White Paper | Aerodynamic Design Best Practices Using PowerFlow and modeFRONTIER optimization
The example in this paper is an aerodynamic guidance study of a generic SUV-type vehicle. The goal was to understand the impact of rear end design changes to provide guidance for achieving minimized drag, while also considering rear lift and side force fluctuations. The project was conducted on ExaCLOUD, which provided secure, web-based access to the complete Exa simulation software suite and modeFRONTIER.
Lucid Motors boosts electric vehicle performance with modeFRONTIER
Lucid Air prototypes are undergoing a rigorous development program. modeFRONTIER has been used - together with other applications - to optimize the design of an inverter with the aim of enhancing efficiency and minimize failure rates.
Knowledge-Based Integrated Aircraft
A multidisciplinary optimization framework connecting the geometric model, aerodynamic model and structural model is performed on a wing shape with predefined loads on the wing. For global optimization, MOGA is used and for local optimization Simplex algorithm is used as the design variables are continuos.
Formulation and optimization of involute spur gear in external gear pump
These analytical expressions are then used within a multi-objective numerical optimization algorithm aimed at minimizing both the ﬂow non-uniformity and the pump size to achieve a speciﬁc displacement.
ESTECO webinar recording | RELIABILITY BASED ROBUST DESIGN OPTIMIZATION OF A FREE-FALL-LIFE-BOAT
The webinar focuses on a reliability-based optimization method to statistically increase the safety of free fall lifeboats, which are typically used to evacuate passengers in oil platforms and large transport vessels.
Novel cost effective configurations of combined power plants for smalls scale cogeneration from biomass design of the particle heat exchanger
A general design procedure have been developed for the application of the Immersed Particle Heat Exchanger to a novel, small scale, externally fired combined cycle capable of generating electrical and thermal power from carbon-neutral biomass. The Immersed Particle Heat Exchanger serves as the high temperature heat exchanger needed to couple the Brayton cycle with an external combustor of biom
Planform Dependency of Optimum Supersonic Airfoil for Wing-Body-Nacelle Configuration Using Multi-Fidelity Design Optimization
In this paper, supersonic wing design problems for supersonic transport (SST) with integrated engine intake and nacelle was discussed to obtain design knowledge of a supersonic airfoil with respect to wing planform dependency for a realistic configuration. Optimum wing designs were analyzed considering the interference between the engine intake, the nacelle, and the wing for two different planforms using a multi-fidelity design method.
Optimization of High lift device system deployment for takeoff performance
This work presents a proposed framework intended to be used for the optimization of highlift devices, namely Flaps and Slats for the present study. This paper addresses a first phase of a work aimed at a complete tool of high lift devices using modeFRONTIER as the optimizer in the process. The study takes into account the experience of a company inserted in the aeronautical environment and of the databases constituted from old aircraft.
Development of a Multidisciplinary Design Optimization Framework Applied on UAV Design by Considering Models for Mission, Surveillance, and Stealth Performance
This paper presents a Multidisciplinary Design Optimization (MDO) framework that is intended to be employed in the early design stages of Unmanned Aerial Vehicles (UAVs). A development approach for modeling the sensor performance and the radar signature is proposed and it is shown that their integration in a framework which also takes into account the geometry, the aerodynamics, the stability, and the mission simulation is feasible.
Aircraft conceptual design of a business jet (category Large) using Multidisciplinary Design Optimization techniques
A Multidisciplinary Design Optimization approach considering closed-loop flight control laws was applied to a conceptual design of a large-cabin business jet. The optimization algorithm used in this work is the Multi-Objective Genetic Algorithm of second generation (MOGA-II algorithm) using modeFRONTIER. Two types of analysis were done: mono-objective, maximizing the internal rate of return, and multi-objective, maximizing the internal rate of return and minimizing Dubai – London City mission block time.