Hybrid-Delta Wing Simulations – Industrial Application for Combat Aircraft Design

2022 ◽  
Author(s):  
Andreas Hövelmann ◽  
Patrick Pölzlbauer ◽  
Stefan Pfnür ◽  
Andreas Winkler ◽  
Stephan M. Hitzel
Keyword(s):  
Industrial Application ◽  
Delta Wing ◽  
Aircraft Design ◽  
Combat Aircraft

Designer Solid Shims for Assembly of Advanced Carbon Composite Pre-preg based Aircraft Structures

2021 ◽  
Vol 13 (1) ◽  
Author(s):  
Sanjay Kumar ◽  
P. Selvaraj
Keyword(s):  
Composite Structure ◽  
Delta Wing ◽  
Critical Path ◽  
Research Work ◽  
Carbon Composite ◽  
Raw Material ◽  
Manufacturing Cost ◽  
Interface Surface ◽  
Combat Aircraft ◽  
And Performance

A modern combat aircraft uses considerable amount of advanced composite material in structure build for better flight performance, stealth requirement and higher payload. Combat aircrafts made using composite structure require large numbers of custom shims of various thickness and shapes throughout interface surface, which are presently prepared by suit on assembly process to fill gaps measured between sub-structure parts and skin. The scope of study is four plus generation combat aircraft like Indian Light combat aircraft. These gaps arise due to composite raw material characteristics, mould tool and manufacturing process which results in geometry variation. This research has focussed the delta wing integral fuel tank composite structure. However, these research findings can be applied in other wing shapes made by composite part within the scope. The shims, whether liquid or solid, are necessary to eliminate gaps, maintain structural performance and minimize pull-down forces required to bring the aircraft into engineering nominal configuration for aerodynamic efficiency. Customized shims amount to significant delays in production with much of the time being spent in the critical path of the aircraft assembly. In this research work, we present an alternative strategy for the use of designer solid shim, based on redesign of lay-up moulding tool (female type) and shims manufacturing with change in existing manufacturing value stream. The experimented method has reduced the manufacturing cost of wing assembly, shorten the shimming process cycle and improve the assembly efficiency, product quality and performance.

The role of drag prediction in combat aircraft design and development

2008 ◽  
Vol 112 (1132) ◽  
pp. 327-332 ◽  
Author(s):  
J. B. Newton
Keyword(s):  
Structural Design ◽  
Wind Tunnel Test ◽  
Aircraft Design ◽  
Design And Development ◽  
Overall Design ◽  
Methods Development ◽  
Combat Aircraft ◽  
Future Challenges ◽  
Drag Prediction

Abstract This paper gives an overview of combat aircraft drag prediction in the context of the overall design and development process. Following a brief summary of the author’s experience in this field, the importance of drag prediction during initial configuration design is discussed, emphasising the need for the drag aerodynamicist to develop a good understanding of the other aerodynamic disciplines involved, as well as an appreciation of the of the total design process encompassing structural design, propulsion integration and systems installation. A brief description is given of typical simplified prediction methods used in initial design, followed by an example of drag synthesis procedures based on wind-tunnel test and analysis, illustrating the need for good understanding of test techniques and the requirements of other aerodynamic disciplines. Some future challenges are identified, requiring continual involvement in research and methods development programmes.

scholarly journals Devising a concept of integrated design and modeling of aircraft

2021 ◽  
Vol 5 (1(113)) ◽  
pp. 15-23
Author(s):  
Oleksandr Grebenikov ◽  
Andrii Humennyi ◽  
Oleksandr Dveirin ◽  
Oleksandr Soboliev ◽  
Lilia Buival
Keyword(s):  
Three Dimensional ◽  
Integrated Design ◽  
Aircraft Design ◽  
Parametric Modeling ◽  
Parametric Models ◽  
Space Distribution ◽  
Design Parameters ◽  
Combat Aircraft ◽  
Cad Cam ◽  
And Training

The analysis of aircraft design methods reported here has revealed that building a competitive aircraft necessitates devising a scientifically based concept of integrated aircraft design employing CAD/CAM/CAE/PLM software suites. A generalized concept of integrated design and three-dimensional computer modeling of aircraft involving the CAD/CAM/CAE/PLM systems has been developed. Based on the proposed concept, the principles of integrated design of aircraft were devised. The features of designing the training and training-combat aircraft, transport-category aircraft, light civilian aircraft have been described. A method for determining the take-off weight, design parameters, and formation of the general appearance of aircraft has been improved. The method is intended to form the appearance of the aircraft at the stages of preliminary design, the purpose of which is reduced to determining the permissible version of the aircraft project. The project must meet the predefined requirements and restrictions in the selected aircraft scheme and the assigned set of parameters that characterize its airframe and power plant. A method of parametric modeling of aircraft has been improved, which includes the stages of creating a master geometry of the aircraft and a model of space distribution. Parametric models of master geometry and models of space distribution, training and training-combat aircraft, transport-category aircraft, light civilian aircraft have been constructed. Methods of integrated design of aircraft main units have been devised and theoretically substantiated. Parametric models of master geometry of the wing for a training aircraft, the wings, appendage, and fuselage of a light civilian aircraft were built, taking into consideration the design features of aircraft units of various categories

