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BOEING-VERTOL VR-1 AIRFOIL (vr1-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: BOEING-VERTOL VR-1 AIRFOIL (vr1-il)
Reynolds number: 100,000
Max Cl/Cd: 44.06 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-vr1-il-100000-n5.txt
Download as CSV file: xf-vr1-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: BOEING-VERTOL VR-1 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.5818   0.07337   0.06761  -0.0543   1.0000   0.0350
 -10.250  -0.5966   0.06849   0.06268  -0.0569   1.0000   0.0349
 -10.000  -0.6134   0.06449   0.05863  -0.0578   1.0000   0.0347
  -9.750  -0.6334   0.06115   0.05521  -0.0564   1.0000   0.0345
  -9.500  -0.6503   0.05818   0.05214  -0.0540   1.0000   0.0343
  -9.250  -0.6629   0.05513   0.04895  -0.0515   1.0000   0.0342
  -9.000  -0.6738   0.05209   0.04571  -0.0486   1.0000   0.0340
  -8.750  -0.6812   0.04921   0.04261  -0.0456   1.0000   0.0338
  -8.500  -0.6864   0.04650   0.03965  -0.0423   1.0000   0.0337
  -8.250  -0.6896   0.04396   0.03684  -0.0389   1.0000   0.0337
  -8.000  -0.6911   0.04160   0.03418  -0.0354   1.0000   0.0339
  -7.750  -0.6900   0.03948   0.03172  -0.0320   1.0000   0.0343
  -7.500  -0.6864   0.03751   0.02941  -0.0288   1.0000   0.0346
  -7.250  -0.6805   0.03567   0.02720  -0.0257   1.0000   0.0349
  -7.000  -0.6549   0.03346   0.02454  -0.0263   0.9954   0.0351
  -6.750  -0.6264   0.03136   0.02219  -0.0273   0.9903   0.0353
  -6.500  -0.5962   0.02953   0.02015  -0.0285   0.9855   0.0356
  -6.250  -0.5661   0.02798   0.01843  -0.0294   0.9806   0.0360
  -6.000  -0.5358   0.02660   0.01690  -0.0303   0.9754   0.0365
  -5.750  -0.5027   0.02535   0.01554  -0.0317   0.9713   0.0371
  -5.500  -0.4738   0.02433   0.01445  -0.0322   0.9655   0.0383
  -5.250  -0.4426   0.02340   0.01341  -0.0331   0.9602   0.0399
  -5.000  -0.4087   0.02253   0.01243  -0.0345   0.9564   0.0412
  -4.750  -0.3821   0.02162   0.01155  -0.0346   0.9499   0.0423
  -4.500  -0.3521   0.02084   0.01076  -0.0354   0.9445   0.0436
  -4.250  -0.3183   0.02014   0.01002  -0.0368   0.9407   0.0453
  -4.000  -0.2924   0.01961   0.00941  -0.0366   0.9335   0.0475
  -3.750  -0.2618   0.01903   0.00879  -0.0373   0.9282   0.0513
  -3.500  -0.2279   0.01849   0.00822  -0.0386   0.9245   0.0582
  -3.000  -0.1772   0.01702   0.00730  -0.0381   0.9110   0.1526
  -2.750  -0.1542   0.01579   0.00702  -0.0379   0.9056   0.3463
  -2.500  -0.1385   0.01485   0.00709  -0.0355   0.8977   0.5493
  -2.250  -0.1103   0.01449   0.00720  -0.0347   0.8933   0.6766
  -2.000  -0.0806   0.01444   0.00732  -0.0342   0.8884   0.7493
  -1.750  -0.0525   0.01456   0.00757  -0.0330   0.8822   0.8161
  -1.500  -0.0151   0.01473   0.00774  -0.0337   0.8783   0.8618
  -1.250   0.0265   0.01480   0.00773  -0.0358   0.8751   0.8833
  -1.000   0.0607   0.01490   0.00776  -0.0368   0.8689   0.8995
  -0.750   0.0974   0.01495   0.00773  -0.0384   0.8633   0.9127
  -0.500   0.1364   0.01496   0.00766  -0.0404   0.8591   0.9256
  -0.250   0.1788   0.01502   0.00768  -0.0432   0.8540   0.9370
   0.000   0.2217   0.01506   0.00769  -0.0462   0.8482   0.9474
   0.250   0.2643   0.01505   0.00765  -0.0491   0.8434   0.9579
   0.500   0.3084   0.01501   0.00760  -0.0523   0.8383   0.9662
