Automated Optimization of Two Dimensional High Speed Missile Inlets

ثبت نشده
چکیده

Certain fonts that you requested in your dvi file could not be found on the system. In order to print your document, other fonts that are installed were substituted for these missing fonts. Below is a list of the substitutions that were made.

برای دانلود رایگان متن کامل این مقاله و بیش از 32 میلیون مقاله دیگر ابتدا ثبت نام کنید

ثبت نام

اگر عضو سایت هستید لطفا وارد حساب کاربری خود شوید

منابع مشابه

AIAA 99-2108 Three Dimensional Optimization of Supersonic Inlets

An innovative design methodology has been implemented and used to address the intricate exercise of high speed inlets design. An eecient and robust process allows to optimize the aerodynamic performance of inlets. This optimization process links together an optimizer with a fast and accurate simulation tool into an automated optimization loop. This paper presents the implementation of these new...

متن کامل

Automated Optimal Design Using CFD and High Performance Computing

The advent of high performance computing has led to an increased role of CFD in automated optimal design, particularly in aeronautics. This paper presents a brief description of the optimization problem, strategies for its solution, algorithms for optimization, references to recent applications, impact of high performance computing and parallelization, and two examples of application to the des...

متن کامل

Automated Design Optimization for the P2 and P8 Hypersonic Inlets

An automated design methodology incorporating industry-standard Navier – Stokes codes and a gradient-based optimizer has been developed. This system is used to redesign the well-known NASA P2 and P8 hypersonic inlets. First, the Navier – Stokes simulations of the original P2 and P8 inlet designs are validated using numerical convergence studies and comparison with wind-tunnel experimental data ...

متن کامل

Optimal Trajectory Study of a Small Size Waverider and Wing-Body Reentry Vehicle at Suborbital Entry Speed of Approximately 4 km/s with Dynamic Pressure and Heat Rate Constraint

A numerical trajectory optimization study of two types of lifting-entry reentry vehicle has been presented at low suborbital speed of 4.113 km/s and -15 degree entry angle. These orbital speeds are typical of medium range ballistic missile with ballistic range of approximately 2000 km at optimum burnout angle of approximately 41 degree for maximum ballistic range. A lifting reentry greatly enha...

متن کامل

Scientific Flow Field Simulation of Cruciform Missiles Through the Thin Layer Navier Stokes Equations

The thin-layer Navier-Stokes equations are solved for two complete missile configurations on an IBM 3090-200 vectro-facility supercomputer. The conservation form of the three-dimensional equations, written in generalized coordinates, are finite differenced and solved on a body-fitted curvilinear grid system developed in conjunction with the flowfield solver. The numerical procedure is based on ...

متن کامل

ذخیره در منابع من


  با ذخیره ی این منبع در منابع من، دسترسی به آن را برای استفاده های بعدی آسان تر کنید

عنوان ژورنال:

دوره   شماره 

صفحات  -

تاریخ انتشار 1998