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BOEING-VERTOL VR-5 AIRFOIL (vr5-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: BOEING-VERTOL VR-5 AIRFOIL (vr5-il)
Reynolds number: 500,000
Max Cl/Cd: 112.83 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-vr5-il-500000.txt
Download as CSV file: xf-vr5-il-500000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4694   0.08832   0.08602  -0.0164   0.8513   0.0209
  -8.750  -0.4772   0.08124   0.07893  -0.0218   0.8429   0.0211
  -8.500  -0.4786   0.07613   0.07379  -0.0268   0.8332   0.0213
  -8.250  -0.4768   0.07204   0.06962  -0.0300   0.8251   0.0215
  -8.000  -0.4708   0.06824   0.06575  -0.0326   0.8161   0.0217
  -7.750  -0.4631   0.06453   0.06195  -0.0350   0.8082   0.0220
  -7.500  -0.4530   0.06097   0.05829  -0.0372   0.7997   0.0224
  -7.250  -0.4412   0.05720   0.05439  -0.0394   0.7917   0.0232
  -7.000  -0.4275   0.05289   0.04987  -0.0415   0.7839   0.0244
  -6.750  -0.4065   0.04684   0.04327  -0.0435   0.7767   0.0262
  -6.500  -0.3903   0.04252   0.03859  -0.0440   0.7692   0.0263
  -6.000  -0.3639   0.02593   0.02081  -0.0441   0.7561   0.0208
  -5.750  -0.3416   0.02209   0.01638  -0.0438   0.7493   0.0211
  -5.500  -0.3168   0.02051   0.01470  -0.0440   0.7415   0.0221
  -5.250  -0.2899   0.02020   0.01434  -0.0442   0.7346   0.0232
  -5.000  -0.2631   0.01826   0.01206  -0.0439   0.7273   0.0240
  -4.500  -0.2074   0.01626   0.00953  -0.0436   0.7139   0.0262
  -4.250  -0.1813   0.01461   0.00778  -0.0435   0.7076   0.0281
  -4.000  -0.1532   0.01434   0.00747  -0.0437   0.7008   0.0302
  -3.750  -0.1249   0.01395   0.00696  -0.0437   0.6941   0.0323
  -3.500  -0.0979   0.01293   0.00583  -0.0435   0.6882   0.0343
  -3.250  -0.0700   0.01245   0.00536  -0.0437   0.6819   0.0368
  -3.000  -0.0420   0.01218   0.00503  -0.0438   0.6763   0.0394
  -2.750  -0.0135   0.01190   0.00469  -0.0439   0.6705   0.0412
  -2.500   0.0139   0.01123   0.00398  -0.0439   0.6647   0.0437
  -2.250   0.0417   0.01088   0.00356  -0.0440   0.6598   0.0461
  -2.000   0.0704   0.01061   0.00329  -0.0442   0.6545   0.0489
  -1.750   0.0991   0.01039   0.00303  -0.0444   0.6493   0.0513
  -1.500   0.1276   0.01019   0.00274  -0.0446   0.6447   0.0537
  -1.250   0.1564   0.00993   0.00250  -0.0448   0.6396   0.0600
  -1.000   0.1853   0.00972   0.00233  -0.0451   0.6345   0.0751
  -0.750   0.2090   0.00782   0.00209  -0.0457   0.6302   0.5980
  -0.500   0.2357   0.00756   0.00215  -0.0454   0.6260   0.7005
  -0.250   0.2632   0.00747   0.00219  -0.0452   0.6216   0.7480
   0.000   0.2907   0.00745   0.00222  -0.0450   0.6176   0.7846
   0.500   0.3449   0.00741   0.00228  -0.0443   0.6092   0.8380
   0.750   0.3709   0.00739   0.00233  -0.0437   0.6045   0.8660
   1.000   0.3947   0.00741   0.00238  -0.0425   0.6003   0.8968
   1.250   0.4196   0.00742   0.00242  -0.0417   0.5961   0.9169
   1.500   0.4455   0.00740   0.00243  -0.0411   0.5914   0.9334
   1.750   0.4723   0.00740   0.00240  -0.0408   0.5869   0.9493
   2.000   0.5027   0.00744   0.00241  -0.0413   0.5829   0.9656
   2.250   0.5390   0.00745   0.00244  -0.0432   0.5787   0.9806
   2.500   0.5775   0.00749   0.00247  -0.0456   0.5743   0.9969
   2.750   0.6074   0.00759   0.00251  -0.0463   0.5704   1.0000
   3.000   0.6361   0.00768   0.00260  -0.0467   0.5661   1.0000
   3.250   0.6651   0.00775   0.00268  -0.0472   0.5614   1.0000
   3.500   0.6939   0.00785   0.00275  -0.0476   0.5570   1.0000
   3.750   0.7226   0.00797   0.00285  -0.0479   0.5520   1.0000
   4.000   0.7515   0.00804   0.00296  -0.0483   0.5459   1.0000
   4.250   0.7800   0.00815   0.00304  -0.0486   0.5404   1.0000
   4.500   0.8087   0.00824   0.00316  -0.0490   0.5340   1.0000
   4.750   0.8373   0.00832   0.00327  -0.0493   0.5272   1.0000
