Supersonic Experimental Airplane (NEXST) for Next Generation SST Technology - Development and flight test plan for the Unmanned Scaled Supersonic Glider

Sakata, Keisuke

doi:10.2514/6.2002-527

Cited by 19 publications

(2 citation statements)

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“…Japan Aerospace Exploration Agency (JAXA) initiated a scaled supersonic experimental aeroplane project named NEXST (National Experimental Supersonic Transport) project [16] in 1996 so as to establish advanced design technologies for the next-generation SST. The program ended in 2007.…”

Section: Historical Backgroundmentioning

confidence: 99%

Review and prospect of supersonic business jet design

Sun

Smith

2017

Progress in Aerospace Sciences

101

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This paper reviews the environmental issues and challenges appropriate to the design of supersonic business jets (SSBJs). There has been a renewed, worldwide interest in developing an environmentally friendly, economically viable and technologically feasible supersonic transport aircraft. A historical overview indicates that the SSBJ will be the pioneer for the next generation of supersonic airliners. As a high-end product itself, the SSBJ will likely take a market share in the future. The mission profile appropriate to this vehicle is explored considering the rigorous environmental constraints. Mitigation of the sonic boom and improvements aerodynamic efficiency in flight are the most challenging features of civil supersonic transport. Technical issues and challenges associated with this type of aircraft are identified, and methodologies for the SSBJ design are discussed. Due to the tightly coupled issues, a multidisciplinary design, analysis and optimization environment is regarded as the essential approach to

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Section: Historical Backgroundmentioning

confidence: 99%

Review and prospect of supersonic business jet design

Sun

Smith

2017

Progress in Aerospace Sciences

101

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“…16 The original designed cranked arrow wing was modified so that the leading edges can be deflected as leading-edge flaps. Two different leading-edge cross sections were tested, that is, the original design (relatively sharp leading edge) and the rounded leading edge, which has a diameter of 2% of the wing mean aerodynamic chord.…”

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confidence: 99%

Studies on Vortex Flaps with Rounded Leading Edges for Supersonic Transport Configuration

Rinoie¹,

Miyata²,

Kwak³

et al. 2004

Journal of Aircraft

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Wind-tunnel measurements were taken on a cranked arrow wing supersonic transport configuration with leading-edge vortex flaps. Force and surface pressure measurements were made at Reynolds number based on the wing mean aerodynamic chord from 9.2 × × 10 5 to 3.8 × × 10 6 . Two different flap cross sections (the originally designed nonrounded leading edge and the rounded leading edge) were tested. The purpose of the measurements is to clarify how the differences of the Reynolds number affect the flow around the rounded leading-edge vortex flaps and the flap performance. The wing with the rounded leading-edge vortex flaps indicated some benefit of the lift/drag ratio as compared with those of the nonrounded vortex flaps at a relatively high-lift coefficient greater than 0.3. Different flow patterns were observed over the rounded leading-edge vortex flaps when the Reynolds number was increased at a lift coefficient greater than 0.5. The spanwise length of the separated region shortens as the Reynolds number is increased. Nomenclaturepitching moment coefficient nondimensionalized using C mac and measured about 0.25 C mac C mac = wing mean aerodynamic chord, m C p = pressure coefficient C r = wing root chord at model centerline, m D = rounded leading-edge diameter, m L/D = lift/drag ratio M = freestream Mach number Re = Reynolds number based on mean aerodynamic chord U ∞ = freestream velocity, m/s x = chordwise coordinate measured from apex of delta wing at model centerline, m y = spanwise coordinate orthogonal to x, measured from model centerline, m α = wing angle of attack, deg δ fLEin = inboard vortex flap deflection angle, deg δ fLEout = outboard leading-edge flap deflection angle, deg

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Improvements in the reliability and quality of unstructured hybrid mesh generation

Ito

Nakahashi

2004

Numerical Methods in Fluids

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SUMMARYThis paper presents a reliable and automated approach to the generation of unstructured hybrid grids comprised of tetrahedra, prisms and pyramids for high Reynolds number viscous ow simulations. To enhance robustness, the hybrid mesh generation process starts with the formation of an isotropic tetrahedral grid. Prismatic layers are then added on no-slip walls fully automatically by obeying userspeciÿed boundary conditions and three parameters: the number of the layers, an initial layer thickness normal to the walls, and a stretching factor. Topological modiÿcations to the original isotropic tetrahedral elements are prohibited during the layer generation process. The tetrahedral elements near no-slip walls are shifted inward and the resulting gap between the tetrahedra and the walls is ÿlled up with prismatic elements. To enhance the quality of the prismatic layers around sharp corners, two normals are evaluated for the marching process in these regions. The addition of prismatic elements is locally stopped if negative-volume elements are created or not enough space is left. An angle-based smoothing method ensures that the quality of the tetrahedral elements is retained for a reasonable computational cost. The method is demonstrated for two scaled experimental supersonic airplane models designed at the National Aerospace Laboratory of Japan (NAL). Numerical results are compared with wind tunnel experimental data.

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Supersonic Experimental Airplane (NEXST) for Next Generation SST Technology - Development and flight test plan for the Unmanned Scaled Supersonic Glider

Cited by 19 publications

References 0 publications

Review and prospect of supersonic business jet design

Review and prospect of supersonic business jet design

Studies on Vortex Flaps with Rounded Leading Edges for Supersonic Transport Configuration

Improvements in the reliability and quality of unstructured hybrid mesh generation

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