variavel0=<b>GUILHERME AUGUSTO VARGAS CESAR</b> - vargas@iae.cta.br IAE
<b>PAULO AFONSO DE OLIVEIRA SOVIERO</b> - soviero@aer.ita.br ITA
<b>Abstract.</b> The problem of unsteady lifting surfaces with straight leading edges in sonic flow that was already studied in Cesar and Soviero (2001) is extended in this work to the case of finite thickness wings. The wings are supposed to be undergoing harmonic oscillation near the sonic flight speed in an inviscid, shock free flow. The thickness effect is accounted for in the analysis through the use of the local Mach number distribution over the wing surface at its mean position, as it was obtained in Alksene, and Spreiter (1961), by employing the local linearization concept and a suitable coordinate transformation. Sample results are shown for a rectangular wing, which are compared with that of analogous theory shown in other works, such as in Ruo et al. (1974). The generalized aerodynamic forces coefficients for a series of reduced frequencies and thickness as well as pressure distributions for finite wings of various aspect ratios are shown.
<b>Keywords.</b> Unsteady aerodynamics, Sonic flow, Panel method, Linearized theory, Finite thickness wing.