The three-dimensional, unsteady, inviscid and viscous flow is simulated over the joined-wing section of a HALE aircraft, based on the Intelligence, Surveillance and Reconnaissance (ISR) or Sensorcraft configuration. These high-aspect ratio wings undergo large deflections, and necessitate simultaneous consideration of the nonlinear structural analysis to account for the aeroelastic effect, using dynamic grid for accurate prediction of the stall behavior, due to the unsteady fluid loads. A Reynolds-Averaged Navier- Stokes (RANS) based flow solver, COBALT, is used for the prediction of the unsteady fluid loads on the structure. Towards this end, a test case on the ONERA M6 Wing was simulated to understand usage of the flow solver, and quantitative as well as qualitative results compared with published results. Additionally, a low-speed validation was performed on the Sensorcraft geometry, with qualitative results compared with those available for a similar geometry. The operating regime of the Sensorcraft is simulated and the unsteady fluid loads determined. Hence, steady and unsteady results for angles of attack of 0° and 12°, respectively, are presented for this geometry. Flow separation is observed at region near the join on the main and aft wings at 12° angle of attack. Coefficient of lift at this high angle of attack is 1.37. Also, qualitative surface pressure variation is presented, with quantitative distributions extracted at particular locations. The pressure loads determined are applied on the structure, which would result in a deformation of the structure, which will then be re-meshed in the grid generator software and the flow analysis carried out again on this new shape. © 2003 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.
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