kynema::interfaces::components::AerodynamicBody Class Reference

#include <aerodynamics.hpp>

Public Member Functions
	AerodynamicBody (const AerodynamicBodyInput &input, std::span< const Node > nodes)
template<typename DeviceType >
void	CalculateMotion (const HostState< DeviceType > &state)
void	SetInflowFromVector (std::span< const std::array< double, 3 > > inflow_velocity)
template<typename T >
void	SetInflowFromFunction (const T &inflow_velocity_function)
void	SetAerodynamicLoads (std::span< const std::array< double, 6 > > aerodynamic_loads)
void	CalculateAerodynamicLoads (double fluid_density)
void	CalculateNodalLoads ()
template<typename DeviceType >
void	AddNodalLoadsToState (HostState< DeviceType > &state)

Public Attributes
size_t	id
std::vector< size_t >	node_ids
	IDs of the beam nodes in this aerodynamic body.
std::vector< std::array< double, 7 > >	node_u
	Displacements of the beam nodes (copied from state based on node_ids)
std::vector< std::array< double, 6 > >	node_v
	Velocities of the beam nodes (copied from state based on node_ids)
std::vector< std::array< double, 6 > >	node_f
	Aerodynamic forces at the beam nodes with moment arm applied from aerodynamic center to reference axis (output)
std::vector< std::array< double, 7 > >	xr_motion_map
	Initial position and orientation of beam reference axis at aerodynamic sections.
std::vector< std::array< double, 7 > >	u_motion_map
	Displacements of beam reference axis at aerodynamic sections.
std::vector< std::array< double, 6 > >	v_motion_map
	Velocities of beam reference axis at aerodynamic sections.
std::vector< std::array< double, 4 > >	qqr_motion_map
	Total rotation quaternion of beam reference axis at aerodynamic sections (reference + displacement)
std::vector< std::array< double, 3 > >	con_motion
	Vectors from reference axis to aerodynamic center at aerodynamic sections in reference configuration (includes twist)
std::vector< std::array< double, 3 > >	x_motion
	Positions of aerodynamic centers at aerodynamic sections in global coordinates.
std::vector< std::array< double, 3 > >	v_motion
	Velocities of aerodynamic centers at aerodynamic sections in global coordinates.
std::vector< std::array< double, 3 > >	con_force
	Vectors from aerodynamic center to reference axis at aerodynamic sections in reference configuration (negative of con_motion)
std::vector< std::array< double, 3 > >	v_inflow
	Inflow velocity at aerodynamic sections.
std::vector< std::array< double, 3 > >	v_rel
	Relative velocity at aerodynamic sections (v_inflow - v_motion) (output)
std::vector< double >	alpha
	Angle of attack at aerodynamic sections (output)
std::vector< double >	cn
	Normal force coefficient at aerodynamic sections (perpendicular to airfoil chord) (output)
std::vector< double >	ct
	Tangent force coefficient at aerodynamic sections (parallel to airfoil chord) (output)
std::vector< double >	cm
	Moment coefficient at aerodynamic sections (output)
std::vector< std::array< double, 6 > >	loads
	Aerodynamic loads (forces and moments) at aerodynamic centers (output)
std::vector< std::array< double, 3 > >	ref_axis_moments
	Total moment about beam reference axis at aerodynamic sections (accounting for AC moment arm and aerodynamic moment) (output)
std::vector< double >	twist
	Aerodynamic section twist.
std::vector< double >	chord
	Aerodynamic section chord length.
std::vector< double >	delta_s
	Aerodynamic section width for force/moment calculation.
std::vector< size_t >	polar_size
	Number of points in each aerodynamic polar.
std::vector< std::vector< double > >	aoa
	Angle of attack polar at each aerodynamic section.
std::vector< std::vector< double > >	cl_polar
	Lift coefficient polar at each aerodynamic section.
std::vector< std::vector< double > >	cd_polar
	Drag coefficient polar at each aerodynamic section.
std::vector< std::vector< double > >	cm_polar
	Moment coefficient polar at each aerodynamic section.
std::vector< double >	jacobian_xi
	Locations of aerodynamic section width boundaries along the beam (used for section width calculation)
std::vector< double >	motion_interp
	Flattened matrix to interpolate motion from beam nodes to aerodynamic sections.
std::vector< double >	shape_deriv_jac
	Flattened matrix to interpolate motion derivatives from beam nodes to aerodynamic sections (used for section width calculation)

Constructor & Destructor Documentation

AerodynamicBody()

kynema::interfaces::components::AerodynamicBody::AerodynamicBody	(	const AerodynamicBodyInput &	input,
		std::span< const Node >	nodes
	)

Member Function Documentation

AddNodalLoadsToState()

template<typename DeviceType >

void kynema::interfaces::components::AerodynamicBody::AddNodalLoadsToState ( HostState< DeviceType > &  state )

inline

CalculateAerodynamicLoads()

void kynema::interfaces::components::AerodynamicBody::CalculateAerodynamicLoads

(

double

fluid_density

)

CalculateMotion()

template<typename DeviceType >

void kynema::interfaces::components::AerodynamicBody::CalculateMotion ( const HostState< DeviceType > &  state )

inline

CalculateNodalLoads()

void kynema::interfaces::components::AerodynamicBody::CalculateNodalLoads

(

)

SetAerodynamicLoads()

void kynema::interfaces::components::AerodynamicBody::SetAerodynamicLoads

(

std::span< const std::array< double, 6 > >

aerodynamic_loads

)

SetInflowFromFunction()

template<typename T >

void kynema::interfaces::components::AerodynamicBody::SetInflowFromFunction ( const T &  inflow_velocity_function )

inline

SetInflowFromVector()

void kynema::interfaces::components::AerodynamicBody::SetInflowFromVector

(

std::span< const std::array< double, 3 > >

inflow_velocity

)

