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BOEING-VERTOL VR-12 AIRFOIL (vr12-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: BOEING-VERTOL VR-12 AIRFOIL (vr12-il)
Reynolds number: 50,000
Max Cl/Cd: 28.89 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-vr12-il-50000-n5.txt
Download as CSV file: xf-vr12-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: BOEING-VERTOL VR-12 AIRFOIL                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.4804   0.13327   0.12623   0.0001   1.0000   0.1082
 -10.750  -0.4830   0.13031   0.12332  -0.0026   1.0000   0.1129
 -10.500  -0.4978   0.12806   0.12117  -0.0079   1.0000   0.1148
 -10.250  -0.4856   0.12286   0.11602  -0.0075   1.0000   0.1165
 -10.000  -0.4714   0.11858   0.11172  -0.0067   1.0000   0.1192
  -9.750  -0.4658   0.11486   0.10804  -0.0077   1.0000   0.1218
  -9.500  -0.4638   0.11117   0.10439  -0.0094   1.0000   0.1243
  -9.250  -0.3884   0.09214   0.08572  -0.0306   1.0000   0.0712
  -9.000  -0.3817   0.08806   0.08167  -0.0302   1.0000   0.0704
  -8.750  -0.3796   0.08385   0.07750  -0.0307   1.0000   0.0692
  -8.500  -0.5012   0.08467   0.07789  -0.0325   1.0000   0.0586
  -8.250  -0.5005   0.08063   0.07385  -0.0330   1.0000   0.0583
  -8.000  -0.5022   0.07662   0.06979  -0.0334   1.0000   0.0581
  -7.750  -0.5044   0.07269   0.06578  -0.0334   1.0000   0.0580
  -7.500  -0.5060   0.06895   0.06195  -0.0328   1.0000   0.0578
  -7.250  -0.5071   0.06544   0.05833  -0.0315   1.0000   0.0576
  -7.000  -0.5083   0.06219   0.05497  -0.0295   1.0000   0.0573
  -6.750  -0.5096   0.05912   0.05173  -0.0271   1.0000   0.0568
  -6.500  -0.5102   0.05614   0.04856  -0.0244   1.0000   0.0565
  -6.250  -0.5098   0.05325   0.04542  -0.0215   1.0000   0.0565
  -6.000  -0.5082   0.05045   0.04226  -0.0185   1.0000   0.0572
  -5.750  -0.5047   0.04780   0.03912  -0.0154   1.0000   0.0582
  -5.500  -0.4977   0.04526   0.03620  -0.0126   1.0000   0.0590
  -5.250  -0.4874   0.04271   0.03341  -0.0104   1.0000   0.0596
  -5.000  -0.4749   0.04042   0.03085  -0.0083   1.0000   0.0601
  -4.750  -0.4606   0.03851   0.02876  -0.0065   1.0000   0.0616
  -4.500  -0.4450   0.03689   0.02690  -0.0048   1.0000   0.0641
  -4.250  -0.4276   0.03520   0.02488  -0.0032   1.0000   0.0663
  -4.000  -0.4080   0.03351   0.02283  -0.0017   1.0000   0.0676
  -3.750  -0.3871   0.03205   0.02100  -0.0003   1.0000   0.0693
  -3.500  -0.3551   0.03058   0.01922  -0.0012   0.9962   0.0728
  -3.250  -0.3208   0.02927   0.01780  -0.0025   0.9918   0.0761
  -3.000  -0.2853   0.02817   0.01654  -0.0038   0.9872   0.0793
  -2.750  -0.2480   0.02741   0.01552  -0.0054   0.9829   0.0850
  -2.500  -0.2130   0.02652   0.01464  -0.0069   0.9781   0.0906
  -2.250  -0.1760   0.02588   0.01385  -0.0087   0.9733   0.0969
  -2.000  -0.1436   0.02530   0.01324  -0.0098   0.9676   0.1070
  -1.750  -0.1101   0.02474   0.01270  -0.0112   0.9616   0.1259
  -1.500   0.0038   0.02150   0.01279  -0.0258   0.9747   1.0000
  -1.250   0.0404   0.02168   0.01258  -0.0280   0.9661   1.0000
  -1.000   0.0820   0.02186   0.01246  -0.0311   0.9578   1.0000
  -0.750   0.1213   0.02201   0.01238  -0.0337   0.9469   1.0000
  -0.500   0.1707   0.02204   0.01219  -0.0379   0.9330   1.0000
  -0.250   0.2259   0.02183   0.01180  -0.0426   0.9139   1.0000
