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BOEING-VERTOL VR-7 AIRFOIL (vr7-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: BOEING-VERTOL VR-7 AIRFOIL (vr7-il)
Reynolds number: 500,000
Max Cl/Cd: 96.22 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-vr7-il-500000-n5.txt
Download as CSV file: xf-vr7-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4519   0.07870   0.07646  -0.0379   1.0000   0.0103
  -9.750  -0.4715   0.07028   0.06808  -0.0435   1.0000   0.0102
  -9.500  -0.5210   0.05633   0.05407  -0.0553   0.9984   0.0102
  -9.250  -0.5106   0.04733   0.04471  -0.0662   0.9283   0.0104
  -9.000  -0.5019   0.04325   0.04024  -0.0684   0.8666   0.0106
  -8.750  -0.5024   0.04022   0.03684  -0.0667   0.8232   0.0108
  -8.500  -0.5020   0.03666   0.03291  -0.0648   0.7959   0.0110
  -8.250  -0.5048   0.03145   0.02718  -0.0624   0.7767   0.0113
  -8.000  -0.5037   0.02621   0.02129  -0.0596   0.7622   0.0118
  -7.750  -0.4934   0.02256   0.01702  -0.0574   0.7502   0.0124
  -7.500  -0.4751   0.02063   0.01464  -0.0561   0.7392   0.0128
  -7.250  -0.4543   0.01933   0.01311  -0.0551   0.7292   0.0132
  -7.000  -0.4312   0.01870   0.01236  -0.0545   0.7198   0.0136
  -6.750  -0.4073   0.01805   0.01159  -0.0539   0.7113   0.0139
  -6.500  -0.3835   0.01728   0.01064  -0.0533   0.7040   0.0142
  -6.250  -0.3591   0.01651   0.00973  -0.0527   0.6970   0.0146
  -6.000  -0.3346   0.01580   0.00887  -0.0521   0.6905   0.0150
  -5.750  -0.3099   0.01511   0.00805  -0.0515   0.6843   0.0154
  -5.500  -0.2850   0.01451   0.00733  -0.0509   0.6774   0.0157
  -5.250  -0.2596   0.01409   0.00678  -0.0504   0.6710   0.0162
  -5.000  -0.2351   0.01347   0.00609  -0.0498   0.6642   0.0167
  -4.750  -0.2102   0.01302   0.00559  -0.0492   0.6583   0.0172
  -4.500  -0.1848   0.01262   0.00515  -0.0488   0.6529   0.0175
  -4.250  -0.1592   0.01226   0.00474  -0.0483   0.6472   0.0181
  -4.000  -0.1337   0.01195   0.00436  -0.0478   0.6414   0.0186
  -3.750  -0.1077   0.01164   0.00400  -0.0474   0.6359   0.0192
  -3.500  -0.0816   0.01136   0.00367  -0.0470   0.6309   0.0199
  -3.250  -0.0555   0.01110   0.00335  -0.0466   0.6264   0.0206
  -3.000  -0.0292   0.01085   0.00309  -0.0462   0.6217   0.0220
  -2.750  -0.0025   0.01065   0.00287  -0.0460   0.6163   0.0234
  -2.500   0.0242   0.01049   0.00265  -0.0457   0.6111   0.0249
  -2.250   0.0510   0.01030   0.00245  -0.0454   0.6064   0.0275
  -2.000   0.0781   0.01015   0.00229  -0.0451   0.6011   0.0315
  -1.750   0.1049   0.01000   0.00214  -0.0449   0.5957   0.0397
  -1.500   0.1315   0.00981   0.00202  -0.0446   0.5904   0.0625
  -1.250   0.1563   0.00935   0.00187  -0.0442   0.5844   0.1620
  -1.000   0.1796   0.00875   0.00173  -0.0436   0.5788   0.3118
  -0.750   0.2006   0.00803   0.00169  -0.0425   0.5729   0.5235
  -0.500   0.2253   0.00781   0.00168  -0.0419   0.5665   0.5951
   0.000   0.2746   0.00745   0.00168  -0.0403   0.5540   0.7106
   0.250   0.2984   0.00730   0.00170  -0.0393   0.5479   0.7715
   0.500   0.3239   0.00719   0.00173  -0.0386   0.5413   0.8159
   0.750   0.3504   0.00715   0.00176  -0.0381   0.5345   0.8563
   1.250   0.4146   0.00719   0.00186  -0.0395   0.5203   0.9223
   1.500   0.4524   0.00727   0.00191  -0.0416   0.5118   0.9424
   1.750   0.4903   0.00738   0.00196  -0.0437   0.5023   0.9578
   2.000   0.5275   0.00746   0.00201  -0.0457   0.4934   0.9680
   2.250   0.5623   0.00757   0.00206  -0.0473   0.4838   0.9749
   2.500   0.5952   0.00769   0.00212  -0.0484   0.4726   0.9818
   2.750   0.6290   0.00780   0.00219  -0.0498   0.4624   0.9871
   3.000   0.6627   0.00792   0.00227  -0.0512   0.4539   0.9921
   3.250   0.6965   0.00803   0.00236  -0.0526   0.4444   0.9964
   3.500   0.7308   0.00815   0.00244  -0.0541   0.4342   0.9998
   3.750   0.7551   0.00829   0.00254  -0.0535   0.4234   1.0000
   4.000   0.7784   0.00844   0.00266  -0.0526   0.4112   1.0000
   4.250   0.8018   0.00860   0.00278  -0.0518   0.3995   1.0000
