Objectives and Constraints for Transonic Wing Optimization

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Abstract

Consideration of the aerodynamic shape optimization problem definition is presented. An issue with drag minimization is that shocked-free solutions often result which have isolated performance improvements. As such, in this paper, optimizing the range parameter is considered enriched with the operating point as a design variable. A constraint on dimensional lift is therefore required. Analytical treatment of this problem is used to demonstrate that supercritical solutions result providing the lift is above a critical threshold. Also, three-dimensional effects penalise lift coefficient and promote higher optimum Mach numbers. Single- and multi-point optimizations of the NASA CRM wing are considered, inspired by the AIAA ADODG Case 4, as well as a range optimization. A shocked solution is found for the range optimization.
Original languageEnglish
Title of host publicationAIAA SciTech Forum and Exposition 2020
PublisherAmerican Institute of Aeronautics and Astronautics Inc. (AIAA)
Number of pages16
DOIs
Publication statusPublished - 5 Jan 2020
EventAIAA SciTech Forum - Hyatt Regency Hotel, Orlando, United States
Duration: 6 Jan 202010 Jan 2020

Conference

ConferenceAIAA SciTech Forum
Country/TerritoryUnited States
CityOrlando
Period6/01/2010/01/20

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  • HPC (High Performance Computing) Facility

    Susan L Pywell (Manager), Simon A Burbidge (Other), Polly E Eccleston (Other) & Simon H Atack (Other)

    Facility/equipment: Facility

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