Unsteady aerodynamics measurements on an elastic wing model of SST

Tamayama, Masato; Miwa, Hitoshi; Nakamichi, Jiro

doi:10.2514/6.1997-836

Cited by 7 publications

(10 citation statements)

References 2 publications

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“…The wing structure is made up of a 7 mm thick aluminum plate with holes drilled to make it flexible. It was found in the experiments that the frequency of the first wing bending mode increased from 9.79 Hz in vacuum to around 15 Hz at Mach 0.8 [16]. It was also indicated that the response of the wing in vacuum is much lower than in air, and this has been used to justify neglecting the inertial effect of the flap motion on the wing response.…”

Section: Nal-sst Arrow Wingmentioning

confidence: 89%

“…Distinct peaks on the unsteady pressure can be seen Along with the measured unsteady pressure and deformation, the finite element model (FEM) data in the form of a structural grid and computed natural modes of vibration are also provided in the paper [15]. A brief description of the structure of the experimental model is presented in an earlier paper by Tamayama [16]. The wing structure is made up of a 7 mm thick aluminum plate with holes drilled to make it flexible.…”

Section: Nal-sst Arrow Wingmentioning

confidence: 99%

“…Closer examination of the structural model presented in [15] showed the presence of an unidentified mode between the first wing bending and torsion modes. To test the stiffening of the original model in the flow an aeroelastic simulation was performed with the given FEM model and the flow conditions described in the experiment [16]. A small impulse was given to the wing and the frequency of the oscillation was calculated.…”

Section: Nal-sst Arrow Wingmentioning

confidence: 99%

“…The Japan Aerospace Exploration Agency (JAXA) [formerly National Aerospace Laboratory (NAL)], as part of the Japanese SST program, is developing an experimental supersonic transport model and a wind-tunnel model of this was tested in the transonic regime for unsteady pressure and dynamic deformation [15,16]. The purpose of the experiment was to accumulate data for the validation of aeroelastic codes and active control technology.…”

Section: Introductionmentioning

confidence: 99%

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Evaluation of a Simplified Grid Treatment for Oscillating Trailing-Edge Control Surfaces

Rampurawala

Badcock

2007

Journal of Aircraft

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The aeroelastic behavior associated with control surfaces is of particular practical interest. The treatment of the control surface in a computational fluid dynamics based simulation is complicated by the change in topology of the geometry as the flap edge is exposed. This paper evaluates the use of a treatment which blends the flap edge into the wing. This simplifies the mesh treatment by avoiding topological changes. The influence of the treatment of the forced flap motions on the aerodynamic responses of the rigid benchmark active control technology wing and a flexible supersonic transport wing is evaluated. Comparison is made with results obtained when the flap edge is exposed. It is shown that the predictions from the blended treatment give similar results, including local effects on the control surface, to calculations which include the flap edge effects. Nomenclature f = force acting at the grid points K = structural stiffness matrix M = structural mass matrix M 1 = freestream Mach number x = grid locations = change in grid locations f = flap angle = generalized modal coordinates 0 i = blending function for transfinite interpolation ! = modal frequency Subscripts a = aerodynamic surface grid s = structural grid

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Section: Nal-sst Arrow Wingmentioning

confidence: 89%

Section: Nal-sst Arrow Wingmentioning

confidence: 99%

Section: Nal-sst Arrow Wingmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Evaluation of a Simplified Grid Treatment for Oscillating Trailing-Edge Control Surfaces

Rampurawala

Badcock

2007

Journal of Aircraft

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“…2) If the wind tunnel is continuously driven, the temperature drifts in the tunnel during a test influence the pressure transducer signal 7) . In order to eliminate this effect, steady pressure distributions…”

mentioning

confidence: 99%