   4.500   0.8251   0.00877   0.00292  -0.0510   0.3897   1.0000
   4.750   0.8481   0.00897   0.00308  -0.0501   0.3787   1.0000
   5.000   0.8716   0.00915   0.00324  -0.0494   0.3685   1.0000
   5.250   0.8952   0.00933   0.00341  -0.0486   0.3591   1.0000
   5.500   0.9182   0.00955   0.00360  -0.0478   0.3462   1.0000
   5.750   0.9410   0.00978   0.00381  -0.0469   0.3310   1.0000
   6.000   0.9637   0.01002   0.00402  -0.0460   0.3167   1.0000
   6.250   0.9860   0.01030   0.00425  -0.0451   0.3005   1.0000
   6.500   1.0079   0.01060   0.00452  -0.0441   0.2836   1.0000
   6.750   1.0281   0.01102   0.00483  -0.0429   0.2598   1.0000
   7.000   1.0460   0.01160   0.00524  -0.0414   0.2240   1.0000
   7.250   1.0621   0.01231   0.00575  -0.0397   0.1882   1.0000
   7.500   1.0802   0.01287   0.00621  -0.0382   0.1651   1.0000
   7.750   1.0976   0.01347   0.00669  -0.0367   0.1404   1.0000
   8.000   1.1151   0.01405   0.00717  -0.0352   0.1220   1.0000
   8.250   1.1328   0.01459   0.00766  -0.0338   0.1041   1.0000
   8.500   1.1489   0.01521   0.00820  -0.0321   0.0876   1.0000
   8.750   1.1654   0.01577   0.00873  -0.0305   0.0769   1.0000
   9.000   1.1813   0.01634   0.00928  -0.0289   0.0688   1.0000
   9.250   1.1974   0.01686   0.00981  -0.0272   0.0629   1.0000
   9.500   1.2110   0.01744   0.01039  -0.0252   0.0576   1.0000
   9.750   1.2234   0.01796   0.01095  -0.0229   0.0531   1.0000
  10.000   1.2332   0.01862   0.01161  -0.0203   0.0488   1.0000
  10.250   1.2456   0.01919   0.01223  -0.0183   0.0452   1.0000
  10.500   1.2555   0.01994   0.01301  -0.0162   0.0405   1.0000
  10.750   1.2652   0.02076   0.01385  -0.0142   0.0367   1.0000
  11.000   1.2732   0.02175   0.01485  -0.0122   0.0330   1.0000
  11.250   1.2822   0.02276   0.01591  -0.0106   0.0305   1.0000
  11.500   1.2900   0.02393   0.01712  -0.0091   0.0280   1.0000
  11.750   1.2961   0.02532   0.01855  -0.0077   0.0260   1.0000
  12.000   1.3047   0.02662   0.01993  -0.0067   0.0246   1.0000
  12.250   1.3121   0.02808   0.02146  -0.0058   0.0235   1.0000
  12.500   1.3178   0.02976   0.02320  -0.0049   0.0223   1.0000
  12.750   1.3214   0.03170   0.02518  -0.0042   0.0210   1.0000
  13.000   1.3272   0.03350   0.02707  -0.0036   0.0205   1.0000
  13.250   1.3330   0.03534   0.02900  -0.0032   0.0198   1.0000
  13.500   1.3372   0.03737   0.03112  -0.0027   0.0192   1.0000
  13.750   1.3405   0.03952   0.03335  -0.0024   0.0184   1.0000
  14.000   1.3424   0.04185   0.03575  -0.0022   0.0178   1.0000
  14.250   1.3428   0.04439   0.03836  -0.0020   0.0173   1.0000
  14.500   1.3398   0.04733   0.04138  -0.0020   0.0167   1.0000
  14.750   1.3420   0.04981   0.04396  -0.0020   0.0163   1.0000
  15.000   1.3416   0.05265   0.04690  -0.0022   0.0160   1.0000
  15.250   1.3429   0.05536   0.04970  -0.0025   0.0154   1.0000
  15.500   1.3425   0.05837   0.05281  -0.0030   0.0151   1.0000
  15.750   1.3412   0.06158   0.05611  -0.0035   0.0147   1.0000
  16.000   1.3389   0.06498   0.05961  -0.0042   0.0144   1.0000
  16.250   1.3356   0.06859   0.06331  -0.0051   0.0140   1.0000
  16.500   1.3315   0.07240   0.06720  -0.0061   0.0136   1.0000
  16.750   1.3254   0.07658   0.07147  -0.0073   0.0134   1.0000
  17.000   1.3190   0.08086   0.07584  -0.0086   0.0131   1.0000
  17.250   1.3164   0.08468   0.07978  -0.0099   0.0128   1.0000
  17.500   1.3130   0.08870   0.08391  -0.0112   0.0125   1.0000
  17.750   1.3093   0.09282   0.08813  -0.0127   0.0122   1.0000
  18.000   1.3042   0.09719   0.09261  -0.0144   0.0119   1.0000
  18.250   1.2984   0.10174   0.09726  -0.0162   0.0117   1.0000
  18.500   1.2921   0.10648   0.10210  -0.0181   0.0114   1.0000
  18.750   1.2858   0.11132   0.10704  -0.0202   0.0111   1.0000
  19.000   1.2784   0.11636   0.11218  -0.0225   0.0109   1.0000
  19.250   1.2705   0.12159   0.11750  -0.0250   0.0107   1.0000
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