Aeroelastic response of a 2-D airfoil in a compressible flow field and exposed to blast loading

Effect of thrust on the aeroelastic instability of a composite swept wing with two engines in subsonic compressible flow

“…Leishman (1993) presented approximate indicial functions for different Mach numbers and pitch axis locations to calculate the unsteady lift on airfoils in subsonic compressible flow. Extracting the aerodynamic indicial functions for some flight speed regimes, Marzocca et al (2002) studied the aeroelastic stability of a 2D airfoil in compressible flow. Marzocca et al (2006) also proposed a unified approach for the aerodynamic indicial functions to cover the incompressible and compressible flight speed regimes.…”

“…where k ¼ ob=U 1 is the reduced frequency and the coefficients A ðÞ j and b ðÞ j are given by Marzocca et al (2002).…”

Active vibration control of a fully clamped laminated composite plate subjected to impulsive pressure loadings

“…In this sense, blast loads occurring from fuel and nuclear explosions, gust and sonic boom pulses, are likely to act on their structure [13][14][15][16][17].…”

“…of the finite element model, mode summation method is used with weighted modal matrix φ which is normalized with respect to the mass matrix including dominant modes in the dynamic behavior. After mode summation, the equation of motion becomes B P + + = + Mη Cη Kη F F (16) where M is the weighted mass matrix which equals to unit matrix, C is weighted damping matrix, K is weighted stiffness matrix that includes selected eigenvalues, B F and P F are the reduced blast and piezoelectric force vectors respectively. State-space equations are obtained from the reduced finite element model and can be written with (18) in the closed form as follows,…”

Generalized Transonic Unsteady Aerodynamics via Computational-Fluid-Dynamics/ Indicial Approach.

“…Whereas the representation in the time domain of the unsteady aerodynamic loads is necessary toward determination of the open-closed-loop dynamic response of aeroelastic systems exposed to arbitrary time-dependent external pressure pulses, the formulation in the frequency domain is required toward determination of the flutter instability boundary. 5 The time-domain formulation can also be used for such a purpose. 6 In contrast to the linear indicial approach where the unsteady loads can be expressed in the time domain via the Duhamel's superposition principle, in the transonic flowfield that involves arbitrary time variation of the angle of attack and/or inflow velocity, a generalized Duhamel's superposition principle should be used.…”