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BOEING-VERTOL VR-5 AIRFOIL (vr5-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: BOEING-VERTOL VR-5 AIRFOIL (vr5-il)
Reynolds number: 500,000
Max Cl/Cd: 105.11 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-vr5-il-500000-n5.txt
Download as CSV file: xf-vr5-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: BOEING-VERTOL VR-5 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.5034   0.08626   0.08365  -0.0091   0.7846   0.0093
  -9.000  -0.5141   0.07846   0.07584  -0.0153   0.7762   0.0095
  -8.750  -0.5278   0.06894   0.06627  -0.0274   0.7664   0.0096
  -8.500  -0.5453   0.05694   0.05402  -0.0368   0.7587   0.0098
  -8.000  -0.5309   0.04606   0.04265  -0.0415   0.7425   0.0101
  -7.750  -0.5564   0.02179   0.01644  -0.0428   0.7392   0.0114
  -7.500  -0.5338   0.01935   0.01354  -0.0426   0.7317   0.0118
  -7.250  -0.5089   0.01785   0.01169  -0.0424   0.7238   0.0123
  -7.000  -0.4827   0.01700   0.01067  -0.0424   0.7167   0.0128
  -6.750  -0.4555   0.01660   0.01019  -0.0425   0.7097   0.0132
  -6.500  -0.4283   0.01611   0.00959  -0.0425   0.7035   0.0136
  -6.250  -0.4012   0.01548   0.00884  -0.0426   0.6974   0.0141
  -6.000  -0.3741   0.01482   0.00802  -0.0425   0.6914   0.0148
  -5.750  -0.3470   0.01416   0.00720  -0.0425   0.6859   0.0155
  -5.500  -0.3195   0.01365   0.00662  -0.0426   0.6800   0.0162
  -5.250  -0.2916   0.01340   0.00631  -0.0427   0.6742   0.0169
  -5.000  -0.2636   0.01310   0.00595  -0.0428   0.6685   0.0180
  -4.750  -0.2356   0.01278   0.00554  -0.0428   0.6624   0.0195
  -4.250  -0.1793   0.01229   0.00498  -0.0432   0.6517   0.0221
  -4.000  -0.1511   0.01203   0.00466  -0.0433   0.6461   0.0237
  -3.750  -0.1227   0.01184   0.00436  -0.0434   0.6411   0.0247
  -3.500  -0.0948   0.01143   0.00396  -0.0436   0.6358   0.0263
  -3.250  -0.0664   0.01124   0.00374  -0.0438   0.6301   0.0277
  -3.000  -0.0378   0.01110   0.00356  -0.0440   0.6250   0.0297
  -2.750  -0.0091   0.01099   0.00341  -0.0442   0.6195   0.0312
  -2.500   0.0191   0.01063   0.00302  -0.0444   0.6146   0.0331
  -2.250   0.0476   0.01043   0.00277  -0.0446   0.6101   0.0344
  -2.000   0.0763   0.01025   0.00257  -0.0448   0.6051   0.0358
  -1.750   0.1051   0.01010   0.00239  -0.0451   0.6001   0.0374
  -1.250   0.1627   0.00986   0.00207  -0.0456   0.5912   0.0423
  -1.000   0.1916   0.00974   0.00195  -0.0458   0.5860   0.0469
  -0.500   0.2490   0.00941   0.00178  -0.0464   0.5768   0.1108
  -0.250   0.2763   0.00854   0.00165  -0.0471   0.5728   0.3745
   0.000   0.3025   0.00776   0.00165  -0.0473   0.5694   0.6211
   0.250   0.3304   0.00766   0.00167  -0.0473   0.5657   0.6762
   0.500   0.3585   0.00757   0.00172  -0.0474   0.5611   0.7151
   0.750   0.3861   0.00753   0.00177  -0.0473   0.5557   0.7587
   1.000   0.4129   0.00750   0.00183  -0.0469   0.5511   0.8003
   1.250   0.4409   0.00749   0.00188  -0.0469   0.5472   0.8207
   1.500   0.4690   0.00750   0.00192  -0.0470   0.5434   0.8332
   1.750   0.4970   0.00753   0.00197  -0.0470   0.5398   0.8451
   2.000   0.5248   0.00758   0.00203  -0.0470   0.5361   0.8579
   2.250   0.5524   0.00761   0.00209  -0.0469   0.5322   0.8727
   2.500   0.5797   0.00763   0.00217  -0.0467   0.5279   0.8889
   2.750   0.6067   0.00768   0.00224  -0.0466   0.5236   0.9058
   3.250   0.6612   0.00776   0.00238  -0.0463   0.5158   0.9389
   3.500   0.6904   0.00779   0.00244  -0.0466   0.5102   0.9556
   3.750   0.7233   0.00787   0.00250  -0.0478   0.5038   0.9732
   4.000   0.7568   0.00791   0.00260  -0.0492   0.4978   1.0000
   4.250   0.7854   0.00802   0.00270  -0.0495   0.4911   1.0000
   4.500   0.8141   0.00811   0.00281  -0.0499   0.4822   1.0000
   4.750   0.8425   0.00824   0.00293  -0.0502   0.4717   1.0000
