class Rotor

Basic Rotor class (development release)

Public Methods

Rotor()

~Rotor()

void CalcDepVars()

void ComputeCT_and_vi()

Compute the values of the dependent variables

Public Members

class Rotor_NewtonMethod: public Newton<Rotor>

Private Fields

int b

Geometry variables

double R

number of blades

double c

radius (m)

double theta1

mean chord of blades (m)

Vector3D r_hub

blade torsion (º)

double Izz

Inertia/Mechanics

double a

Aerodynamic variables

double delta_0

mean lift coefficient of blades (1/rad)

double delta_1

double delta_2

double B

Coefficients of drag: cd=delta0+delta1*alpha+delta2*alpha^2

double k_i

Modified Momentum Theory constants:

double k_v

double eta_w

double omega

State variables

double omega_nom

rotor spin velocity (rad/seg)

Vector3D velocity

nominal rotor spin velocity.

double rho

velocity respect to air in global axes

double sigma

Computed variables --------------------------------------------------------

double lock

solidity

double v_i

Intermediate variables:

double lambda_i

induced velocity

double mu

non-dimensional induced velocity ¿(1/omega R)?

double mu_z

advance parameter

double theta_C

Control variables

double CT

Non-dimensional Forces and Moments;

double CQ

Thrust coefficient

Documentation

Basic Rotor class (development release)

Rotor()

~Rotor()

void CalcDepVars()

void ComputeCT_and_vi()

Compute the values of the dependent variables

int b

Geometry variables

double R

number of blades

double c

radius (m)

double theta1

mean chord of blades (m)

Vector3D r_hub

blade torsion (º)

double Izz

Inertia/Mechanics

double a

Aerodynamic variables

double delta_0

mean lift coefficient of blades (1/rad)

double delta_1

double delta_2

double B

Coefficients of drag: cd=delta0+delta1*alpha+delta2*alpha^2

double k_i

Modified Momentum Theory constants:

double k_v

double eta_w

double omega

State variables

double omega_nom

rotor spin velocity (rad/seg)

Vector3D velocity

nominal rotor spin velocity. (rad/seg)

double rho

velocity respect to air in global axes

double sigma

Computed variables --------------------------------------------------------

double lock

solidity

double v_i

Intermediate variables:

double lambda_i

induced velocity

double mu

non-dimensional induced velocity ¿(1/omega R)?

double mu_z

advance parameter

double theta_C

Control variables

double CT

Non-dimensional Forces and Moments;

double CQ

Thrust coefficient

This class has no child classes.

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