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CL_fo_aeroAcc

Acceleration due to aerodynamic forces

Calling Sequence

[acc] = CL_fo_aeroAcc(v, rho, coef_aero)

Description

Parameters

v:

Norm of velocity vector (velocity relative to the atmosphere) [m/s]. (1xN or 1x1)

rho:

Density of the atmosphere [kg/m^3]. (1xN or 1x1)

coef_aero:

Aerodynamic coefficients vector * area / mass [m^2/kg]. (3xN or 3x1)

acc:

Acceleration vector [m/s^2]. (3xN)

Authors

See also

Examples

// --- Example 1: acceleration for a sphere
vel = [7000; 0; 0]; // Spacecraft velocity vector / atmosphere
rho = 4.E-12; // Atmospheric density (kg/m^3)

// Aero coeff vector (aero_vec): in the direction of the force => -vel
cx = 2.2;
aero_vec = cx * CL_unitVector(-vel);
area = 1; // m^2  (area = pi * radius^2)
mass = 100; // kg
acc = CL_fo_aeroAcc(CL_norm(vel), rho, aero_vec .* (area / mass))

// --- Example 2: Acceleration for a flat plate
// Only one side considered (defined by "normal")
vel = [7000; 0; 0]; // Spacecraft velocity vector / atmosphere
rho = 4.E-12; // Atmospheric density (kg/m^3)
normal = [[1; 0; 0], [1; 1; 0]]; // Normal vector to the plate
temp = 1100; // K
temp_p = 300; // K
m_mol_mass = 0.015; // kg
ratio_spec = 0.1;
alpha = 1;

// NB: function CL_mod_aeroPanelCoefV expects velocity of wind / plate => -vel
aero_vec = CL_mod_aeroPanelCoefV(-vel,  normal, temp, temp_p, m_mol_mass, ratio_spec, alpha, 1, "acv");
area = 1; // m^2
mass = 100; // kg
acc = CL_fo_aeroAcc(CL_norm(vel), rho, aero_vec .* (area / mass))

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