- an external flow around NACA64-618 aerofoil. The flow conditions are available in following Table. Using flow aerodynamics knowledge and Consider the flow case above law of the wall': (1) Determine the flow status, such as laminar or turbulent flow, compressible or incompressible flow. (2) Choose the right boundary layer thickness calculation formula; and estimate its value to be used in meshing procedure. (3) For a structured/hybrid mesh generation for the case, the accurate wall distance and inflation layer information based on a user determined y+ value are required. Please follow the guidance from ME7724 lectures or general CFD theory to obtain this information for meshing procedure (all formula and calculation details should be included); explain your choice of the y+ value in terms of the boundary layer flow physics; Demonstrate that inflation layers properly reflect the physical viscous layer. Airfoil le (m) Uo (m/s) To (K); po (kg/m³); p∞ (Pa); µ (kg/ms) #3 a, 1 NACA64-618 0.6 45.03 317.6; 1.018; 92810; 1.9234E-5

Elements Of Electromagnetics
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Consider the flow case
an external flow around NACA64-618 aerofoil. The flow
conditions are available in following Table. Using flow aerodynamics knowledge and
above 'law of the wall':
(1) Determine the flow status, such as laminar or turbulent flow, compressible or
incompressible flow.
(2) Choose the right boundary layer thickness calculation formula; and estimate its
value to be used in meshing procedure.
(3) For a structured/hybrid mesh generation for the case, the accurate wall distance
and inflation layer information based on a user determined y+ value are required.
Please follow the guidance from ME7724 lectures or general CFD theory to obtain
this information for meshing procedure (all formula and calculation details should
be included); explain your choice of the y+ value in terms of the boundary layer
flow physics; Demonstrate that inflation layers properly reflect the physical
viscous layer.
#3
Airfoil
le (m)
Uo (m/s)
Too (K); Po (kg/m³); pœ∞ (Pa); µ (kg/ms)
a.°
1
NACA64-618
0.6
45.03
317.6; 1.018; 92810; 1.9234E-5
Transcribed Image Text:Consider the flow case an external flow around NACA64-618 aerofoil. The flow conditions are available in following Table. Using flow aerodynamics knowledge and above 'law of the wall': (1) Determine the flow status, such as laminar or turbulent flow, compressible or incompressible flow. (2) Choose the right boundary layer thickness calculation formula; and estimate its value to be used in meshing procedure. (3) For a structured/hybrid mesh generation for the case, the accurate wall distance and inflation layer information based on a user determined y+ value are required. Please follow the guidance from ME7724 lectures or general CFD theory to obtain this information for meshing procedure (all formula and calculation details should be included); explain your choice of the y+ value in terms of the boundary layer flow physics; Demonstrate that inflation layers properly reflect the physical viscous layer. #3 Airfoil le (m) Uo (m/s) Too (K); Po (kg/m³); pœ∞ (Pa); µ (kg/ms) a.° 1 NACA64-618 0.6 45.03 317.6; 1.018; 92810; 1.9234E-5
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