FLYING WING GEOMETRY & TEST CONDITIONS


NAL Geometric Details:

  1 .  Mean Aerodynamic Chord (MAC)   =  279.884 mm.
  2 .  Span                                                 =  705.32 mm.
  3 .  Half Model Reference Area (S)      =  (0.174/2) = 0.087m2.

  4 .  Moment Reference Point (X, Y, Z)  =  [0, 0, 0] {Nose of the model}.
  5 .  Moment Reference Arm                  =  499 mm.

 NAL Geometry :

  1 . NAL Pressure Model  in IGES format.

         NAL_Pressure_Model.igs.gz

  2 . NAL Pressure Model with sting in IGES format.

         NAL_Pressure_Model_with_Sting.igs.gz

  3 . NAL Force Model-1 in IGES format.

         NAL_Force_Model1.igs.gz

  4 . NAL Force Model-2 in IGES format. 

         NAL_Force_Model2.igs.gz

  5 . NAL Tunnel Wall Model in IGES format.

         NAL_Tunnel_Wall_Model.igs.gz

  
NAL Test Conditions:

  1 .  Mach Number           =  0.12957~ 0.13 @ T  =  300K.
  2 .  Reynolds Number      =  1432079 ~ 1.4x10^6 (Based on Root Chord of 499mm).
  3 .  Free stream velocity  =  45 m/s.
  4 .  Kinematic viscosity    = 1.568 x 10-5 m2/s.

The NAL Wind Tunnel Test Matrix can be downloaded from the link given below.

NAL_WindTunnel_Test_Matrix.pdf

The Figure below gives the Pressure Port locations for the NAL Pressure Model.

 

IIT-Kanpur Geometry Details :

  1 . Scale                                             =  1:12
  2 . Mean Aerodynamic Chord (MAC)   =  502.386 mm
  3 . Span                                                 =  1175.518 mm
  4 . Model Reference Area (S)              =  0.486 m2
  5 . Moment Reference Point (X, Y, Z)  =  [0, 0, 0] {Nose of the model}
  6 . Moment Reference Arm                  =  831.805 mm

IIT-Kanpur Geometry :

  1 . IIT-Kanpur Model in IGES format.

        IIT_Kanpur_Pressure_Model.igs.gz


IIT-Kanpur Test Conditions :

     To be specified.