Airfoil design utilizing parallel processors. II-Applications

Presented as Paper 95-0126 at the 33rd Aerospace Sciences Meeting and Exhibit January 9-12,1995 / Reno, NVThe article of record as published may be found at https://doi.org/10.2514/6.1995-126One test case and two airfoil design applications were performed utilizing a parallel optimization scheme coupled to different fiow solvers. Parallel processors use computational fluid dynamics to evaluate the aerodynamic performance of multiple geometries simultaneously. The test case designed an airfoil to match the pressure distribution corresponding to an airfoil of a known shape. A transonic design application varied an airfoil's shape to maximize its lift-to-drag ratio

Aerodynamic Analysis and Design of High-Performance Sails

High-performance sails, such as the ones used on the America Cup boats, require sails whose aerodynamic characteristics approach those of rigid wings, yet permit a reduction in sail area in high wind and sea conditions. To this end, two-cloth sails are coming into use. These sails are constructed out of an articulated forebody that is a truncated ellipse, the aft of which has sail tracks, or rollers, along the edges to accommodate the twin sails. As the sails on either side need to be of the same length, due to the requirement to sail on different tacks, the two cloth sections need to be of equal length. The requirement then is to have their clews separated and able to slide over each other. More importantly, the transition between the rigid mast section and sails needs to be as aerodynamically smooth as possible in order to reduce drag and hence maximize the lift to drag ratio of the airfoil section that is made up of the mast and twin sails. A computational analysis using ANSYS CFX is presented in this chapter which shows that the aerodynamic characteristics of this type of two-cloth sail are almost as good as those of two-element rigid wing sections. Optimum sail trim configurations are analyzed in order to maximize the thrust production. Applications may soon extend beyond competitive sailing purposes for use on sailing ships equipped with hydrokinetic turbines to produce hydrogen via electrolysis (energy ships). Additionally, high performance sails can be used onboard cargo ships to reduce overall fuel consumption

Transonic Axial Compressor Design Tool

Approved for public release; distribution is unlimited.A new design procedure using commercially-off-the-shelf (COTS) software, MATLAB, SolidWorks and ANSYS-WorkBench (CFX and Mechanical) for the geometry generation and analysis of axial compressors.U.S. Army Research Laboratory, Mechanical Sciences Division ResearchU.S. Army Research Laboratory, Mechanical Sciences Divisio

Airfoil design utilizing parallel processors

The article of record as published may be found at https://doi.org/10.2514/3.46994An aerodynamic design scheme using parallel processors has been developed that significantly decreases the processing time required to optimize a desired performance. The parallel optimization scheme, when coupled with a flow solver, evaluates the aerodynamic performance of numerous geometries simultaneously.A test case was conducted utilizing the parallel optimization scheme and a similar sequential optimization scheme to design an airfoil to match the pressure distribution corresponding to a known shape. This design application demonstrates the practicality and versatility of aerodynamic design via optimization using parallel processors

Student Guide Curriculum 591

This document provides a guide to the resident Astronautical Engineering Degree Programs in the Department of Mechanical and Aerospace Engineering (MAE). Separate guides are available for distance learning programs, the Mechanical Engineering Program, and Doctoral Programs. Much of the information contained within is based on a standard 9-quarter 591 curriculum leading to a Master of Science in Astronautical Engineering (MSAE) and the 5500 subspecialty code. There are, however, students with programs of different lengths and this guide serves these students as well, with the necessary adjustment of the information provided. Regardless of duration, your academic program is tailored to you, and you should consult with the Program Officer and Academic Associate to ensure that your program meets your educational needs, the requirements of your sponsor and degree requirements. This guide provides information on educational objectives, degree requirements, thesis requirements, required paperwork, subspecialty code requirements (for Navy Officers), and planning your educational program. The MAE Department faculty and staff are here to help you succeed

Student Guide Curriculum 570

Welcome to the Department of Mechanical and Aerospace Engineering. This guide will help you with planning your academic program at NPS. While the guide is rather complete it is not totally proscriptive, and there can be room in some areas for variations that may better suit your personal educational objectives. So please take the guide in the spirit it was intended - as a guide - and not a complete, regimented set of absolute requirements. If you have questions, come ask us, we are here to support you

Doctoral Student Policy

Welcome to the Department of Mechanical and Aerospace Engineering. This guide will help you with planning your doctoral studies in the MAE Department at NPS. The PhD degree is the terminal degree in the American University System, and has special meaning for those in the field. It generally indicates that a person who holds this degree is a true expert and scholar in the field and has a great understanding in the literature and practice of their discipline

Optimization of Vertical Axis Wind Turbine Arrays

Energy Academic Group Science and Technology ProjectDoubling the number of blades from 3 to 6 gives a 2.3 times increase in torque. Running two (3-bladed) VAWTs inward at 1m part gives a less than one percent increase in combined torque. Bringing them closer to 0.5m increases the overall torque by 7

Optimal Control of Shock Wave Attenuation using Liquid Water Droplets with Application to Ignition Overpressure in Launch Vehicles

This paper presents the first solution of an optimal control problem concerning unsteady blast wave attenuation where the control takes the form of the initial distribution of liquid water droplets. An appropriate two-phase flow model is adopted for compressible homogeneous two-phase flows. The dynamical system includes an empirical model for water droplet vaporization, the dominant mechanism for attenuating the jump in pressure across the shock front. At the end of the simulation interval, an appropriate target state is defined such that the jump in pressure of the target state is less than that of the simulated blast wave. Given the nature of the non-linear system, the final time must also be a free variable. A novel control algorithm is presented which can satisfy all necessary conditions of the optimal system and avoid taking a variation at the shock front. The adjoint-based method is applied to NASA’s problem of Ignition Overpressure blast waves generated during ignition of solid grain rocket segments on launch vehicles. Results are shown for a range of blast waves that are plausible to see in the launch environment of the shuttle. Significant parameters of effective droplet distributions are identified.N. D. Moshman would like to thank Professors Chris Brophy, Frank Giraldo and Wei Kang at the Naval Postgraduate School and Bruce Vu at NASA Kennedy Space Center. In addition, N. D. Moshman thanks the Naval Postgraduate School and the Army Research Office for funding this research