   0.000   0.2649   0.02161   0.01144  -0.0440   0.8915   1.0000
   0.250   0.2991   0.02143   0.01115  -0.0445   0.8730   1.0000
   0.500   0.3278   0.02133   0.01097  -0.0440   0.8564   1.0000
   0.750   0.3549   0.02121   0.01079  -0.0432   0.8392   1.0000
   1.000   0.3807   0.02106   0.01058  -0.0420   0.8213   1.0000
   1.250   0.4025   0.02097   0.01044  -0.0402   0.8005   1.0000
   1.500   0.4262   0.02079   0.01022  -0.0384   0.7794   1.0000
   1.750   0.4488   0.02062   0.01001  -0.0365   0.7560   1.0000
   2.000   0.4707   0.02047   0.00981  -0.0344   0.7290   1.0000
   2.250   0.4912   0.02037   0.00966  -0.0321   0.6959   1.0000
   2.500   0.5115   0.02028   0.00952  -0.0299   0.6552   1.0000
   2.750   0.5325   0.02020   0.00928  -0.0275   0.6034   1.0000
   3.000   0.5537   0.02022   0.00894  -0.0251   0.5404   1.0000
   3.250   0.5729   0.02060   0.00883  -0.0227   0.4800   1.0000
   3.500   0.5917   0.02123   0.00904  -0.0209   0.4334   1.0000
   3.750   0.6111   0.02191   0.00945  -0.0194   0.3982   1.0000
   4.250   0.6516   0.02328   0.01038  -0.0169   0.3522   1.0000
   4.500   0.6729   0.02396   0.01092  -0.0158   0.3350   1.0000
   4.750   0.6948   0.02462   0.01150  -0.0148   0.3207   1.0000
   5.000   0.7173   0.02530   0.01208  -0.0140   0.3081   1.0000
   5.250   0.7402   0.02597   0.01269  -0.0132   0.2965   1.0000
   5.500   0.7636   0.02665   0.01341  -0.0125   0.2859   1.0000
   5.750   0.7873   0.02737   0.01407  -0.0118   0.2773   1.0000
   6.000   0.8105   0.02809   0.01486  -0.0111   0.2682   1.0000
   6.250   0.8340   0.02887   0.01562  -0.0104   0.2603   1.0000
   6.500   0.8569   0.02966   0.01652  -0.0097   0.2526   1.0000
   6.750   0.8810   0.03053   0.01736  -0.0092   0.2469   1.0000
   7.000   0.9032   0.03148   0.01852  -0.0085   0.2404   1.0000
   7.250   0.9262   0.03239   0.01947  -0.0078   0.2348   1.0000
   7.500   0.9476   0.03343   0.02065  -0.0070   0.2289   1.0000
   7.750   0.9681   0.03448   0.02187  -0.0062   0.2229   1.0000
   8.000   0.9907   0.03549   0.02290  -0.0056   0.2184   1.0000
   8.250   1.0100   0.03686   0.02454  -0.0046   0.2140   1.0000
   8.500   1.0280   0.03823   0.02619  -0.0036   0.2090   1.0000
   8.750   1.0484   0.03936   0.02739  -0.0028   0.2044   1.0000
   9.000   1.0657   0.04077   0.02897  -0.0018   0.1998   1.0000
   9.250   1.0784   0.04249   0.03107  -0.0003   0.1948   1.0000
   9.500   1.0954   0.04380   0.03253   0.0008   0.1902   1.0000
   9.750   1.1120   0.04512   0.03394   0.0019   0.1856   1.0000
  10.000   1.1164   0.04719   0.03642   0.0039   0.1800   1.0000
  10.250   1.1305   0.04846   0.03782   0.0052   0.1752   1.0000
  10.500   1.1432   0.04991   0.03941   0.0065   0.1708   1.0000
  10.750   1.1373   0.05270   0.04262   0.0091   0.1662   1.0000
  11.000   1.1414   0.05461   0.04473   0.0109   0.1619   1.0000
  11.250   1.1652   0.05508   0.04511   0.0115   0.1577   1.0000
  11.500   1.1366   0.05932   0.04982   0.0149   0.1548   1.0000
  11.750   1.1039   0.06367   0.05444   0.0180   0.1527   1.0000
  12.000   1.0623   0.06971   0.06069   0.0189   0.1511   1.0000
  12.250   0.9522   0.08754   0.07862   0.0111   0.1513   1.0000
  12.500   0.9027   0.10109   0.09216   0.0035   0.1471   1.0000
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