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BOEING-VERTOL VR-7 AIRFOIL WITH TAB (vr7b-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: BOEING-VERTOL VR-7 AIRFOIL WITH TAB (vr7b-il)
Reynolds number: 500,000
Max Cl/Cd: 92.8 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-vr7b-il-500000-n5.txt
Download as CSV file: xf-vr7b-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.6052   0.08038   0.07806   0.0075   0.8026   0.0098
  -8.500  -0.6225   0.06967   0.06726  -0.0052   0.7905   0.0097
  -8.250  -0.7012   0.03474   0.03086  -0.0175   0.7889   0.0107
  -8.000  -0.6824   0.03267   0.02855  -0.0176   0.7771   0.0109
  -7.750  -0.6606   0.03121   0.02688  -0.0177   0.7657   0.0111
  -7.500  -0.6390   0.02920   0.02458  -0.0177   0.7544   0.0114
  -7.250  -0.6166   0.02692   0.02199  -0.0177   0.7430   0.0117
  -7.000  -0.5935   0.02441   0.01908  -0.0177   0.7321   0.0121
  -6.750  -0.5692   0.02203   0.01627  -0.0176   0.7219   0.0126
  -6.500  -0.5434   0.02013   0.01398  -0.0175   0.7122   0.0131
  -6.250  -0.5161   0.01897   0.01250  -0.0175   0.7039   0.0136
  -6.000  -0.4891   0.01780   0.01114  -0.0176   0.6964   0.0140
  -5.750  -0.4614   0.01707   0.01030  -0.0178   0.6900   0.0144
  -5.500  -0.4333   0.01640   0.00953  -0.0179   0.6836   0.0147
  -5.250  -0.4051   0.01576   0.00877  -0.0181   0.6774   0.0150
  -5.000  -0.3767   0.01514   0.00804  -0.0182   0.6708   0.0154
  -4.750  -0.3481   0.01455   0.00734  -0.0184   0.6636   0.0158
  -4.500  -0.3195   0.01401   0.00669  -0.0186   0.6574   0.0163
  -4.250  -0.2905   0.01359   0.00619  -0.0188   0.6519   0.0169
  -4.000  -0.2615   0.01319   0.00571  -0.0191   0.6465   0.0173
  -3.750  -0.2327   0.01260   0.00507  -0.0194   0.6411   0.0179
  -3.500  -0.2035   0.01221   0.00466  -0.0197   0.6350   0.0185
  -3.250  -0.1741   0.01190   0.00430  -0.0200   0.6296   0.0192
  -3.000  -0.1446   0.01161   0.00396  -0.0204   0.6251   0.0199
  -2.750  -0.1149   0.01134   0.00365  -0.0207   0.6202   0.0207
  -2.500  -0.0852   0.01112   0.00338  -0.0211   0.6153   0.0215
  -2.250  -0.0554   0.01087   0.00310  -0.0215   0.6105   0.0233
  -2.000  -0.0256   0.01068   0.00290  -0.0219   0.6050   0.0255
  -1.750   0.0043   0.01050   0.00270  -0.0223   0.5994   0.0284
  -1.500   0.0342   0.01037   0.00254  -0.0227   0.5945   0.0334
  -1.250   0.0642   0.01018   0.00239  -0.0231   0.5888   0.0453
  -1.000   0.0941   0.00999   0.00225  -0.0236   0.5826   0.0749
  -0.750   0.1242   0.00931   0.00210  -0.0246   0.5770   0.2343
  -0.500   0.1541   0.00832   0.00200  -0.0258   0.5706   0.5010
  -0.250   0.1837   0.00803   0.00198  -0.0263   0.5642   0.5965
   0.000   0.2129   0.00772   0.00198  -0.0266   0.5578   0.6851
   0.250   0.2414   0.00755   0.00203  -0.0266   0.5511   0.7586
   0.500   0.2694   0.00746   0.00204  -0.0265   0.5450   0.8034
   0.750   0.2968   0.00740   0.00207  -0.0262   0.5382   0.8386
   1.000   0.3245   0.00741   0.00209  -0.0259   0.5315   0.8624
   1.250   0.3517   0.00741   0.00212  -0.0256   0.5247   0.8850
   1.500   0.3787   0.00745   0.00214  -0.0253   0.5178   0.9054
   1.750   0.4069   0.00749   0.00216  -0.0253   0.5104   0.9222
   2.000   0.4351   0.00755   0.00217  -0.0253   0.5016   0.9350
   2.250   0.4627   0.00757   0.00218  -0.0252   0.4923   0.9474
   2.500   0.4908   0.00758   0.00216  -0.0251   0.4832   0.9639
   2.750   0.5234   0.00761   0.00217  -0.0262   0.4742   0.9860
   3.000   0.5546   0.00771   0.00222  -0.0270   0.4652   1.0000
   3.250   0.5849   0.00784   0.00230  -0.0277   0.4550   1.0000
   3.500   0.6151   0.00796   0.00239  -0.0283   0.4458   1.0000
   3.750   0.6452   0.00810   0.00249  -0.0289   0.4363   1.0000
