GOLAND THEME FULL

Rampurawala, Aeroelastic system identification using transonic CFD data for a wing/store configuration, Aerospace Science and Technology, 11(2-3):145-154,2007. Rampurawala, Aeroelastic system identification using transonic CFD data for a 3D wing, IX International Conference on Recend Advances in Structural Dynamics, 17-19 July 2005, Southampton, UK. Zweber, Numerical analysis of store-induced limit-cycle oscillation, Journal of Aircraft, 41(6),1315-1326,2004.

GOLAND THEME FULL

Nichkawde Studies of Store-Induced Limit-Cycle Oscillations Using a Model with Full System Nonlinearities, Nonlinear Dynamics, 37(4),323-339,2004 Eastep, Influence of tip store mass location on wing limit cycle oscillation, in Proceedings of the 2003 AIAA Dynamics Specialist Conference, AIAA Paper 2003-1731. Zweber, Effects of viscosity on store-induced limit-cycle oscillation, in ITEA Aircraft-Stores Compatibility Symposium, Destin, Florida, 2003. Scott, The dependence of store-induced limit-cycle oscillation predictions on modelling fidelity, in RTO Applied Vehicle Technology Panel Symposium, Paris, France, Paper No. Hodges and C.E.S Cesnik, Nonlinear aeroleastic analysis of complete aircraft in subsonic flow, Journal of Aircraft, 37(5),753-760,2000. Goland, The flutter of a uniform cantilever wing, Journal of Applied Mechanics, 12(4), A-197 - A-208, 1945. This was implemented in MatLab using MSC. By varying the structural parameters, 1000 samples of different mode shapes and natural frequencies were generated. The CFD based eigenvalue analysis requires the normal mode shapes and natural frequencies as inputs. In the following example, seven parameters were allowed to vary within +/- 5% of their nominal values to perform Monte-Carlo analysis of the aeroelastic stability. In the Goland wing case this can play a decisive factor with respect to flutter. The influence of structural variability on the aerelastic behaviour of aircraft has been receiving increased attention from the community. Structural and Modal files ( Input Files).ICEM CFD HEXA Projects ( ICEM Multiblock).The wing with store has also been shown to develop an LCO in the transonic regime, Beran et al(2004). The clean case model has been shown to flutter at relative low velocities, Beran et al(2004), Woodgate and Badcock(2007). The result of the model is a very flexible wing that can exhibit several different aeroelastic behaviors. The material properties of every element consist of a Young's modulus of 1.4976x10 9 slugs/ft 2, a shear modulus ofĥ.616x10 8 slugs/ft 2, and a structural density of 0.0001 slugs/ft 3. The spar and rib caps are modeled by rod elements and posts connect the wing skins at every spar/rib intersection. The finite element model is built up from shear panels, modeling the spars and ribs, and membrane elements, modeling the wing skins. The wing structure is modeled by a finite element model of the wing box. The store has a width of 1ft and a length of 10ft. Two configurations are available, with or without a tip store. The aerofoil consists of a 4% thick parabolic arc. The model represents a cantilevered wing with a 20ft span and 6ft chord. The Goland wing model used in this work is based on the described model in Beran et al(2004). Goland Wing - Inviscid Flowfield at M0.90

Goland theme