   0.02831   0.01971  -0.0122   0.1621   1.0000
  10.250   1.1595   0.02991   0.02130  -0.0099   0.1443   1.0000
  10.500   1.1583   0.03175   0.02310  -0.0079   0.1291   1.0000
  10.750   1.1568   0.03379   0.02510  -0.0063   0.1172   1.0000
  11.000   1.1562   0.03592   0.02724  -0.0051   0.1057   1.0000
  11.250   1.1565   0.03810   0.02946  -0.0041   0.0966   1.0000
  11.500   1.1558   0.04046   0.03186  -0.0033   0.0895   1.0000
  11.750   1.1542   0.04300   0.03443  -0.0027   0.0832   1.0000
  12.000   1.1537   0.04552   0.03700  -0.0022   0.0779   1.0000
  12.250   1.1535   0.04807   0.03964  -0.0017   0.0730   1.0000
  12.500   1.1501   0.05099   0.04254  -0.0015   0.0689   1.0000
  12.750   1.1521   0.05346   0.04516  -0.0012   0.0644   1.0000
  13.000   1.1516   0.05621   0.04798  -0.0011   0.0610   1.0000
  13.500   1.1530   0.06157   0.05349  -0.0008   0.0554   1.0000
  13.750   1.1549   0.06424   0.05629  -0.0007   0.0525   1.0000
  14.000   1.1557   0.06707   0.05918  -0.0009   0.0503   1.0000
  14.250   1.1571   0.06981   0.06191  -0.0010   0.0482   1.0000
  14.500   1.1594   0.07272   0.06503  -0.0012   0.0460   1.0000
  14.750   1.1617   0.07563   0.06811  -0.0015   0.0441   1.0000
  15.000   1.1635   0.07863   0.07123  -0.0019   0.0425   1.0000
  15.250   1.1644   0.08179   0.07447  -0.0026   0.0411   1.0000
  15.500   1.1663   0.08478   0.07751  -0.0031   0.0399   1.0000
  15.750   1.1654   0.08841   0.08131  -0.0040   0.0387   1.0000
  16.000   1.1612   0.09272   0.08587  -0.0054   0.0375   1.0000
  16.250   1.1559   0.09730   0.09066  -0.0071   0.0364   1.0000
  16.500   1.1507   0.10192   0.09547  -0.0089   0.0356   1.0000
  16.750   1.1446   0.10677   0.10048  -0.0110   0.0348   1.0000
  17.000   1.1382   0.11178   0.10563  -0.0133   0.0341   1.0000
  17.250   1.1325   0.11671   0.11068  -0.0156   0.0334   1.0000
  17.500   1.1286   0.12133   0.11538  -0.0179   0.0327   1.0000
  17.750   1.1225   0.12644   0.12057  -0.0205   0.0321   1.0000
  18.000   1.1035   0.13479   0.12916  -0.0254   0.0319   1.0000
  18.250   1.0809   0.14443   0.13902  -0.0312   0.0318   1.0000
  18.500   1.0551   0.15551   0.15027  -0.0380   0.0320   1.0000
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