Rolling Moment Characteristics at High Alpha on Several Planforms of Cranked Arrow Wing Configuration

Kwak, Dong-Youn; Hirai, Kentaro; Rinoie, Kenichi; Kato, Hideaki

doi:10.2514/6.2009-3937

Cited by 3 publications

(5 citation statements)

References 11 publications

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“…5 for AOA ranging from -30 to +30 deg. The linearity of its lift coefficient is found to be good for this wide range of positive AOA, owing to the stability of the vortex system over the present cranked-arrow wing with a large inboard sweepback angle of 66deg 1) . The linearity deteriorates for negative AOA probably because the engine nacelles would interfere with the vortex system.…”

Section: Lift and Drag Characteristicsmentioning

confidence: 97%

“…Generally, the cranked-arrow wing has good aerodynamic characteristics over a wide range of flight Mach number and angle of attack, because of its stable vortex system. Such aerodynamics have been investigated in detail for wing-fuselage configurations without tails by Rinoie, Kwak, et al [1][2][3][4][5] But those for overall configuration of practical vehicles with tails and control surfaces have not yet been clarified sufficiently. Then the aerodynamic stability and controllability for the proposed baseline configuration are analyzed through wind tunnel tests in this development study.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Development of a Small-scale Supersonic Flight Experiment Vehicle as a Flying Test Bed for Future Space Transportation Research

Mizobata

Minato

Higuchi

et al. 2014

AEROSPACE TECHNOLOGY JAPAN

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Innovation in technologies for high-speed atmospheric flights is essential for establishment of both supersonic/hypersonic and reusable space transportations. It is quite effective to verify such technologies through small-scale flight tests in practical high-speed environments, prior to installation to large-scale vehicles. Thus we are developing a small-scale supersonic flight experiment vehicle as a flying test bed. Several aerodynamic configurations are proposed and analyzed by wind tunnel tests. A twin-engine configuration with a cranked-arrow main wing is selected as the baseline of the first generation vehicle. Its flight capability is predicted by point mass analysis on the basis of aerodynamic characterization and propulsion performance estimation. In addition, a prototype vehicle with an almost equivalent configuration and dimension is designed and fabricated for verification of the subsonic flight characteristics of the experiment vehicle. Its first flight test is carried out and good flight capability is demonstrated. Furthermore a revised aerodynamic configuration with an air-turbo ramjet gas-generator cycle (ATR-GG) engine is being designed for the second generation design with improvement in flight capability at higher Mach numbers. Development of the engine, airframe structure, and autonomous guidance/control system is underway. This prospective flight experiment vehicle will be applied to flight verification of innovative fundamental technologies for high-speed atmospheric flights such as turbo-ramjet propulsion with endothermic or biomass fuels, MEMS and morphing techniques for aerodynamic control, aero-servo-elastic technologies, etc.

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Section: Lift and Drag Characteristicsmentioning

confidence: 97%

Section: Introductionmentioning

confidence: 99%

Development of a Small-scale Supersonic Flight Experiment Vehicle as a Flying Test Bed for Future Space Transportation Research

Mizobata

Minato

Higuchi

et al. 2014

AEROSPACE TECHNOLOGY JAPAN

View full text Add to dashboard Cite

show abstract

“…The first suction peak at 55% local semi-span indicates the inboard primary vortex, whereas the small suction peak at approximately 70% local semi-span represents the inboard secondary vortex at α = 12.5 • and 15 • . It is induced by the primary vortex and causes the re-separation of the boundary layer [17]. At X = 0.75C r , the suction peak at approximately 85% local semi-span corresponds to the outboard primary vortex at α = 12.5 • , exhibiting the strong negative pressure.…”

Section: Observation Of Span-wise Surface Pressurementioning

confidence: 99%

Characteristics of Vortices around Forward Swept Wing at Low Speeds/High Angles of Attack

Kanazaki,

Setoguchi

2023

Aerospace

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The forward-swept wing (FSW), one of the wing planforms used in aircraft, is known for its high performance in reducing wave drag. Additionally, a study has shown that this wing planform can mitigate sonic booms, which pose a significant challenge to achieving supersonic transport (SST). Therefore, FSW is expected to find applications in future SST aircraft owing to aerodynamic advantages at high speeds. However, there is a lack of sufficient knowledge and systematization to improve aerodynamic performance at low speeds and high angles of attack during takeoff and landing. These are crucial for practical implementation. Although the aerodynamic benefits of an FSW in high-speed flight can be harnessed using advanced structural and control technologies, the realization of SST using an FSW is challenging without enhanced research on low-speed aerodynamics. This study explores the practical aerodynamic knowledge of FSWs. We utilized a numerical simulation based on the Navier–Stokes equation and focused on investigating wake vortex phenomena. Our simulation included various wing planforms, including backward-swept wings (BSWs). The results revealed the presence of vortices with lateral axes emanating from the FSW, while longitudinal vortices were observed in the BSW. Based on these results, we developed a theoretical hypothesis for the vortex structure around an FSW.

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“…4, the linearity of the lift coefficient is found to be good for a wide range of AOA from -20 to +20 deg. It is probably owing to the stability of the vortex system over the present cranked-arrow wing with a large inboard sweepback angle of 66deg 4) .…”

Section: Longitudinal Aerodynamicsmentioning

confidence: 99%

“…Such aerodynamics have been investigated in detail for wing-fuselage configurations without tails by Rinoie, Kwak, et al [4][5][6][7][8] But those for overall configuration of practical vehicles with tails and control surfaces have not yet been clarified sufficiently. Thus the aerodynamic stability and controllability for the proposed overall configuration with tails and control surfaces are analyzed intensively in this development study.…”

Section: Aerodynamic Characterizationmentioning

confidence: 99%

Aerodynamics and Flight Capability of a Supersonic Flight Experiment Vehicle

Mizobata

Suzuki

Ooishi

et al. 2016

AEROSPACE TECHNOLOGY JAPAN

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With the aims of creating and validating innovative fundamental technologies for high-speed atmospheric flights, a small scale supersonic flight experiment vehicle is designed as a flying test bed. An aerodynamic configuration is proposed for the 2nd-generation vehicle with a cranked-arrow main wing and a single Air Turbo Ramjet Gas-generator-cycle (ATR-GG) engine. Its longitudinal, lateral, and control surface aerodynamics are characterized through intensive wind-tunnel tests. They are found to be quite moderate except that the directional stability deteriorates severely at large angles of attack and side slip, and that the elevon deflections for roll control cause adverse yaw. These aerodynamic anomalies will result in a tendency of roll reversal at large angles of attack. It can be prevented to some extent by coordinated rudder deflections. In addition, necessity of transonic drag reduction is clarified through thrust margin and flight capability analyses. Probability of 5 to 20 % drag reduction in the transonic regime (Mach 0.8 to 1.2) is demonstrated by configuration modification on the basis of the area rule at Mach 1.1.

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Rolling Moment Characteristics at High Alpha on Several Planforms of Cranked Arrow Wing Configuration

Cited by 3 publications

References 11 publications

Development of a Small-scale Supersonic Flight Experiment Vehicle as a Flying Test Bed for Future Space Transportation Research

Development of a Small-scale Supersonic Flight Experiment Vehicle as a Flying Test Bed for Future Space Transportation Research

Characteristics of Vortices around Forward Swept Wing at Low Speeds/High Angles of Attack

Aerodynamics and Flight Capability of a Supersonic Flight Experiment Vehicle

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