   0.750   0.3478   0.01502   0.00763  -0.0549   0.8311   0.9754
   1.000   0.3879   0.01496   0.00758  -0.0574   0.8255   0.9834
   1.250   0.4279   0.01493   0.00759  -0.0601   0.8179   0.9910
   1.500   0.4686   0.01476   0.00745  -0.0626   0.8088   0.9983
   1.750   0.4919   0.01463   0.00733  -0.0615   0.7938   1.0000
   2.000   0.5113   0.01448   0.00717  -0.0594   0.7769   1.0000
   2.250   0.5310   0.01431   0.00698  -0.0573   0.7583   1.0000
   2.500   0.5475   0.01420   0.00684  -0.0546   0.7338   1.0000
   2.750   0.5655   0.01404   0.00663  -0.0520   0.7043   1.0000
   3.000   0.5829   0.01398   0.00650  -0.0495   0.6724   1.0000
   3.250   0.6001   0.01399   0.00645  -0.0470   0.6375   1.0000
   3.500   0.6170   0.01408   0.00641  -0.0444   0.5915   1.0000
   3.750   0.6314   0.01433   0.00635  -0.0413   0.5110   1.0000
   4.000   0.6363   0.01525   0.00644  -0.0368   0.3668   1.0000
   4.250   0.6376   0.01668   0.00701  -0.0325   0.2251   1.0000
   4.500   0.6468   0.01772   0.00761  -0.0295   0.1589   1.0000
   4.750   0.6597   0.01850   0.00817  -0.0270   0.1307   1.0000
   5.000   0.6740   0.01919   0.00876  -0.0247   0.1141   1.0000
   5.250   0.6883   0.01991   0.00937  -0.0224   0.1025   1.0000
   5.500   0.7041   0.02053   0.01000  -0.0204   0.0928   1.0000
   5.750   0.7193   0.02126   0.01071  -0.0182   0.0857   1.0000
   6.000   0.7354   0.02194   0.01138  -0.0163   0.0791   1.0000
   6.250   0.7513   0.02273   0.01215  -0.0144   0.0742   1.0000
   6.500   0.7687   0.02350   0.01295  -0.0127   0.0701   1.0000
   6.750   0.7860   0.02431   0.01374  -0.0111   0.0666   1.0000
   7.000   0.8044   0.02523   0.01466  -0.0097   0.0633   1.0000
   7.250   0.8246   0.02610   0.01559  -0.0085   0.0602   1.0000
   7.500   0.8446   0.02703   0.01654  -0.0074   0.0577   1.0000
   7.750   0.8652   0.02809   0.01758  -0.0065   0.0558   1.0000
   8.000   0.8880   0.02939   0.01891  -0.0059   0.0542   1.0000
   8.250   0.9105   0.03063   0.02033  -0.0052   0.0523   1.0000
   8.500   0.9314   0.03184   0.02170  -0.0043   0.0504   1.0000
   8.750   0.9510   0.03301   0.02296  -0.0034   0.0487   1.0000
   9.000   0.9708   0.03435   0.02437  -0.0025   0.0475   1.0000
   9.250   0.9910   0.03594   0.02602  -0.0019   0.0466   1.0000
   9.500   1.0089   0.03789   0.02821  -0.0008   0.0459   1.0000
   9.750   1.0228   0.04000   0.03067   0.0008   0.0451   1.0000
  10.000   1.0331   0.04220   0.03322   0.0028   0.0443   1.0000
  10.250   1.0404   0.04444   0.03578   0.0049   0.0434   1.0000
  10.500   1.0454   0.04654   0.03817   0.0072   0.0424   1.0000
  10.750   1.0483   0.04864   0.04050   0.0096   0.0417   1.0000
  11.000   1.0471   0.05077   0.04284   0.0124   0.0412   1.0000
  11.250   1.0417   0.05323   0.04553   0.0153   0.0409   1.0000
  11.500   1.0340   0.05583   0.04835   0.0179   0.0407   1.0000
  11.750   1.0229   0.05876   0.05150   0.0202   0.0405   1.0000
  12.000   1.0084   0.06207   0.05503   0.0219   0.0403   1.0000
  12.250   0.9877   0.06616   0.05937   0.0229   0.0403   1.0000
  12.500   0.9590   0.07146   0.06494   0.0227   0.0404   1.0000
  12.750   0.9171   0.07924   0.07302   0.0200   0.0407   1.0000
  13.000   0.8437   0.09497   0.08906   0.0102   0.0416   1.0000
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