   5.000   0.8657   0.00844   0.00340  -0.0496   0.5208   1.0000
   5.250   0.8942   0.00851   0.00350  -0.0499   0.5119   1.0000
   5.500   0.9226   0.00859   0.00362  -0.0502   0.5016   1.0000
   5.750   0.9507   0.00867   0.00371  -0.0504   0.4876   1.0000
   6.000   0.9787   0.00878   0.00383  -0.0507   0.4721   1.0000
   6.250   1.0064   0.00892   0.00399  -0.0509   0.4536   1.0000
   6.500   1.0332   0.00919   0.00417  -0.0511   0.4231   1.0000
   6.750   1.0577   0.00975   0.00451  -0.0510   0.3770   1.0000
   7.000   1.0810   0.01049   0.00501  -0.0510   0.3234   1.0000
   7.250   1.1024   0.01144   0.00567  -0.0508   0.2703   1.0000
   7.500   1.1247   0.01224   0.00630  -0.0506   0.2334   1.0000
   7.750   1.1457   0.01314   0.00696  -0.0503   0.1849   1.0000
   8.000   1.1609   0.01460   0.00800  -0.0495   0.1194   1.0000
   8.250   1.1792   0.01563   0.00887  -0.0489   0.0857   1.0000
   8.500   1.1974   0.01659   0.00970  -0.0483   0.0651   1.0000
   8.750   1.2158   0.01746   0.01054  -0.0476   0.0516   1.0000
   9.000   1.2325   0.01841   0.01144  -0.0468   0.0406   1.0000
   9.250   1.2474   0.01945   0.01247  -0.0458   0.0329   1.0000
   9.500   1.2566   0.02074   0.01377  -0.0443   0.0285   1.0000
   9.750   1.2696   0.02180   0.01490  -0.0433   0.0261   1.0000
  10.000   1.2793   0.02317   0.01630  -0.0422   0.0243   1.0000
  10.250   1.2820   0.02517   0.01837  -0.0407   0.0228   1.0000
  10.500   1.2934   0.02648   0.01978  -0.0399   0.0221   1.0000
  10.750   1.3026   0.02802   0.02141  -0.0391   0.0213   1.0000
  11.000   1.3112   0.02965   0.02311  -0.0383   0.0205   1.0000
  11.250   1.3191   0.03136   0.02489  -0.0376   0.0198   1.0000
  11.500   1.3258   0.03322   0.02681  -0.0370   0.0191   1.0000
  11.750   1.3280   0.03552   0.02917  -0.0361   0.0185   1.0000
  12.000   1.3256   0.03827   0.03200  -0.0351   0.0180   1.0000
  12.250   1.3277   0.04059   0.03441  -0.0342   0.0177   1.0000
  12.500   1.3340   0.04257   0.03649  -0.0336   0.0174   1.0000
  12.750   1.3392   0.04463   0.03865  -0.0329   0.0171   1.0000
  13.000   1.3438   0.04678   0.04089  -0.0323   0.0168   1.0000
  13.250   1.3480   0.04898   0.04318  -0.0317   0.0165   1.0000
  13.500   1.3520   0.05121   0.04550  -0.0311   0.0162   1.0000
  13.750   1.3564   0.05349   0.04787  -0.0307   0.0158   1.0000
  14.000   1.3604   0.05586   0.05032  -0.0304   0.0154   1.0000
  14.250   1.3641   0.05832   0.05286  -0.0303   0.0151   1.0000
  14.500   1.3670   0.06086   0.05546  -0.0301   0.0148   1.0000
  14.750   1.3690   0.06351   0.05820  -0.0299   0.0145   1.0000
  15.000   1.3700   0.06623   0.06100  -0.0294   0.0142   1.0000
  15.250   1.3690   0.06909   0.06396  -0.0282   0.0139   1.0000
  15.500   1.3668   0.07239   0.06742  -0.0277   0.0137   1.0000
  15.750   1.3652   0.07585   0.07104  -0.0282   0.0136   1.0000
  16.000   1.3623   0.07956   0.07491  -0.0288   0.0135   1.0000
  16.250   1.3580   0.08353   0.07904  -0.0297   0.0134   1.0000
  16.500   1.3523   0.08782   0.08349  -0.0307   0.0132   1.0000
  16.750   1.3453   0.09244   0.08828  -0.0321   0.0131   1.0000
  17.000   1.3370   0.09736   0.09337  -0.0337   0.0129   1.0000
  17.250   1.3275   0.10259   0.09876  -0.0356   0.0128   1.0000
  17.500   1.3168   0.10820   0.10454  -0.0379   0.0126   1.0000
  17.750   1.3053   0.11416   0.11065  -0.0405   0.0125   1.0000
  18.000   1.2918   0.12067   0.11734  -0.0436   0.0124   1.0000
  18.250   1.2773   0.12760   0.12444  -0.0472   0.0124   1.0000
  18.500   1.2612   0.13517   0.13218  -0.0513   0.0123   1.0000
  18.750   1.2414   0.14391   0.14112  -0.0564   0.0123   1.0000
  19.000   1.2183   0.15402   0.15142  -0.0626   0.0124   1.0000
  19.250   1.1884   0.16661   0.16423  -0.0707   0.0126   1.0000
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