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Adjoint-Based Mesh Adaptation and Shape Optimization for Simulations with PropulsionWe demonstrate a well-posed formulation of permeable boundary conditions and mass- flow-rate functionals for adjoint-based mesh refinement and shape optimization governed by the steady Euler equations. The boundary conditions are used to model propulsion- system effects of inlets and nozzles. A two-shock diffuser with an analytic solution is used to verify the implementation. Numerical examples show that the adjoint solution is smooth at the boundary, indicating that the discretization is adjoint consistent when exit pressure is specified at subsonic outflow, and stagnation temperature and pressure at subsonic inflow. The results focus on improving simulation techniques for low-boom aircraft analysis and design. By including mass-flow-rate outputs, we obtain reliable estimates of engine flow rates concurrently with nearfield pressure signatures without increasing simulation cost. We also demonstrate the importance of mass-flow-rate constraints in shape optimization by examining trade-offs between maximizing performance of a shrouded supersonic nozzle and minimizing shocks in its nearfield.
Document ID
20190026552
Acquisition Source
Ames Research Center
Document Type
Conference Paper
Authors
Nemec, Marian
(NASA Ames Research Center Moffett Field, CA, United States)
Rodriguez, David L.
(Science and Technology Corp. Moffett Field, CA, United States)
Aftosmis, Michael J.
(NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
June 23, 2019
Publication Date
June 20, 2019
Subject Category
Numerical Analysis
Report/Patent Number
ARC-E-DAA-TN69560
Meeting Information
Meeting: AIAA Aviation and Aeronautics Forum (Aviation 2019)
Location: Dallas, TX
Country: United States
Start Date: June 17, 2019
End Date: June 21, 2019
Sponsors: American Institute of Aeronautics and Astronautics (AIAA)
Funding Number(s)
CONTRACT_GRANT: NNA16BD60C
Distribution Limits
Public
Copyright
Public Use Permitted.
Technical Review
NASA Peer Committee
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