sc_aero.h File Reference

Aerodynamic functions. More...

Go to the source code of this file.

Classes
struct	aero_angles_s
	Structure for storing orbit data. More...
struct	low_speed_aero_s
	Structure for storing the low speed aero data. More...
struct	suborb_aero_s
	Structure for storing the suborb aero data. More...

Typedefs
typedef struct aero_angles_s	aero_angles_t
	Structure for storing orbit data.
typedef struct low_speed_aero_s	low_speed_aero_t
	Structure for storing the low speed aero data.
typedef struct suborb_aero_s	suborb_aero_t
	Structure for storing the suborb aero data.

Functions
ml_matrix	low_speed_lift_and_drag (double angle, low_speed_aero_t d, const ml_matrix &v, double rho, const ml_matrix &c, double speedOfSound, double kinematicViscosity)
	Low speed lift and drag torque. More...
ml_matrix	suborb_lift_and_drag (double angle, suborb_aero_t d, const ml_matrix &v, double rho, const ml_matrix &c, double speedOfSound)
	suborb lift and drag torque
ml_matrix	simple_lift_and_drag (double v, double k, double cD0, double cLAlpha, double s, double density, double alpha)
	Simple lift and drag coefficients. More...
ml_matrix	lift_and_drag (double v, double rho, double kinematicViscosity, double speedOfSound, double length, double s, double oswaldEff, double aspectRatio, double zetaTrans, double thickness)
	Mach dependent lift and drag. More...
aero_angles_t	alpha_and_beta (const ml_matrix &v_body, const ml_matrix &v_body_dot)
	Compute the angle of attack and sideslip. More...
aero_angles_t	alpha_and_beta (const ml_matrix &v_body)
	Compute the angle of attack and sideslip. More...
ml_matrix	lift_vector (const ml_matrix &v_body)
	Lift vector. More...
ml_matrix	body_to_wind (double alpha, double beta)
	Body to wind axes. More...
double	local_angle_of_attack (double alpha, const ml_matrix &aB, double delta)
	Body to wind axes. More...
double	rankine_hugoniot_factor (double gamma, double m, double p_inf)
	Pressure modification for Newtonian. More...

Function Documentation

low_speed_lift_and_drag()

ml_matrix low_speed_lift_and_drag	(	double	angle,
		low_speed_aero_t	d,
		const ml_matrix &	v,
		double	rho,
		const ml_matrix &	c,
		double	speedOfSound,
		double	kinematicViscosity
	)

Low speed lift and drag torque.

Good above Mach 4.

Parameters

angle	Hinge angle
d	Low speed aero data structure
v	Velocity vector in the body frame (3x1)
rho	Atmospheric density
c	Center of mass
cP	Aerodynamic center
speedOfSound	Speed of sound
kinematicViscosity	Kinematic viscosity

Returns

ml_matrix [force;torque].

References aero_angles_s::alpha, low_speed_aero_s::alpha0, alpha_and_beta(), low_speed_aero_s::aspectRatio, low_speed_aero_s::axis, low_speed_aero_s::cP, low_speed_aero_s::length, lift_vector(), local_angle_of_attack(), low_speed_aero_s::oswaldEff, low_speed_aero_s::s, low_speed_aero_s::thickness, and low_speed_aero_s::zetaTrans.

Referenced by aero_low_speed::update().

simple_lift_and_drag()

ml_matrix simple_lift_and_drag	(	double	v,
		double	k,
		double	cD0,
		double	cLAlpha,
		double	s,
		double	density,
		double	alpha
	)

Simple lift and drag coefficients.

Parameters

v	Velocity (m/s)
k	Induced drag constant
cD0	Drag coefficient at zero angle of attack
cLAlpha	Linear lift slope
s	Effective area (m^2)
density	Atmospheric density (kg/m^3)
alpha	Angle of attack (rad)

Returns

ml_matrix [lift;drag].

References lift_and_drag().

lift_and_drag()

ml_matrix lift_and_drag	(	double	v,
		double	density,
		double	kinematicViscosity,
		double	speedOfSound,
		double	length,
		double	s,
		double	oswaldEff,
		double	aspectRatio,
		double	zetaTrans,
		double	thickness
	)

Mach dependent lift and drag.

Parameters

v	Velocity (m/s)
density	Density
kinematicViscosity	Kinematic viscosity
speedOfSound	Speed of sound
length	Characteristic length
s	Area
oswaldEff	Oswald efficiency factor
aspectRatio	Aspect ratio of wing
zetaTrans	Damping factor for transonic region
thickness	Wing thickness

Returns

ml_matrix [lift;drag].

Referenced by simple_lift_and_drag().

alpha_and_beta() [1/2]

aero_angles_t alpha_and_beta	(	const ml_matrix &	v_body,
		const ml_matrix &	v_body_dot
	)

Compute the angle of attack and sideslip.

Parameters

v_body	Velocity vector in the body frame (m/s)
v_body_dot	Velocity vector derivative in the body frame (m/s)

Returns

Data structure with alpha, beta, their derivatives and total velocities

References aero_angles_s::alpha, aero_angles_s::alpha_dot, aero_angles_s::beta, aero_angles_s::beta_dot, aero_angles_s::v_total, and aero_angles_s::v_total_dot.

Referenced by lift_vector(), and low_speed_lift_and_drag().

alpha_and_beta() [2/2]

aero_angles_t alpha_and_beta

(

const ml_matrix &

v_body

)

Compute the angle of attack and sideslip.

Parameters

v_body	Velocity vector in the body frame (m/s)
v_body_dot	Velocity vector derivative in the body frame (m/s)

Returns

Data structure with alpha, beta, their derivatives and total velocities

References aero_angles_s::alpha, aero_angles_s::alpha_dot, aero_angles_s::beta, aero_angles_s::beta_dot, aero_angles_s::v_total, and aero_angles_s::v_total_dot.

lift_vector()

ml_matrix lift_vector

(

const ml_matrix &

v_body

)

Lift vector.

Parameters

v_body

Velocity vector in the body frame (m/s)

Returns

Data structure with alpha, beta, their derivatives and total velocities

References aero_angles_s::alpha, alpha_and_beta(), aero_angles_s::beta, and body_to_wind().

Referenced by low_speed_lift_and_drag().

body_to_wind()

ml_matrix body_to_wind	(	double	alpha,
		double	beta
	)

Body to wind axes.

Parameters

alpha	Angle of attack
beta	Sideslip

Returns

Body to wind axes matrix

Referenced by lift_vector().

local_angle_of_attack()

double local_angle_of_attack	(	double	alpha,
		const ml_matrix &	aB,
		double	delta
	)

Body to wind axes.

Parameters

alpha	Angle of attack
aB	Axis of rotation
delta	Local angle

Returns

Body to wind axes matrix

Referenced by low_speed_lift_and_drag().

rankine_hugoniot_factor()

double rankine_hugoniot_factor	(	double	gamma,
		double	m,
		double	p_inf
	)

Pressure modification for Newtonian.

Parameters

gamma	Ratio of specific heats
m	Mach number
p_inf	Pressure at infinity

Returns

Maximum pressure coefficient