A Note on the Evaluation of the Supersonic Downwash Integral

1954 ◽  
Vol 5 (2) ◽  
pp. 111-118
Author(s):  
B. A. Hunn
Keyword(s):  
Closed Form ◽  
Numerical Evaluation ◽  
Delta Wing ◽  
Aircraft Design ◽  
Current Trends ◽  
Centre Line ◽  
Trailing Edges ◽  
Leading Edges

SummaryTo calculate tail loads in flight it is necessary to know the angle of downwash at all points of the tailplane for any given value of wing incidence. Current trends in aircraft design place the tailplane off the plane of the wing. There exist solutions for the downwash in the z=0 plane for a delta wing with subsonic leading edges. This note gives a form of integral suitable for numerical evaluation which determines the downwash in the plane of symmetry (y=0) of a delta wing with subsonic leading edges. This note also points out an apparent error in Ref. 4 by G. N. Ward and gives a closed form for the downwash at a point whose forward Mach cone totally includes an arrowhead wing with supersonic trailing edges and whose centre line coincides with the axis of the cone.

Manufacturing Process of Blended Delta-Shaped Wing Model

2013 ◽  
Vol 845 ◽  
pp. 971-974 ◽  
Author(s):  
Shabudin Mat ◽  
I. Shah Ishak ◽  
Khidzir Zakaria ◽  
Z. Ajis Khan
Keyword(s):  
Wind Tunnel ◽  
Manufacturing Process ◽  
Delta Wing ◽  
Wind Tunnel Test ◽  
Aircraft Design ◽  
Wing Model ◽  
Tunnel Model ◽  
Cad Cam ◽  
Actual Flow ◽  
Flow Cycle

Aerodynamicists have long acknowledged the blended wing body (BWB) aircraft design could produce great aerodynamic advantages due to the integration of the delta wing structure with the thick center body. Therefore the wind tunnel test campaign is crucial to gain information of the flow field that governs the delta-shaped wing which has frequently baffled the aerodynamicists. In such, the wind tunnel test required acceptable quality of delta-shaped wing model for results validity. Consequently, the manufacturing process as well as the selection of the appropriate machinery tools, must be wisely designed and performed. The modular 3D concept in associating with CAD/CAM technology was utilised in the process. Finally, the actual flow cycle of manufactures blended BWB aircraft model was sucessfully established. The objective of this paper is to highlight those complexity manufacturing process and techniques involved in order to produce a good blended delta-shaped wind tunnel model.

Verification and Validation of High-Fidelity Open-Source Simulation Tools for Supersonic Aircraft Aerodynamic Analysis

2021 ◽  
Author(s):  
Henry Stoldt ◽  
Artem Korobenko ◽  
Paul Ziade ◽  
Craig Johansen
Keyword(s):  
Open Source ◽  
Large Scale ◽  
Delta Wing ◽  
Three Dimensional ◽  
Aircraft Design ◽  
Verification And Validation ◽  
Small Scale ◽  
High Fidelity ◽  
Supersonic Aircraft ◽  
Academic Settings

Abstract Small supersonic vehicle concepts used as research platforms to test new aerospace technologies, such as advanced propulsion systems or large sensor payloads, require major modifications to conventional, large-scale, manned, supersonic airframe design. High-fidelity numerical simulation of these concepts in academic settings often requires the use of in-house or available open-source tools instead of expensive commercial software or those with export-control restrictions. A verification and validation analysis of two widely-used open-source compressible-flow solvers, rhoCentralFoam (rCF) and SU2, is performed for several flow problems relevant to the supersonic aerodynamics of small-scale, autonomous aircraft concepts. The one-dimensional shock tube problem, two-dimensional supersonic turbulent boundary layer, and three-dimensional delta wing are simulated with both solvers. The effects of flux scheme, flux limiters, and Courant-Friedrichs-Lewy (CFL) number on solution accuracy, stability, and solver speed are assessed. The solvers' limitations and their usefulness as supersonic aircraft design tools in a holistic sense are discussed.

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