Feasibility study on the second generation SST

Mizuno, Hiroshi; Hagiwara, Sei; Hanai, Toshio; Takami, Hikaru

doi:10.2514/6.1991-3104

Cited by 4 publications

(1 citation statement)

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“…Compared with the data published in literature 14 the operational empty weight is predicted approximately 16 % higher. The mass breakdown indicates significant discrepancies between predicted and published fuselage and system weights 15.…”

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confidence: 81%

Improvement of a preliminary design and optimization program for the evaluation of future aircraft projects

Strohmeyer

Seubert

1998

7th AIAA/USAF/NASA/ISSMO Symposium on Multidisciplinary Analysis and Optimization

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Nomenclature A = aspect ratio B = wing span C D = drag coefficient C D,0 = zero-lift drag coefficient, C D (C L =0) C L = lift coefficient C L / C D = lift-over-drag ratio, L / D C M = pitching moment coefficient C p = pressure coefficient c = chord length H = flight altitude, km h = height, m k = k-factor of quadratic drag polar k α = correction factor for vortex lift l µ = aerodynamic mean chord M ∞ = freestream Mach number R = range, km S = wing reference area, m 2 W = weight, t x, y, z = cartesian coordinates x C.G. = x-position of the center of gravity x N = x-position of aerodynamic neutral point α = angle of attack ε = trim angle ϕ 25 = sweep angle of quarter-chord line λ = bypass ratio η = non-dimensionalized chord length τ = taper ratio Indices C.G. = center of gravity C = canard cr = cruise f = friction HTP = horizontal tailplane lin = linear loc = local max = maximum value opt = optimum value p = pressure req = requiredIntroduction Analyses of the international operating airlines predict an annual increase of the worldwide air traffic between 5 % and 7 % for the next decades (Fig. 1). Based on these predictions the large aircraft companies and national aeronautical research institutes think about alternative concepts such as the supersonic commercial transport aircraft (SCT) or the Megaliner (A3XX) -which go beyond the conventional stretching of the existing wide bodies (B747, A330/A340).

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confidence: 81%