Aircraft design is a compromise between many competing factors and constrains. These constrains are mainly economical and technical, both having a great influence on how a design is carried out. The technological depends on the economical, therefore it is necessary to find new methods that will allow engineers to lower the time that takes to develop a new design and at the same time lower the cost.
Throughout the development of this report there will be a brief explanation of what the actual Aircraft Design Process is and in which stages the methodology that the authors are proposing will be implemented as well as the tools that will interact to produce this methodology. The proposed tool will be the first part of a methodology that, according to the authors, by integrating separate tools that are currently used in different stages of the aeronautical design, will promote a decrease in the time frame for the initial stages of the design process…
Contents
1 INTRODUCTION
1.1 BACKGROUND
1.1.1 Conventional Design Process
1.1.2 Objective of this thesis
1.1.3 Planning
2 PANAIR 502I
2.1 FUNDAMENTALS
2.1.1 What is PANAIR
2.2 IMPLEMENTATION
2.2.1 Working with PANAIR
2.2.2 Input File
2.2.3 Output File
2.3 PANAIR SURFACE VALIDATION
2.3.1 Validation procedure
2.3.2 Grid Point Extraction
2.3.3 Result comparison
3 CATIA V5
3.1 PARAMETRIC AIRCRAFT MODEL
3.1.1 About CATIA in this thesis
3.1.2 Building structure
3.1.3 Fuselage Part
3.1.4 Wing Parts
3.1.5 Horizontal Tail
3.1.6 Vertical Tail
3.1.7 Engine Configuration
3.1.8 Engines choice and positioning
3.2 PARAMETERIZATION
3.2.1 General Parameterizations rules
3.2.2 Examples of parametric modeling
3.2.3 Examples of different configurations
3.3 AUTOMATIC MESH MODEL
3.3.1 Meshing Tool
3.3.2 Modification of CATIA model for making automatic mesh possible
3.3.3 Parameterization of the meshed product
3.3.4 The Automatic Mesh Environment
3.3.5 Examples of different configurations
4 TRANSLATION PROGRAM
4.1 FUNDAMENTALS
4.2 IMPLEMENTATION
4.2.1 Environment
4.2.2 Results
4.2.3 Validation
5 DISCUSSION AND CONCLUSION
5.1 THE THESIS WORK OVERALL
5.2 PARAMETRIC MODEL
5.3 PANAIR
5.4 TRANSLATION PROGRAM
5.4.1 Comparison between different PAM configurations
5.4.2 Comparison between different Cessna surface configurations
5.4.3 Validation
6 APPENDIX
6.1 CATIA
6.1.1 Examples of different mesh configurations
6.1.2 Fuselage plus Wing configuration for PANAIR analyzes
6.1.3 Full Configuration minus the Engine for PANAIR analyzes
6.1.4 Pre-set Engines
6.2 TRANSLATION PROGRAM
6.2.1 Edge Numbering
6.2.2 Forced Intersections
6.2.3 Input File of the “Full Configuration minus the Engine”
6.2.4 Output File of the “Full Configuration minus the Engine”
6.3 SURFACE DIVISION VALIDATION RESULTS
6.3.1 Lift Coefficient results (Cl)
6.3.2 Induced Drag Coefficient Results (CDi)
7 REFERENCES
Author: Tarkian, Mehdi
Source: Linköping University
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