By Daniel P. Raymer
This best-selling textbook offers the complete strategy of plane conceptual layout - from standards definition to preliminary sizing, configuration structure, research, sizing, optimization, and exchange reviews. utilizing a real-world method of the method of layout, this identify beneficial properties greater than 900 pages of layout equipment, illustrations, tips, motives, and equations. It contains overviews of lofting, subsystems, maintainability, producibility, vulnerability, and stealth; ideas and calculation tools for aerodynamics, balance and keep watch over, propulsion, buildings, weights, functionality, and value; insurance of traditional and unconventional layout equipment, together with UAV, canard, tandem wing, C-wing, indirect wing, asymmetrical, multi-fuselage, wing-in-ground-effect, and extra.
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Additional resources for Aircraft Design. A Conceptual Approach
Lips T, Fritsche B (2005) Acomparison of commonly used re-entry analysis tools. Acta Astronaut 2005(57):12 36. Liaw GS, Guo KL, Chou LC (1993) Burnett solutions along the stagnation line of a cooled cylinder in low-density hypersonic flows. AIAA Paper, 1993–2726 37. Zhong X (1993) On numerical solutions of Burnett equations for hypersonic flow past 2-d circular blunt leading edges in continuum transition regime. AIAA Paper, 1993–3092 38. Zhong X, Furumoto G (1994) Solutions of the Burnett equations for axisymmetric hypersonic flow past spherical blunt bodies.
As stated by Macrossan , being a ratio of two characteristic lengths, K n ∞ is only a state parameter rather than a flow parameter, and cannot sufficiently describe hypersonic flows, especially those involving the aeroheating problem. We have found that Wr is approximately inversely proportional to the modified Cheng’s parameter K 2 , a fitted correlation parameter that is popularly used in the engineering practice. This parameter was first introduced by Cheng  based on the TVSL model, and later modified by Engel  according to correlation with the experimental data.
2 there will emerge a gradual and successive evolution as the rarefaction degree increases. The boundary layer and the shock wave will thicken and go closer to each other, leading to touch, overlap, and even mergence. This interaction process is precisely accompanied by the enhancement of the nonlinear effects in the flow and heat transfer. In many early studies, the variation of the aeroheating performance was directly considered to be caused by viscous interaction between the shock wave and the boundary layer.
Aircraft Design. A Conceptual Approach by Daniel P. Raymer