Wing design for supersonic transports using integral equation method

Matsushima, Kisa; Iwamiya, Toshiyuki; Nakahashi, Kazuhiro

doi:10.1016/s0955-7997(03)00055-9

Cited by 13 publications

(8 citation statements)

References 3 publications

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“…Finally, a comment is given, regarding the here-described extension for high-transonic Mach numbers of the original Takanashi transonic inverse design method in comparison to Matsushima's inverse design method for supersonic flow (10,12) . The approaches taken to consider supersonic flow (or regions of supersonic flow in a transonic flow) are different.…”

Section: Modifications For Flow With High Transonic Mach Numbermentioning

confidence: 99%

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DLR transonic inverse design code, extensions and modifications to increase versatility and robustness

Streit¹,

Hoffrogge²

2017

Aeronaut. j.

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The DLR inverse design code computes the wing geometry for a prescribed target pressure distribution. It is based on the numerical solution of the integral inverse transonic small perturbation (TSP) equations. In this work, several extensions and modifications of the inverse design code are described. Results are validated with corresponding redesign test cases. The first modification concerns applications for high transonic Mach numbers or cases with strong shocks. The introduced modifications enable converged design solutions for cases where the original method failed. The second modification is the extension of the code to general non-planar wings. Previously, the design code was restricted to non-planar wing designs with small dihedral or to nacelle design. A third modification concerns aerofoil/wings designed for wind-tunnel design. In order to design a swept wing between two wind-tunnel walls, the solution method was extended to two symmetry planes. The introduced extensions and modifications have increased the robustness and range of applicability of the inverse design code.

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Section: Modifications For Flow With High Transonic Mach Numbermentioning

confidence: 99%

“…Extensions of Takanashi's method to supersonic flow and to multi-lifting surfaces are described in Refs 10 and 11. Applications of these extensions are given in Refs 12 and 13. An efficient 3D inverse design method which uses a different approach as the Takanashi method is the CDISC knowledge-based method (14) .…”

Section: Introductionmentioning

confidence: 99%

DLR transonic inverse design code, extensions and modifications to increase versatility and robustness

Streit¹,

Hoffrogge²

2017

Aeronaut. j.

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“…American Institute of Aeronautics and Astronautics There are many input parameters for designing a SSBJ; therefore, a configure file is formed to collect all input parameters together. In lift calculation section, the base wing geometry is taken from JAXA's study 14 and modified. Total lift is calculated from the sum of the lift forces of wing slices in finite thickness.…”

Section: A Aircraft Designmentioning

confidence: 99%

Design and Optimization of a Supersonic Business Jet

Kıyıcı

Aradağ

2015

22nd AIAA Computational Fluid Dynamics Conference

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Supersonic transport (SST) technology has widely been investigated. Flow characteristics become complicated in supersonic conditions, and aerodynamic shape optimization studies are required for the design process of supersonic vehicles. An optimized aircraft is very efficient in terms of fuel consumption and pressure losses. This study focuses on the aerodynamic design and shape optimization of a supersonic business jet. For this purpose, a design algorithm (BF-I) is developed with the help of historical trends of supersonic aircrafts, commercial aircrafts and experimental correlations. After obtaining the baseline geometry, a gradient-based optimization is employed to get optimum results for the design. The developed numerical methodology is tested for both 2D and 3D geometries. CFD analysis are performed by using SU 2 (Stanford University Unstructured) solver that has high performance for compressible flows. Euler equations are used for the analyses.

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“…In addition, the CFD results also suggest that different optimum airfoils should be used depending on the planform because the trends of aerodynamic performance differ according to the planform. The several researches have been carried out regarding supersonic wing design [4] [5]. In reference [4], a natural laminar flow wing was designed by the inverse design.…”

Section: Introductionmentioning

confidence: 99%

“…The several researches have been carried out regarding supersonic wing design [4] [5]. In reference [4], a natural laminar flow wing was designed by the inverse design. In reference [5], the multi-disciplinary design which was considered the interaction between the aerodynamics and the structure by an evolutionary algorithm was discussed.…”

Section: Introductionmentioning

confidence: 99%

Planform Dependency on Airfoil Design Results for Supersonic Wing in Supersonic and Transonic

Kishi

Kanazaki

Makino

et al. 2016

JFCMV

Self Cite

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In this study, the wing design problem for different planforms for supersonic transport (SST) under supersonic and transonic cruise conditions is discussed to obtain knowledge of the supersonic air-foil from the viewpoint of wing planform dependency. Two types of planforms were considered-a cranked arrow wing with a high sweep-back angle and a tapered wing with a low sweepback angle. The optimum airfoils of these planforms were designed by efficient global optimization, which combined the evolutionary algorithm with the Kriging surrogate model. To acquire design knowledge, the functional analysis of variance was applied to the solution space and the design space. The design results show that the optimum airfoil and the contribution ratios of design variables for the airfoils of the two planform are different.

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Wing design for supersonic transports using integral equation method

Cited by 13 publications

References 3 publications

DLR transonic inverse design code, extensions and modifications to increase versatility and robustness

DLR transonic inverse design code, extensions and modifications to increase versatility and robustness

Design and Optimization of a Supersonic Business Jet

Planform Dependency on Airfoil Design Results for Supersonic Wing in Supersonic and Transonic

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