# 4.2.1.9. Tail fin Aerodynamics Theory

## 4.2.1.9.1. Notations

**Tail fin aerodynamic reference point**

The tail fin aerodynamic reference point, \(\boldsymbol{x}_\text{ref}\), is the point where the aerodynamic loads are calculated on the tail fin. The structural solver computes the instantenous position, velocity, acceleration, of the reference point at each time step. The initial position of the reference point with respect to the tower top is a user input. Typical choices are the leading edge/apex of the fin or a point close to the center of pressure at zero angle of attack. The other aerodynamic inputs (e.g. aerodynamic moment coefficient) need to be consistent with the choice of the reference point.

**Tail fin coordinate system**

The inertial and tail fin coordinate systems are illustrated in Fig. 4.9. The transformation matrix from the inertial coordinate system to the tail fin coordinate system is given by \(\boldsymbol{R}_\text{tf,i}\).

The reference orientation (when the structure is un-deflected), the transformation matrix is:

For a common application with a vertical fin, the three angles are zero. TODO: The order of the angles might be different in the current implementation (3-2-1) instead of (1-2-3) above)

**Velocities**

The following velocity vectors (3D vectors in global coordinates) are defined (see Fig. 4.9):

\(\boldsymbol{V}_\text{wind}\): Undisturbed Wind speed vector at the reference point

\(\boldsymbol{V}_\text{dist}\): Disturbed wind speed vector at the reference point (the disturbed wind contains the influence of the tower on the flow). AeroDyn has internal methods to compute \(\boldsymbol{V}_\text{dist}\) from \(\boldsymbol{V}_\text{wind}\). For now, we use “wind” but in the future we might use “dist”. In the theory below we would simply replace all the “wind” by “dist”.

\(\boldsymbol{V}_\text{elast}\): Structural translational velocity vector at the reference point

\(\boldsymbol{V}_\text{ind}\): Induced velocity from the wake at the reference point (assumed to be zero for now)

\(\boldsymbol{\omega}\): Structural rotational velocity of the fin

All velocities (except for \(\boldsymbol{V}_\text{ind}\) and \(\boldsymbol{V}_\text{dist}\) which are computed internally by AeroDyn) are provided as input to the aerodynamic solver. The relative wind experienced by the airfoil is given by:

**Angle of attack**

The angle of attack is defined in the \(x_\text{tf}-y_\text{tf}\) plane of the tail fin coordinate systems as illustrated in Fig. 4.10.

We write \(V_{\text{rel},\perp}\) the projection of \(\boldsymbol{V}_\text{rel}\) in this plane. The angle of attack is given by the components of this vector:

In this implementation, the function atan2 is used to compute the angle of attack.

**Loads**

If the dimensionless coefficients are known, they can be projected in the \(x_\text{tf}-y_\text{tf}\) plane as follows:

and the loads are therefore given by:

Once the loads are known in the tail fin coordinate systems, they are transferred to the inertial system as follows:

**Induced velocity**

The induced velocity from the wake at the reference point will affect the relative wind and therefore the angle of attack of the tail fin. Different models are implemented to compute this induced velocity. As a first approximation, this velocity may be set to zero (corresponding to the input TFinIndMod=0):

The rotor-averaged induced velocity can also be used as an estimate (TFinIndMod=1). It is computed as the mean induced velocity over all the blade and aerodynamic nodes

Where \(\boldsymbol{V}_{\text{ind},\text{blade}}[i_b, i_r]\) is the induced velocity vector for blade \(i_b\) and at the radial node \(i_r\). NOTE: This averaging corresponds to what is done for the disk-average of the inflow in AeroDyn. In the future, we can use something weighted by the radius, or using precomputed coefficients, as done by Envision.

More advanced models could set the induced velocity to zero when outside of the wake boundary, or include a tower-shadow-like wake model. Such option is not yet available.

## 4.2.1.9.2. Polar-based model

In the polar-based model, the user provides the aerodynamic coefficients \(C_l, C_d, C_m\), as tabulated data, functions of the angle of attack. The aerodynamic moment is assumed to be provided at the reference point. A common practice is to use the center of pressure at zero angle of attack for polar data, so the user might want to chose such a point as the reference point of the fin. The tabulated data are provided as part of the list of airfoils given with AFNames in the AeroDyn input file. The user only needs to indicate the index TFinAFIndex within the list AFNames to indicate which polar to use for the tail fin.