### Flutter, and aeroelasticity in general, is a topic that is often misunderstood or incorrectly applied due to its inherent complexity.

To start, let’s first consider what flutter is; an instability due to an interaction between aerodynamic, inertial, and elastic forces.

Although this type of instability is not unique to aircraft, the instability was initially investigated due to its prominence in aircraft. As with a normal modes (free-vibration) analysis, to carry out a flutter analysis we require a global mass matrix (inertial forces) and a global stiffness matrix (elastic forces), which can be seen in the normal modes equations of motion:

The additional piece we then require when conducting an aeroelastic analysis is the influence from the unsteady aerodynamics present in the problem. These are generated in NASTRAN by default using the Doublet-Lattice Method (DLM), which is the unsteady corollary to the Vortex-Lattice Method (VLM). When using this approach, a 2D planform surface is generated and discretized as seen below, and can be used to generate the Aerodynamic Influence Coefficients (AIC’s).

With these three distinct forces modeled, the flutter problem is often solved iteratively as an eigenvalue problem at all prescribed free-stream air speeds. The results include the damping and associated frequencies of each mode shape at each airspeed. When the damping of one of these modes becomes positive, the first flutter speed has been found.

**1.What are Splines and how do they work?**

When generating the AIC’s for a particular model, there is a slight problem that must be resolved. The structural model degrees of freedom (DOF) and the aerodynamic DOF are not the same.

The hallmark of aeroelasticity in general is the interaction between aerodynamics and structural forces, so there must be a way to freely pass information from one system to another (such as displacements and forces). This is most commonly achieved using splines:

The default spline (surface) used in NASTRAN is the infinite plate spline in which the differential equation of an infinite plate under a point load is solved at all of the structural DOF and then the N linear solutions are superimposed on one another. What this means is that when constructing splines to connect the aerodynamic and structural DOF, reducing regions connected by splines can drastically reduce the computational time required.

For example, take a straight rectangular wing with no control surfaces. In terms of accuracy, there is very little difference between using 1 spline to connect the aerodynamic and structural DOF, and dividing the wing into two regions (such as an outer wing and an inner wing section) and using two splines. Splitting it up into two regions and using two splines will drastically reduce the computational time required to generate the splines, and by proxy, the run of the aeroelastic analysis in general.

**2. You can detect Divergence in a flutter analysis!**

When conducting an aeroelastic analysis, it is actually possible to also detect the divergence speed as well. This might seem strange as divergence is a static aeroelastic instability and flutter analysis in inherently a dynamic stability analysis. When the AIC’s are generated using the DLM, the quasi-steady AIC terms (when the reduced frequency

*k*=0) are actually generated using VLM. When conducting a divergence analysis, all that is needed is information about the elastic forces, and the quasi-steady aerodynamic forces.Since this information is already included in the matrices required to run a classical flutter analysis, it stands to reason that we should be able to detect divergence as well. This explanation is hand waving at best from an academic perspective, but sufficient for the user interested in the application of flutter analysis.

In order to detect divergence, we must look at the vibration frequency of the modes. Notice in the figure below that mode 1 frequency goes to zero at some point. With the behavior of this mode becoming steady, you would then have to go to the damping plot to observe when the mode 1 damping became positive, signaling divergence.

**3. What are the Mach Number and Reduced Frequency and why do they matter?**

Two very important numbers that appear repeatedly in flutter analysis are the Mach number and reduced frequency. When implementing a flutter analysis, these are actually the only two numbers required to generate your AIC’s once the aerodynamic model has been generated. Many are familiar with the Mach number as the free-stream air speed over the speed of sound.

For subsonic flutter analysis, the Mach number is used to account for compressibility effect between 0.3<M<0.8, which is nicely illustrated in the following picture taken from a lecture series from the Mechanical and Aerospace Engineering Department of the Florida Institute of Technology:

As the Mach number increases, the aerodynamic forces are also scaled up. This in turn can greatly affect the results of a flutter analysis in the compressible subsonic flight regime.

The reduced frequency is a much subtler parameter. The reduced frequency is calculated using the following:

where

*ω*is the circular frequency,*b*is the half chord, and*U*is the free-stream velocity. The reduced frequency is really an indication of how unsteady the behavior of the system is. As the reduced frequency approaches 0, the behavior of that corresponding mode approaches steady behavior (such as divergence). As one might expect as the reduced frequency grows larger, the behavior of a mode is more unsteady. As a rule of thumb, a reduced frequency larger than 1 corresponds to highly unstable behavior. In addition, as the reduced frequency increases indicating more unsteady behavior, the lift is reduced and the phase lag between the lift and the dynamic motion of the structure also increases.**4. Modeling Body Freedom Flutter is Easy!**

When conducting flutter analysis on a wing, it is common to simply constrain the root of the wing to be fixed. When conducting a flutter analysis on a full aircraft however, it is very important to consider how the dynamics of the rigid body motion can also couple with the structural and aerodynamics of the model. What this means is that you can end up with a lower flutter speed than otherwise predicted if the aircraft were fixed in place.

This type of behavior is particularly apparent in the Air Force Research Lab (AFRL) Body Freedom Flutter (BFF) aircraft, X-56A, seen below in a picture from the NASA website:

In order to test control surface flutter suppression techniques, this blended wing aircraft was designed to exhibit body freedom flutter. For more conventional design aircraft, body freedom flutter tends to appear less frequently, however it should not be dismissed. Below is what this vehicle looks like when it reaches its flutter speed:

When using NASTRAN’s solution 145, body freedom flutter can be incorporated by simply running a model without any constraints. This allows the six ~0 Hz (rigid body) modes to couple with the elastic modes.

**5. What can you achieve with Aeroelastic Tailoring?**

One of the benefits of using composite materials in an aircraft’s design is the possibility to aeroelastically tailor the loads and behavior of the aircraft. This can actually be done on traditional metallic aircraft structures such as by moving the shear center, however since stiffness of metals is uniform tailoring metallic aircraft structures is more difficult. When using composites, the stiffness of a structure can be manipulated by simply changing the ply angles within the structure, rather than changing the physical geometry.

Typically, aeroelastic tailoring is associated with the tailoring of a wings lift distribution or to allow for better wing gust response, however aeroelastic tailoring can also be used to manipulate the flutter speed and divergence speed of an aircraft. One of the simplest examples of this kind of tailoring was explored by Dr. Patil in 1997 using a composite box beam:

By changing the fiber angles of the four sides of the box beam, he was able to show how the flutter and divergence speed of a wing using this structure changes parametrically as a function of ply angle:

## 0 Comments