Transonic Free-To-Roll Analysis of the F-35 (Joint Strike Fighter) Aircraft

Owens, D. Bruce; McConnell, Jeffrey K.; Brandon, Jay M.; Hall, Robert M.

doi:10.2514/1.16972

Cited by 9 publications

(5 citation statements)

References 6 publications

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“…Wind tunnel 1-DOF test includes free-to-pitch (or freeto-yaw) wind tunnel test [19][20][21][22] and free-to-roll wind tunnel test [23][24][25]. They let the test model oscillate freely on a support apparatus under an initial condition and are usually used to identify free motion modes and dynamic stability derivatives.…”

Section: Hils It Is Worth Mentioning That Sometimes "Virtual Flightmentioning

confidence: 99%

“…Wind tunnel 1-DOF test allows rapid assessment of unsteady aerodynamics effects on the motion of model without the complexity of a free-flying test or VFT. The NASA Langley 16-ft Transonic Tunnel (TT) free-to-roll (FTR) apparatus [24] is taken as an example here. A 1/15thscale F-35 aircraft model is mounted on the FTR apparatus 3 and rolls freely on the rig (see Figure 5).…”

Section: Hils It Is Worth Mentioning That Sometimes "Virtual Flightmentioning

confidence: 99%

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A Review of Wind Tunnel Based Virtual Flight Testing Techniques for Evaluation of Flight Control Systems

Huang

Wang

2015

International Journal of Aerospace Engineering

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Wind tunnel based Virtual Flight Testing (VFT) is a dynamic wind tunnel test for evaluating flight control systems (FCS) proposed in recent decades. It integrates aerodynamics, flight dynamics, and FCS as a whole and is a more realistic and reliable method for FCS evaluation than traditional ground evaluation methods, such as Hardware-in-the-Loop Simulation (HILS). With FCS evaluated by VFT before flight test, the risk of flight test will be further reduced. In this paper, the background, progress, and prospects of VFT are systematically summarized. Specifically, the differences among VFT, traditional dynamic wind tunnel methods, and traditional FCS evaluation methods are introduced in order to address the advantages of evaluating FCS with VFT. Secondly, the progress of VFT is reviewed in detail. Then, the test system and key technologies of VFT for FCS evaluation are analyzed. Lastly, the prospects of VFT for evaluating FCS are described.

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Section: Hils It Is Worth Mentioning That Sometimes "Virtual Flightmentioning

confidence: 99%

Section: Hils It Is Worth Mentioning That Sometimes "Virtual Flightmentioning

confidence: 99%

A Review of Wind Tunnel Based Virtual Flight Testing Techniques for Evaluation of Flight Control Systems

Huang

Wang

2015

International Journal of Aerospace Engineering

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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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“…A trailing-edge flap likewise acts as an aerobrake under landing conditions. Indeed, a wide range of airplanes accepts the trailing-edge flap, from small ones with propeller propulsion systems [39] to medium/large-sized bodies with jet engines [32] and even fighters [29]. The use of a leadingedge flap and a trailing-edge flap together generally improves takeoff/landing aerodynamic performance [5].…”

Section: Introductionmentioning

confidence: 99%

Aerodynamic efficacy of adding yaw-wise rotational degree of freedom to an airplane flap

Chiba

Komatsu

Ito

2020

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This study scrutinized the aerodynamic change of adding a yaw-wise rotational degree of freedom to a single slotted flap of airplane via computational fluid dynamic analyses. Existing slotted flaps have spanwise constant gaps and are disharmonious with the 3D nature of the flow field. A flap geometry and its angle condition are sensitive to aerodynamic performance; small variations in them must be useful in aerodynamic improvement. To add the yaw-wise rotation to a flap is a lower hurdle than to attain other high-lift systems. Therefore, after defining a simple configuration consisting of a fuselage, a wing, and a single slotted flap, we investigated the mesh dependency to consider the diversity in flow phenomena precisely; we examined the effect of the yaw-wise rotation for the flap on improving the whole lift. To place the flap at suitable yaw-wise rotation angles consequently effected raising the lift. We revealed the physical mechanism that accelerating the fluid in the gap between the wing and the flap changes the separation structure on the flap upper surface and grows the lift.

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Transonic Free-To-Roll Analysis of the F-35 (Joint Strike Fighter) Aircraft

Cited by 9 publications

References 6 publications

A Review of Wind Tunnel Based Virtual Flight Testing Techniques for Evaluation of Flight Control Systems

A Review of Wind Tunnel Based Virtual Flight Testing Techniques for Evaluation of Flight Control Systems

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

Aerodynamic efficacy of adding yaw-wise rotational degree of freedom to an airplane flap

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