High performance supersonic missile inlet design using automated optimization

Ge Cheng Zha, Donald Smith, Mark Schwabachei, Khaled Rasheed, Andrew Gelsey, Doyle Knight, Martin Haas

Research output: Contribution to conferencePaperpeer-review

12 Scopus citations

Abstract

A multi-level design strategy for supersonic missile inlet design is developed. The multi-level design strategy combines an efficient simple physical model analysis tool and a sophisticated CFD Navier-Stokes analysis tool. The efficient simple analysis tool is incorporated into the optimization loop and the sophisticated CFD analysis tool is used to verify, select and filter the final design. The Genetic Algorithms and Multi-start gradient line search optimizers are used to search the non- smooth design space. A geometry model for the supersonic missile inlet is developed. A supersonic missile inlet which starts at Mach 2.6 and cruises at Mach 4 was designed. Significant improvement of the inlet total pressure recovery has been obtained. Detailed flow field analysis is also presented.

Original languageEnglish (US)
Pages1355-1371
Number of pages17
DOIs
StatePublished - 1996
Externally publishedYes
Event6th AIAA/NASA/ISSMO Symposium on Multidisciplinary Analysis and Optimization, 1996 - Bellevue, United States
Duration: Sep 4 1996Sep 6 1996

Other

Other6th AIAA/NASA/ISSMO Symposium on Multidisciplinary Analysis and Optimization, 1996
Country/TerritoryUnited States
CityBellevue
Period9/4/969/6/96

ASJC Scopus subject areas

  • Aerospace Engineering
  • Mechanical Engineering

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