PAN AIR analysis of simply connected control surface deflections

Moyer, Seth

doi:10.2514/3.46329

Cited by 4 publications

(1 citation statement)

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“…This procedure allows to find the best combination of geometry and flaps deflection simultaneously. The objective function applied in the present method contains additional terms described below appended to (7) in order to simplify the design process and making it of practical value. The direct utilization of the panel method in an optimization routine to evaluate the objective function is not reasonable because of the cost and computing time.…”

Section: Solution Of the Inverse Problemmentioning

confidence: 99%

Application of the panel method to subsonic aerodynamic design

Kubrynski

1997

Inverse Problems in Engineering

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Communicated by G. S. DulikravichComputational methods play an important part in aerodynamic development of modern flying vehicles. In order to improve the flying efficiency many assistant devices, such as leading/trailing flaps are applied. Although there exist many flow analysis methods useful in such aerodynamic configurations, the inverse methods can significantly improve the process of aerodynamic design and final aerodynamic efficiency. This paper a oanel method which allows for desim of 3-dimensional configurations with orescribed &essure distribution at various desFgn angles of attack, inciuding the effe'ct of flap deflections. The high order panel method is applied to analyze the flow. The flap deflections are simulated by changing Neumann boundary conditions. The inverse problem is solved via optimization: the geometry which minimizes differences between design and actual pressure distributions is found iteratively using an optimization technique. The geometrical constrains and regularity conditions can be specified via penalty function concept. The idea of extending the range of applicability of the inverse panel method to transonic flow is also presented.

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Section: Solution Of the Inverse Problemmentioning

confidence: 99%