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BOEING-VERTOL VR-7 AIRFOIL WITH TAB (vr7b-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: BOEING-VERTOL VR-7 AIRFOIL WITH TAB (vr7b-il)
Reynolds number: 100,000
Max Cl/Cd: 52.09 at α=8.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-vr7b-il-100000.txt
Download as CSV file: xf-vr7b-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4835   0.11176   0.10754   0.0044   1.0000   0.0934
  -9.250  -0.4844   0.10777   0.10360  -0.0005   1.0000   0.0979
  -9.000  -0.5063   0.10290   0.09883  -0.0142   1.0000   0.0999
  -8.750  -0.4770   0.09870   0.09463  -0.0067   1.0000   0.1033
  -8.500  -0.4650   0.09527   0.09121  -0.0077   1.0000   0.1081
  -8.250  -0.4762   0.09001   0.08604  -0.0188   1.0000   0.1135
  -8.000  -0.4857   0.08316   0.07918  -0.0297   1.0000   0.1159
  -7.750  -0.4551   0.08185   0.07794  -0.0216   1.0000   0.1217
  -7.500  -0.4828   0.07619   0.07199  -0.0391   1.0000   0.1295
  -7.250  -0.4016   0.06109   0.05736  -0.0446   0.9854   0.1456
  -7.000  -0.3639   0.05729   0.05363  -0.0445   0.9807   0.1580
  -6.750  -0.3461   0.05183   0.04811  -0.0492   0.9720   0.1732
  -6.500  -0.4256   0.06111   0.05699  -0.0446   0.9842   0.1639
  -6.250  -0.3944   0.05766   0.05352  -0.0481   0.9755   0.1836
  -6.000  -0.3678   0.05414   0.04989  -0.0522   0.9656   0.2114
  -5.750  -0.3442   0.05142   0.04711  -0.0542   0.9549   0.2417
  -5.250  -0.2757   0.03685   0.02968  -0.0637   0.9304   0.0997
  -5.000  -0.2494   0.03306   0.02542  -0.0630   0.9200   0.0845
  -4.750  -0.2252   0.03060   0.02270  -0.0623   0.9097   0.0803
  -4.500  -0.2000   0.02894   0.02069  -0.0617   0.8986   0.0800
  -4.250  -0.1742   0.02747   0.01891  -0.0609   0.8888   0.0798
  -4.000  -0.1486   0.02612   0.01728  -0.0596   0.8805   0.0787
  -3.750  -0.1218   0.02492   0.01591  -0.0590   0.8706   0.0791
  -3.500  -0.0970   0.02393   0.01481  -0.0576   0.8625   0.0808
  -3.250  -0.0717   0.02320   0.01394  -0.0566   0.8528   0.0853
  -3.000  -0.0484   0.02207   0.01294  -0.0554   0.8437   0.0902
  -2.750  -0.0259   0.02130   0.01219  -0.0537   0.8355   0.0964
  -2.500  -0.0011   0.02058   0.01151  -0.0530   0.8262   0.1091
  -2.250   0.0218   0.01968   0.01074  -0.0514   0.8193   0.1432
  -2.000   0.0264   0.01712   0.01101  -0.0458   0.8108   0.7611
  -1.750   0.0337   0.01724   0.01129  -0.0380   0.8041   0.8786
  -1.500   0.0834   0.01749   0.01135  -0.0386   0.7968   0.9677
  -1.250   0.1709   0.01729   0.01079  -0.0490   0.7903   1.0000
  -1.000   0.1898   0.01723   0.01056  -0.0485   0.7815   1.0000
  -0.750   0.2074   0.01715   0.01031  -0.0472   0.7734   1.0000
  -0.500   0.2283   0.01726   0.01029  -0.0468   0.7642   1.0000
  -0.250   0.2464   0.01723   0.01010  -0.0451   0.7570   1.0000
   0.000   0.2689   0.01744   0.01019  -0.0448   0.7474   1.0000
   0.250   0.2883   0.01742   0.01002  -0.0430   0.7408   1.0000
   0.500   0.3131   0.01771   0.01022  -0.0431   0.7309   1.0000
   0.750   0.3349   0.01770   0.01006  -0.0415   0.7249   1.0000
   1.000   0.3617   0.01804   0.01033  -0.0420   0.7146   1.0000
   1.250   0.3851   0.01803   0.01018  -0.0406   0.7090   1.0000
   1.500   0.4129   0.01843   0.01055  -0.0412   0.6983   1.0000
   1.750   0.4382   0.01855   0.01056  -0.0404   0.6917   1.0000
   2.000   0.4656   0.01889   0.01087  -0.0407   0.6819   1.0000
   2.250   0.4920   0.01913   0.01105  -0.0404   0.6743   1.0000
   2.500   0.5190   0.01941   0.01131  -0.0404   0.6654   1.0000
