Canard–wing interference effects on the flight characteristics of a transonic passenger aircraft

Ghoreyshi, Mehdi; Darragh, Ryan; Harrison, Sean; Lofthouse, Andrew J.; Hamlington, Peter E.

doi:10.1016/j.ast.2017.06.024

Cited by 8 publications

(2 citation statements)

References 8 publications

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“…There are many other studies that have been performed to verify the CFD simulation results with the experimental data. These include, among others, the use of 3D RANS CFD software to simu-late the canard for SAAB passenger aircraft [3] and blended wing body (BWB) model [4], ANSYS CFX CFD software for different wing designs of a remote control aircraft [5], CATIA and ANSYS FLUENT for Scottish Aviation Bulldog light aircraft [6], general Zonal Euler Solver (ZEUS) to simulate the supersonic missile of SM-2 Block IVA [7] and the use of CFD++ software to study the drag force on a different geometry of nacelle [8]. All these results have been verified with the wind tunnel testing and they are found to be in good agreement.…”

Section: Introductionmentioning

confidence: 99%

Aerodynamic performance of X-plane with two different types of inboard stores

Rahman¹,

Harmin²,

Koslan³

et al. 2018

IJET

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This paper presents the investigation of aerodynamic performance of inboard Store-X and Store-Y configurations on the X-plane aircraft model through computational fluid dynamics (CFD) analysis. The X-plane and Store-Y represent the default store and pylon integration while Store-X provides a possibility for other types of store to be integrated. These stores are loosely based upon the two most commonly used by the western and eastern blocks. The resultant lift, drag and moment forces are of interest in order to observe their impact with respect to the two different stores configurations. The finding shows that the aerodynamic impact with respect to Store-X installation on the inboard pylon station is insignificant when compared to default system, hence offers the safety of delivering the Store-X from the X-plane aircraft.

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Section: Introductionmentioning

confidence: 99%

Aerodynamic performance of X-plane with two different types of inboard stores

Rahman¹,

Harmin²,

Koslan³

et al. 2018

IJET

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“…This code has been used at the U.S. Air Force Academy (USAFA) for flow field simulation of a variety of aerospace vehicles and for modeling nonlinear unsteady aerodynamics of maneuvering aircraft [20][21][22][23][24][25]. The code development began in February 1990 and has proven to be very robust and accurate since then.…”

Section: Introductionmentioning

confidence: 99%

Simulation and Modeling of Rigid Aircraft Aerodynamic Responses to Arbitrary Gust Distributions

et al. 2018

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Abstract:The stresses resulting from wind gusts can exceed the limit value and may cause large-scale structural deformation or even failure. All certified airplanes should therefore withstand the increased loads from gusts of considerable intensity. A large factor of safety will make the structure heavy and less economical. Thus, the need for accurate prediction of aerodynamic gust responses is motivated by both safety and economic concerns. This article presents the efforts to simulate and model air vehicle aerodynamic responses to various gust profiles. The computational methods developed and the research outcome will play an important role in the airplane's structural design and certification. COBALT is used as the flow solver to simulate aerodynamic responses to wind gusts. The code has a user-defined boundary condition capability that was tested for the first time in the present study to model any gust profile (intensity, direction, and duration) on any arbitrary configuration. Gust profiles considered include sharp edge, one minus cosine, a ramp, and a 1-cosine using tabulated data consisting of gust intensity values at discrete time instants. Test cases considered are a flat plate, a two-dimensional NACA0012 airfoil, and the high Reynolds number aero-structural dynamics (HIRENASD) configuration, which resembles a typical large passenger transport aircraft. Test cases are assumed to be rigid, and only longitudinal gust profiles are considered, though the developed codes can model any gust angle. Time-accurate simulation results show the aerodynamic responses to different gust profiles including transient solutions. Simulation results show that sharp edge responses of the flat plate agree well with the Küssner approximate function, but trends of other test cases do not match because of the thin airfoil assumptions made to derive the analytical function. Reduced order aerodynamic models are then created from the convolution integral of gust amplitude and the time-accurate responses to sharp-edge gusts. Convolution models are next used to predict aerodynamic responses to arbitrary gust profiles without the need of running time-accurate simulations for every gust shape. The results show very good agreement between developed models and simulation data.

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