One-Degree-of-Freedom Flutter

To illustrate the application of classical flutter analysis, a simple configuration is treated first. This example is a one-degree-of-freedom aeroelastic system consisting of a rigid two-dimensional wing that is permitted to rotate in pitch about a specified

One-Degree-of-Freedom Flutter

Figure 5.5. Schematic of the airfoil of a two-dimensional wing that is spring-restrained in pitch

 

reference point. This is a special case of the typical-section configuration shown in Fig. 5.2 for which the plunge degree of freedom is equal to zero, as depicted in Fig. 5.5. The system equations of motion reduce to one equation that can be written as

 

One-Degree-of-Freedom Flutter

M = M exp(i at)

 

(5.43)

 

where

 

One-Degree-of-Freedom Flutter

(5.46)

 

ав = .

 

and rearranging the algebraic relationship, we obtain the final equation to be solved for the flight condition at the flutter boundary as

 

IP

 

+ me (к, MTO) = 0

 

(5.47)

 

1

 

npTOb4

 

To solve this equation, it is presumed that the configuration parameters Ip, , and b

are known. The unknown parameters that describe the motion and flight condition are rn, pTO, k, and Mro. These four unknowns must be determined from the single algebraic equation, Eq. (5.47). Because the aerodynamic coefficient, mp(k, Mro), is complex, it can be written as

me (k, Mro) = Щ[тв (k, M«>)] + i»[m0 (k, Mro)] (5.48)

Подпись: IP nprob4 Подпись: 1 - Подпись: + Щщ (k, 0)] + iS[m0 (k, 0)] = 0 Подпись: (5.49)
One-Degree-of-Freedom Flutter

As a consequence, both the real and imaginary parts of the algebraic relationship must be zero, thus providing two real equations to determine the four unknowns. Therefore, two of the unknown parameters should be specified. A fixed altitude is chosen that specifies the freestream atmospheric density, pro. The second parameter to be fixed is the Mach number, which can be given a temporary value of zero. This, of course, implies that the flow is incompressible and the aerodynamic-moment coefficient is then only a function of the reduced frequency. The governing algebraic equation now can be written as

Equating the imaginary part of the left-hand side to zero gives a relationship that can be solved for the reduced frequency, kF, at the flutter boundary; that is

Подпись: (5.50)S[mp (kF, 0)] = 0

With kF known, Щ[те (kF, 0)] can be numerically evaluated. Equating the real part of the left-hand side to zero now enables the frequency, mF, to be determined from

/ Щ_у = 1 + nproЬ*Щ[тв (kp, 0)] (5 51)

&F / Ip

Подпись: UF Подпись: boJF kF Подпись: (5.52)

Now that kF and mF have been determined, it is possible to compute the flutter speed as

The flutter speed determined by the previous procedure corresponds to the originally specified altitude and is based on an incompressible representation of the airloads. After this speed has been determined, the speed of sound, cro, at the specified altitude can be used to find the flutter Mach number as

Uf

Mp = — (5.53)

cro

If this flutter Mach number is sufficiently small to justify the use of incompressible aerodynamic coefficients, then the altitude-speed combination obtained is a point on the flutter boundary. If the flutter Mach number is too high to validate the in­compressible approximation, then the entire procedure should be repeated using aerodynamic coefficients that are based on the initially computed flutter Mach num­ber. Using the standard atmospheric model, which relates density and the speed of sound, this iterative scheme converges to a flight condition on the flutter boundary.

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