Overview of the abrupt wing stall program

Hall, Robert M.; Woodson, Shawn H.; Chambers, J.

doi:10.1016/j.paerosci.2004.10.002

Cited by 14 publications

(4 citation statements)

References 24 publications

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“…This aircraft, in its pre-production version, experienced abrupt wing stall which resulted in its susceptibility to asymmetric wing stall, or wing drop. 24 Because of the abrupt wing stall of pre-production aircraft, this version makes a good test bed for code comparisons and will be used for the current investigation. The wing drop on the pre-production aircraft was eliminated by modifying the leading-edge flap schedule and adding a porous surface over the wing-fold fairing.…”

Section: B Naval Air Systems Command (Navair)mentioning

confidence: 99%

Computational Methods for Stability and Control (COMSAC): The Time Has Come

Hall

Biedron

Ball

et al. 2005

AIAA Atmospheric Flight Mechanics Conference and Exhibit

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Powerful computational fluid dynamics (CFD) tools have emerged that appear to offer significant benefits as an adjunct to the experimental methods used by the stability and control community to predict aerodynamic parameters. The decreasing costs for and increasing availability of computing hours are making these applications increasingly viable as time goes on and the cost of computing continues to drop. This paper summarizes the efforts of four organizations to utilize high-end computational fluid dynamics (CFD) tools to address the challenges of the stability and control arena. General motivation and the backdrop for these efforts will be summarized as well as examples of current applications.

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Section: B Naval Air Systems Command (Navair)mentioning

confidence: 99%

Computational Methods for Stability and Control (COMSAC): The Time Has Come

Hall

Biedron

Ball

et al. 2005

AIAA Atmospheric Flight Mechanics Conference and Exhibit

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“…The third type is the generic aircraft configuration (Brandon & Nguyen, 1988; Ericsson, Mendenhall, & Perkins, 1996; Ma, Deng, Rong, & Wang, 2015; Ma, Wang, & Deng, 2017; Shi, Deng, Wang, Li, & Tian, 2015), and a pair of forebody leeward vortices is the main feature of its flow field. Besides the above simplified models, many actual aircraft have also been reported to exhibit the wing rock phenomenon in wind tunnel experiments or flight tests, such as the HP 115 (Ross, 1972), F-4, F-5, F-14, Gnat, Harrier (Hsu & Lan, 1985), X-29, X-31 (Ericsson et al., 1996), AV-8B (Hall, Woodson, & Chambers, 2004), F/A-18E fighter (Owens, Bryant, & Barlow, 2006), F-35 fighter (Owens, McConnell, Brandon, & Hall, 2006), a canard-configuration aircraft (Wei, Shi, Geng, & Ang, 2017) and a generic fighter aircraft with a conical forebody (Chung, Cho, Kim, & Jang, 2021).…”

Section: Introductionmentioning

confidence: 99%

Wing rock mode and its mechanism of a flying-wing aircraft

Li,

Feng,

Wang

2023

Flow

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The flying wing is an aerodynamic configuration with high efficiency, but the lack of lateral-directional stability has always been an obstacle that limits its application. In this study, the wing rock motion of a 65° swept flying-wing aircraft is studied via wind tunnel experiments and numerical simulations at a low speed, and various unsteady motion phenomena are focused on. Both the experimental and numerical results show that the flying wing has a bicyclic ${C_l}$ – $\phi $ hysteresis loop during its wing rock, different from the slender delta wing, rectangular wing, generic aircraft configuration, etc., which have a tricyclic hysteresis loop. This form of hysteresis loop implies a different energy exchange manner of the flying wing in the wing rock oscillation. Further analysis shows that the flying wing forms a unilateral leading-edge vortex (LEV) under a high roll angle, with its wing rock oscillation driven by the ‘vortex–shear-layer’ structure, which is different from that of slender and non-slender delta wings. Moreover, the quantitative dynamic hysteresis characteristics of the LEV's strength and location for the flying wing and the slender delta wing are also different. These results have proven the existence of a wing rock mode which is different from previous investigations, which enriches the understanding of self-induced oscillation. Present discoveries are also conducive to the aerodynamic shape design and flight manipulation of a flying-wing aircraft, which is significant for its wider application.

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“…The complex nature of the coefficients and the possibility of spin generally lead to a requirement for extensive wind tunnel and flight testing (Hall et al 2004) to verify the behaviour of the aircraft in a heavy stall (Heinz 2020). Recent developments of advanced numerical methods, such as Detached Eddy Simulation (DES) and unsteady RANS methods (Zhou et al 2019a;Zhou et al 2019b), now offer the opportunity to predict these complex aerodynamic behaviours with greater fidelity (Wang and Fu 2017;Casadei et al 2019;Neves et al 2020), supplementing the existing experimental data and providing design fixes, ahead of the flight testing program.…”

Section: Introductionmentioning

confidence: 99%