   4.000   0.6753   0.00825   0.00260  -0.0296   0.4237   1.0000
   4.250   0.7052   0.00842   0.00272  -0.0302   0.4105   1.0000
   4.500   0.7351   0.00859   0.00286  -0.0308   0.3987   1.0000
   4.750   0.7648   0.00879   0.00301  -0.0315   0.3877   1.0000
   5.000   0.7945   0.00899   0.00318  -0.0321   0.3785   1.0000
   5.250   0.8241   0.00916   0.00336  -0.0326   0.3698   1.0000
   5.500   0.8535   0.00938   0.00355  -0.0332   0.3591   1.0000
   5.750   0.8828   0.00962   0.00375  -0.0338   0.3428   1.0000
   6.000   0.9120   0.00987   0.00398  -0.0344   0.3273   1.0000
   6.250   0.9410   0.01014   0.00421  -0.0350   0.3128   1.0000
   6.500   0.9697   0.01046   0.00448  -0.0356   0.2934   1.0000
   6.750   0.9980   0.01088   0.00481  -0.0362   0.2700   1.0000
   7.000   1.0256   0.01141   0.00520  -0.0368   0.2397   1.0000
   7.250   1.0518   0.01223   0.00577  -0.0375   0.1933   1.0000
   7.500   1.0779   0.01294   0.00633  -0.0380   0.1651   1.0000
   7.750   1.1037   0.01362   0.00688  -0.0384   0.1363   1.0000
   8.000   1.1295   0.01421   0.00739  -0.0388   0.1182   1.0000
   8.250   1.1543   0.01491   0.00798  -0.0391   0.0962   1.0000
   8.500   1.1788   0.01558   0.00859  -0.0393   0.0812   1.0000
   8.750   1.2031   0.01621   0.00919  -0.0394   0.0711   1.0000
   9.000   1.2269   0.01686   0.00982  -0.0395   0.0629   1.0000
   9.250   1.2506   0.01744   0.01043  -0.0396   0.0572   1.0000
   9.500   1.2729   0.01815   0.01113  -0.0395   0.0514   1.0000
   9.750   1.2960   0.01871   0.01175  -0.0395   0.0470   1.0000
  10.000   1.3167   0.01947   0.01250  -0.0393   0.0411   1.0000
  10.250   1.3365   0.02025   0.01331  -0.0390   0.0359   1.0000
  10.500   1.3548   0.02113   0.01420  -0.0386   0.0319   1.0000
  10.750   1.3708   0.02213   0.01522  -0.0382   0.0287   1.0000
  11.000   1.3827   0.02318   0.01633  -0.0371   0.0266   1.0000
  11.250   1.3945   0.02429   0.01751  -0.0361   0.0249   1.0000
  11.500   1.4050   0.02560   0.01887  -0.0353   0.0234   1.0000
  11.750   1.4136   0.02716   0.02048  -0.0345   0.0220   1.0000
  12.000   1.4241   0.02860   0.02201  -0.0340   0.0212   1.0000
  12.250   1.4338   0.03019   0.02368  -0.0336   0.0203   1.0000
  12.500   1.4421   0.03195   0.02552  -0.0333   0.0194   1.0000
  12.750   1.4488   0.03394   0.02758  -0.0330   0.0187   1.0000
  13.000   1.4534   0.03619   0.02990  -0.0328   0.0180   1.0000
  13.250   1.4563   0.03868   0.03248  -0.0328   0.0173   1.0000
  13.500   1.4618   0.04090   0.03480  -0.0327   0.0169   1.0000
  13.750   1.4659   0.04329   0.03730  -0.0327   0.0164   1.0000
  14.000   1.4687   0.04586   0.03996  -0.0328   0.0159   1.0000
  14.250   1.4702   0.04858   0.04278  -0.0329   0.0154   1.0000
  14.500   1.4702   0.05152   0.04581  -0.0331   0.0150   1.0000
  14.750   1.4688   0.05469   0.04907  -0.0334   0.0146   1.0000
  15.000   1.4659   0.05813   0.05259  -0.0339   0.0142   1.0000
  15.250   1.4610   0.06194   0.05650  -0.0346   0.0139   1.0000
  15.500   1.4574   0.06567   0.06033  -0.0353   0.0136   1.0000
  15.750   1.4557   0.06920   0.06397  -0.0360   0.0133   1.0000
  16.000   1.4533   0.07293   0.06783  -0.0369   0.0130   1.0000
  16.250   1.4501   0.07683   0.07184  -0.0379   0.0126   1.0000
  16.500   1.4461   0.08088   0.07600  -0.0390   0.0123   1.0000
  16.750   1.4416   0.08508   0.08030  -0.0403   0.0120   1.0000
  17.000   1.4361   0.08952   0.08484  -0.0416   0.0117   1.0000
  17.250   1.4295   0.09417   0.08959  -0.0432   0.0114   1.0000
  17.500   1.4218   0.09904   0.09456  -0.0448   0.0112   1.0000
  17.750   1.4129   0.10420   0.09981  -0.0467   0.0110   1.0000
  18.000   1.4027   0.10965   0.10536  -0.0488   0.0108   1.0000
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