   5.000   0.8707   0.00838   0.00305  -0.0505   0.4570   1.0000
   5.250   0.8987   0.00855   0.00319  -0.0508   0.4396   1.0000
   5.500   0.9257   0.00885   0.00339  -0.0510   0.4097   1.0000
   5.750   0.9505   0.00946   0.00374  -0.0511   0.3597   1.0000
   6.000   0.9735   0.01034   0.00427  -0.0511   0.2930   1.0000
   6.250   0.9970   0.01109   0.00480  -0.0511   0.2528   1.0000
   6.500   1.0219   0.01161   0.00522  -0.0511   0.2277   1.0000
   6.750   1.0464   0.01216   0.00566  -0.0511   0.2001   1.0000
   7.000   1.0661   0.01325   0.00639  -0.0508   0.1363   1.0000
   7.250   1.0881   0.01402   0.00703  -0.0506   0.1097   1.0000
   7.500   1.1093   0.01480   0.00768  -0.0502   0.0818   1.0000
   7.750   1.1311   0.01548   0.00828  -0.0499   0.0659   1.0000
   8.000   1.1533   0.01607   0.00885  -0.0497   0.0561   1.0000
   8.250   1.1747   0.01670   0.00945  -0.0493   0.0471   1.0000
   8.500   1.1953   0.01736   0.01010  -0.0489   0.0389   1.0000
   8.750   1.2149   0.01807   0.01078  -0.0483   0.0326   1.0000
   9.000   1.2343   0.01875   0.01149  -0.0478   0.0284   1.0000
   9.250   1.2519   0.01951   0.01227  -0.0471   0.0249   1.0000
   9.500   1.2670   0.02033   0.01312  -0.0461   0.0221   1.0000
   9.750   1.2808   0.02130   0.01413  -0.0452   0.0200   1.0000
  10.000   1.2952   0.02226   0.01514  -0.0444   0.0185   1.0000
  10.250   1.3083   0.02335   0.01629  -0.0435   0.0173   1.0000
  10.500   1.3198   0.02460   0.01758  -0.0427   0.0163   1.0000
  10.750   1.3312   0.02589   0.01893  -0.0419   0.0156   1.0000
  11.000   1.3427   0.02719   0.02031  -0.0412   0.0150   1.0000
  11.250   1.3532   0.02860   0.02180  -0.0406   0.0145   1.0000
  11.500   1.3629   0.03012   0.02339  -0.0399   0.0140   1.0000
  11.750   1.3715   0.03178   0.02513  -0.0393   0.0136   1.0000
  12.000   1.3790   0.03356   0.02698  -0.0387   0.0133   1.0000
  12.250   1.3849   0.03553   0.02901  -0.0382   0.0130   1.0000
  12.500   1.3889   0.03770   0.03127  -0.0376   0.0126   1.0000
  12.750   1.3915   0.04004   0.03369  -0.0371   0.0124   1.0000
  13.000   1.3967   0.04215   0.03589  -0.0367   0.0122   1.0000
  13.250   1.4010   0.04437   0.03820  -0.0363   0.0119   1.0000
  13.500   1.4043   0.04671   0.04065  -0.0360   0.0117   1.0000
  13.750   1.4067   0.04919   0.04323  -0.0357   0.0115   1.0000
  14.000   1.4086   0.05179   0.04592  -0.0355   0.0113   1.0000
  14.250   1.4101   0.05452   0.04875  -0.0355   0.0111   1.0000
  14.500   1.4111   0.05736   0.05168  -0.0355   0.0109   1.0000
  14.750   1.4119   0.06028   0.05469  -0.0356   0.0107   1.0000
  15.000   1.4121   0.06330   0.05781  -0.0358   0.0105   1.0000
  15.250   1.4119   0.06645   0.06105  -0.0361   0.0103   1.0000
  15.500   1.4106   0.06982   0.06450  -0.0366   0.0102   1.0000
  15.750   1.4077   0.07341   0.06819  -0.0371   0.0100   1.0000
  16.000   1.4033   0.07726   0.07212  -0.0377   0.0098   1.0000
  16.250   1.3972   0.08141   0.07636  -0.0384   0.0096   1.0000
  16.500   1.3930   0.08538   0.08045  -0.0392   0.0095   1.0000
  16.750   1.3907   0.08918   0.08437  -0.0402   0.0094   1.0000
  17.000   1.3871   0.09322   0.08853  -0.0412   0.0093   1.0000
  17.250   1.3830   0.09742   0.09285  -0.0424   0.0092   1.0000
  17.500   1.3783   0.10177   0.09733  -0.0437   0.0090   1.0000
  17.750   1.3731   0.10628   0.10196  -0.0452   0.0089   1.0000
  18.000   1.3673   0.11091   0.10672  -0.0468   0.0088   1.0000
  18.250   1.3612   0.11571   0.11163  -0.0486   0.0087   1.0000
  18.500   1.3548   0.12064   0.11668  -0.0506   0.0086   1.0000
  18.750   1.3482   0.12569   0.12186  -0.0528   0.0085   1.0000
  19.000   1.3412   0.13090   0.12719  -0.0552   0.0084   1.0000
  19.250   1.3340   0.13622   0.13262  -0.0577   0.0082   1.0000
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