Buffet-Onset Constraint Formulation for Aerodynamic Shape Optimization

Peer Reviewedhttps://deepblue.lib.umich.edu/bitstream/2027.42/143072/1/1.J055172.pd

Aerodynamic Shape Optimization of the STARC-ABL Concept for Minimal Inlet Distortion

The NASA single-aisle turboelectric aircraft with an aft boundary layer propulsor (STARC-ABL) concept utilizes a novel electrically driven aft fan that ingests the fuselage boundary-layer for increased propulsive efficiency. In this paper we examine how aerodynamic shaping of the fuselage diffuser and nacelle inlet can reduce the flow distortion at the aft fan. Adjoint-based aerodynamic shape optimization with the ARP1420 distortion metric objective is used to automatically determine the optimal shapes for minimal fan-face distortion. Single and multipoint optimizations are carried out for simplified body-duct and wing-body-duct configurations. These two configurations highlight the importance of including the wing downwash effects when designing the propulsor. The optimizations showed the body-duct configuration can obtain cruise distortion values of approximately 1% while the wing-body-duct configuration can obtain distortion values of just over 2%

Multipoint Aerodynamic Shape Optimization Investigations of the Common Research Model Wing

Peer Reviewedhttps://deepblue.lib.umich.edu/bitstream/2027.42/140687/1/1.J054154.pd

Aerodynamic Shape Optimization Investigations of the Common Research Model Wing Benchmark

Peer Reviewedhttps://deepblue.lib.umich.edu/bitstream/2027.42/140684/1/1.J053318.pd

A Comparison of Metallic, Composite and Nanocomposite Optimal Transonic Transport Wings

Current and future composite material technologies have the potential to greatly improve the performance of large transport aircraft. However, the coupling between aerodynamics and structures makes it challenging to design optimal flexible wings, and the transonic flight regime requires high fidelity computational models. We address these challenges by solving a series of high-fidelity aerostructural optimization problems that explore the design space for the wing of a large transport aircraft. We consider three different materials: aluminum, carbon-fiber reinforced composites and an hypothetical composite based on carbon nanotubes. The design variables consist of both aerodynamic shape (including span), structural sizing, and ply angle fractions in the case of composites. Pareto fronts with respect to structural weight and fuel burn are generated. The wing performance in each case is optimized subject to stress and buckling constraints. We found that composite wings consistently resulted in lower fuel burn and lower structural weight, and that the carbon nanotube composite did not yield the increase in performance one would expect from a material with such outstanding properties. This indicates that there might be diminishing returns when it comes to the application of advanced materials to wing design, requiring further investigation

Multimission Aircraft Fuel-Burn Minimization via Multipoint Aerostructural Optimization

Peer Reviewedhttps://deepblue.lib.umich.edu/bitstream/2027.42/140677/1/1.J052940.pd

Scalable Parallel Approach for High-Fidelity Steady-State Aeroelastic Analysis and Adjoint Derivative Computations

Peer Reviewedhttps://deepblue.lib.umich.edu/bitstream/2027.42/140671/1/1.j052255.pd

Aerodynamic Shape Optimization of Common Research Model Wing–Body–Tail Configuration

Peer Reviewedhttps://deepblue.lib.umich.edu/bitstream/2027.42/140640/1/1.C033328.pd

Modeling Boundary Layer Ingestion Using a Coupled Aeropropulsive Analysis

Peer Reviewedhttps://deepblue.lib.umich.edu/bitstream/2027.42/143109/1/1.C034601.pd