   2.750   0.5461   0.01976   0.01163  -0.0404   0.6569   1.0000
   3.000   0.5729   0.01999   0.01182  -0.0401   0.6488   1.0000
   3.250   0.6003   0.02043   0.01229  -0.0404   0.6397   1.0000
   3.500   0.6271   0.02059   0.01242  -0.0400   0.6323   1.0000
   3.750   0.6545   0.02112   0.01299  -0.0404   0.6226   1.0000
   4.000   0.6814   0.02123   0.01308  -0.0398   0.6158   1.0000
   4.250   0.7086   0.02176   0.01369  -0.0403   0.6054   1.0000
   4.500   0.7355   0.02164   0.01350  -0.0393   0.5988   1.0000
   4.750   0.7625   0.02204   0.01399  -0.0396   0.5870   1.0000
   5.000   0.7893   0.02224   0.01424  -0.0393   0.5773   1.0000
   5.250   0.8167   0.02223   0.01423  -0.0388   0.5693   1.0000
   5.500   0.8434   0.02272   0.01484  -0.0391   0.5589   1.0000
   5.750   0.8712   0.02245   0.01453  -0.0381   0.5521   1.0000
   6.000   0.8978   0.02274   0.01495  -0.0382   0.5398   1.0000
   6.250   0.9245   0.02297   0.01528  -0.0380   0.5286   1.0000
   6.500   0.9523   0.02282   0.01511  -0.0373   0.5202   1.0000
   6.750   0.9792   0.02289   0.01530  -0.0370   0.5082   1.0000
   7.000   1.0059   0.02267   0.01512  -0.0364   0.4937   1.0000
   7.250   1.0327   0.02230   0.01475  -0.0356   0.4778   1.0000
   7.500   1.0593   0.02208   0.01456  -0.0349   0.4616   1.0000
   7.750   1.0856   0.02211   0.01466  -0.0345   0.4460   1.0000
   8.000   1.1112   0.02221   0.01487  -0.0342   0.4283   1.0000
   8.250   1.1357   0.02234   0.01515  -0.0338   0.4073   1.0000
   8.500   1.1603   0.02236   0.01513  -0.0332   0.3852   1.0000
   8.750   1.1819   0.02269   0.01554  -0.0326   0.3565   1.0000
   9.000   1.2011   0.02318   0.01607  -0.0320   0.3217   1.0000
   9.250   1.2161   0.02405   0.01683  -0.0311   0.2798   1.0000
   9.500   1.2252   0.02558   0.01814  -0.0299   0.2332   1.0000
   9.750   1.2287   0.02763   0.01987  -0.0284   0.1950   1.0000
  10.000   1.2305   0.02985   0.02187  -0.0267   0.1673   1.0000
  10.250   1.2311   0.03195   0.02382  -0.0248   0.1478   1.0000
  10.500   1.2330   0.03403   0.02584  -0.0231   0.1319   1.0000
  10.750   1.2366   0.03619   0.02793  -0.0216   0.1186   1.0000
  11.000   1.2419   0.03833   0.02998  -0.0202   0.1072   1.0000
  11.250   1.2500   0.04035   0.03192  -0.0190   0.0977   1.0000
  11.500   1.2605   0.04241   0.03409  -0.0177   0.0898   1.0000
  11.750   1.2770   0.04440   0.03596  -0.0165   0.0827   1.0000
  12.000   1.2861   0.04656   0.03833  -0.0155   0.0775   1.0000
  12.250   1.3180   0.04890   0.04050  -0.0148   0.0719   1.0000
  12.500   1.3212   0.05140   0.04336  -0.0136   0.0694   1.0000
  12.750   1.3262   0.05400   0.04621  -0.0126   0.0665   1.0000
  13.000   1.3327   0.05658   0.04893  -0.0119   0.0639   1.0000
  13.250   1.3583   0.06034   0.05268  -0.0115   0.0610   1.0000
  13.500   1.3494   0.06397   0.05663  -0.0105   0.0603   1.0000
  13.750   1.3357   0.06772   0.06073  -0.0099   0.0598   1.0000
  14.000   1.3199   0.07197   0.06530  -0.0100   0.0593   1.0000
  14.250   1.3018   0.07673   0.07036  -0.0105   0.0589   1.0000
  14.500   1.2814   0.08204   0.07596  -0.0118   0.0587   1.0000
  14.750   1.2587   0.08797   0.08216  -0.0136   0.0587   1.0000
  15.000   1.2340   0.09454   0.08898  -0.0162   0.0589   1.0000
  15.250   1.2072   0.10187   0.09654  -0.0196   0.0592   1.0000
  15.500   1.1797   0.10996   0.10482  -0.0237   0.0596   1.0000
  15.750   1.1521   0.11889   0.11391  -0.0286   0.0602   1.0000
  16.000   1.1262   0.12842   0.12357  -0.0339   0.0607   1.0000
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