Fin buffeting features of an early F-22 model

Robert, W Moses; Lawrence, J Huttsell

doi:10.2514/6.2000-1695

Cited by 21 publications

(7 citation statements)

References 5 publications

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“…The vortexes over such configurations are well known to contribute to excess lift. The breakdown of those vortex has been the primary cause of severe tail buffeting on the F‐18 E/F (Anthony and Robert, 2005; Moses and Huttsell, 2000; Erickson et al , 1989), and similar behavior has been observed on the F‐22 (Robert, 1999). Due to the similitude in configuration the water tunnel experiment was set up to investigate the vortex breakdown behavior and its relative location to the fin.…”

Section: Water Tunnel Testingmentioning

confidence: 78%

Subscale flight testing used in conceptual design

Jouannet

Berry

Melin

et al. 2012

Aircraft Engineering and Aerospace Technology

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PurposeThe purpose of this paper is to present the latest subscale demonstrator aircraft developed at Linköping University. It has been built as part of a study initiated by the Swedish Material Board (FMV) on a Generic Future Fighter aircraft. The paper will cover different aspects of the performed work: from paper study realised by SAAB to the first flight of the scaled demonstrator. The intention of the paper is to describe what has been realised and explain how the work is may be used to fit within aircraft conceptual design.Design/methodology/approachThe approach has been to address the challenges proposed by the customer of the demonstrator, how to design, manufacture and operate a scaled demonstrator of an aircraft study in conceptual design within five months. Similar research projects have been reviewed in order to perform the current work.FindingsThe results obtained so far have led to new questions. In particular, the project indicated that more research is needed within the area of subscale flight testing for usage in aircraft conceptual design, since a scaled demonstrator is likely to answer some questions but will probably open up new ones.Research limitations/implicationsThe current research is just in its infancy and does not bring any final conclusion but does, however, offer several guidelines for future works. Since the aircraft study was an early phase concept study, not much data are available for validation or comparison. Therefore, the paper is not presenting new methods or general conclusions.Practical implicationsResults from a conceptual aircraft study and a realisation of a scaled prototype are presented, which show that scaled flight testing may be used with some restriction in conceptual design.Originality/valueThe value of this paper is to show that universities can be involved in prototype development and can work in close collaboration with industries to address issues and solutions within aircraft conceptual design.

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Section: Water Tunnel Testingmentioning

confidence: 78%

Subscale flight testing used in conceptual design

Jouannet

Berry

Melin

et al. 2012

Aircraft Engineering and Aerospace Technology

View full text Add to dashboard Cite

show abstract

“…Wentz (1987), Ferman et al (1990), Zimmerman et al (1989), Shah (1991), Lee & Tang (1992), Martin & Thompson (1991) and Lee et al (1993) characterized the surface pressure spectra on tails of model F/A-18 aircraft. Moses & Huttsell (2000) performed similar types of measurements on the "n of a model F-22 aircraft. Luber et al (1996) assessed the impact of dynamic loads on the design of aircraft.…”

Section: Buffeting Of Tails and Plates: Surface Loadingmentioning

confidence: 99%

Vortex Breakdown From a Pitching Delta Wing Incident Upon a Plate: Flow Structure as the Origin of Buffet Loading

Özgören

Şahi̇n

Rockwell

2002

Journal of Fluids and Structures

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“…Studies of model F-18 aircraft, which primarily focused on the surface pressure spectra on tails ( ns), include the works of Wentz, 8 Ferman et al, 9 Zimmerman et al, 10 Shah, 11 Lee and Tang, 12 Martin and Thompson, 13 and Lee et al 14 Similar types of measurements on the n of a model F-22 aircraft were undertaken by Moses and Huttsell. 15 Luber et al 16 addressed the role of dynamic loads on the design of aircraft. Use of active control techniques applied directly to the surface of a n can effectively attenuate the buffet response, as demonstrated by Ashley et al 17 Of course, the origin of buffeting of any aerodynamic surface is the unsteady ow adjacent to it.…”

Section: Introductionmentioning

confidence: 99%

Perturbations of a Delta Wing: Control of Vortex Breakdown and Buffeting

Özgören

Şahi̇n

Rockwell

2001

Journal of Aircraft

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A delta wing is subjected to small-amplitude perturbations over a range of periods, to simulate leading-edge control concepts. Substantial modi cations of the instantaneous and averaged structure of the leading-edge vortex are attainable, both with and without a downstream impingement plate. The features of the vortex response are characterized using a technique of high-image-densityparticle image velocimetry. The locationof the onset of vortex breakdown can either be advanced or retarded, and the attendant changes in vortex structure are interpreted in the context of buffeting of the impingement plate. Comparison of the vortex structure with and without deployment of the plate shows a dramatic in uence of the plate. Nomenclatureperturbation frequency of the wing, Hz f 0 = frequency of vortex breakdown, Hz L = distance between trailing edge of the delta wing and leading edge of the plate L p = length of the plate, mm M = magni cation N = number of samples Re = Reynolds number, U 1 C=º T = total time of sample, s T e = period of wing perturbation, s T 0 = period of inherent (undisturbed) vortex breakdown, s U ref = reference velocity, mm/s U 1 = freestream velocity, mm/s V = total velocity, mm/s hV i = averaged velocity, mm/s v = transverse velocity component, mm/s v rms = root mean square of transverse velocity uctuations, mm/s W p = width of the plate, mm X ¤ b = vortex breakdown location in presence of wing perturbation, mm .X ¤ b / 0 = vortex breakdown location for stationary wing, mm ® = angle of attack of delta wing, deg ®.t / = dynamic angle of attack of delta wing, deg ® 0 = amplitude of wing perturbation, deg N ® = mean angle of attack, deg 1! = incremental values of vorticity, 1/s 3 = sweep angle of delta wing, deg º = kinematic viscosity, mm 2 /s ! = vorticity, 1/s h!i = averaged vorticity,

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Fin buffeting features of an early F-22 model

Abstract: Fin buffeting is an aeroelastic phenomenon encountered by high performance aircraft, especially those with twin vertical tails that must operate at high angles of attack. This buffeting is a concern from fatigue and inspection points of view.

Cited by 21 publications

References 5 publications

Subscale flight testing used in conceptual design

Subscale flight testing used in conceptual design

Vortex Breakdown From a Pitching Delta Wing Incident Upon a Plate: Flow Structure as the Origin of Buffet Loading

Perturbations of a Delta Wing: Control of Vortex Breakdown and Buffeting

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