Member Data Documentation

alpha

std::vector<double> kynema::interfaces::components::AerodynamicBody::alpha

Angle of attack at aerodynamic sections (output)

aoa

std::vector<std::vector<double> > kynema::interfaces::components::AerodynamicBody::aoa

Angle of attack polar at each aerodynamic section.

cd_polar

std::vector<std::vector<double> > kynema::interfaces::components::AerodynamicBody::cd_polar

Drag coefficient polar at each aerodynamic section.

chord

std::vector<double> kynema::interfaces::components::AerodynamicBody::chord

Aerodynamic section chord length.

cl_polar

std::vector<std::vector<double> > kynema::interfaces::components::AerodynamicBody::cl_polar

Lift coefficient polar at each aerodynamic section.

cm

std::vector<double> kynema::interfaces::components::AerodynamicBody::cm

Moment coefficient at aerodynamic sections (output)

cm_polar

std::vector<std::vector<double> > kynema::interfaces::components::AerodynamicBody::cm_polar

Moment coefficient polar at each aerodynamic section.

cn

std::vector<double> kynema::interfaces::components::AerodynamicBody::cn

Normal force coefficient at aerodynamic sections (perpendicular to airfoil chord) (output)

con_force

std::vector<std::array<double, 3> > kynema::interfaces::components::AerodynamicBody::con_force

Vectors from aerodynamic center to reference axis at aerodynamic sections in reference configuration (negative of con_motion)

con_motion

std::vector<std::array<double, 3> > kynema::interfaces::components::AerodynamicBody::con_motion

Vectors from reference axis to aerodynamic center at aerodynamic sections in reference configuration (includes twist)

ct

std::vector<double> kynema::interfaces::components::AerodynamicBody::ct

Tangent force coefficient at aerodynamic sections (parallel to airfoil chord) (output)

delta_s

std::vector<double> kynema::interfaces::components::AerodynamicBody::delta_s

Aerodynamic section width for force/moment calculation.

id

size_t kynema::interfaces::components::AerodynamicBody::id

jacobian_xi

std::vector<double> kynema::interfaces::components::AerodynamicBody::jacobian_xi

Locations of aerodynamic section width boundaries along the beam (used for section width calculation)

loads

std::vector<std::array<double, 6> > kynema::interfaces::components::AerodynamicBody::loads

Aerodynamic loads (forces and moments) at aerodynamic centers (output)

motion_interp

std::vector<double> kynema::interfaces::components::AerodynamicBody::motion_interp

Flattened matrix to interpolate motion from beam nodes to aerodynamic sections.

node_f

std::vector<std::array<double, 6> > kynema::interfaces::components::AerodynamicBody::node_f

Aerodynamic forces at the beam nodes with moment arm applied from aerodynamic center to reference axis (output)

node_ids

std::vector<size_t> kynema::interfaces::components::AerodynamicBody::node_ids

IDs of the beam nodes in this aerodynamic body.

node_u

std::vector<std::array<double, 7> > kynema::interfaces::components::AerodynamicBody::node_u

Displacements of the beam nodes (copied from state based on node_ids)

node_v

std::vector<std::array<double, 6> > kynema::interfaces::components::AerodynamicBody::node_v

Velocities of the beam nodes (copied from state based on node_ids)

polar_size

std::vector<size_t> kynema::interfaces::components::AerodynamicBody::polar_size

Number of points in each aerodynamic polar.

qqr_motion_map

std::vector<std::array<double, 4> > kynema::interfaces::components::AerodynamicBody::qqr_motion_map

Total rotation quaternion of beam reference axis at aerodynamic sections (reference + displacement)

ref_axis_moments

std::vector<std::array<double, 3> > kynema::interfaces::components::AerodynamicBody::ref_axis_moments

Total moment about beam reference axis at aerodynamic sections (accounting for AC moment arm and aerodynamic moment) (output)

shape_deriv_jac

std::vector<double> kynema::interfaces::components::AerodynamicBody::shape_deriv_jac

Flattened matrix to interpolate motion derivatives from beam nodes to aerodynamic sections (used for section width calculation)

twist

std::vector<double> kynema::interfaces::components::AerodynamicBody::twist

Aerodynamic section twist.

u_motion_map

std::vector<std::array<double, 7> > kynema::interfaces::components::AerodynamicBody::u_motion_map

Displacements of beam reference axis at aerodynamic sections.

v_inflow

std::vector<std::array<double, 3> > kynema::interfaces::components::AerodynamicBody::v_inflow

Inflow velocity at aerodynamic sections.

v_motion

std::vector<std::array<double, 3> > kynema::interfaces::components::AerodynamicBody::v_motion

Velocities of aerodynamic centers at aerodynamic sections in global coordinates.

v_motion_map

std::vector<std::array<double, 6> > kynema::interfaces::components::AerodynamicBody::v_motion_map

Velocities of beam reference axis at aerodynamic sections.

v_rel

std::vector<std::array<double, 3> > kynema::interfaces::components::AerodynamicBody::v_rel

Relative velocity at aerodynamic sections (v_inflow - v_motion) (output)

x_motion

std::vector<std::array<double, 3> > kynema::interfaces::components::AerodynamicBody::x_motion

Positions of aerodynamic centers at aerodynamic sections in global coordinates.

xr_motion_map

std::vector<std::array<double, 7> > kynema::interfaces::components::AerodynamicBody::xr_motion_map

Initial position and orientation of beam reference axis at aerodynamic sections.

---

The documentation for this class was generated from the following files:

• /home/runner/work/kynema/kynema/kynema/src/interfaces/components/aerodynamics.hpp
• /home/runner/work/kynema/kynema/kynema/src/interfaces/components/aerodynamics.cpp