With the availability and a ordability of unsteady computational uid dynamics (CFD) that includes grid motion, research has recently focused on exploiting CFD for computing the aero-dynamic derivatives in the above formulas.2{5 This work aims to determine the damping terms in Equation.

2016年10月9日 · In this paper a CFD simulation was carried out on ballistic missile with a new structure for determining the flight performance and the aerodynamic configuration.

2020年1月5日 · The present work focuses on the qualitative and quantitative validation of the computational fluid dynamics (CFD) solutions using two high-speed vehicle geometries. The first geometry studied is the high-supersonic NASA Tandem Canard Missile (TCM).

In this work a useful tool for analyzing the static and dynamic stability of missiles and rockets equipped with grid fins is presented. The proposed method, applicable to subsonic flows, is based on the use of the Doublet-Lattice Method combined with the “Unit Grid Fin” concept.

2010年10月26日 · Development of indigenous CFD codes and their applications for complex aerodynamic and propulsive flow problems pertaining to DRDO missiles are presented. Grid generators, 3D Euler and Navier Stokes solvers are developed in‐house using state of art numerical techniques and physical models.

Three dimensional CFD aerodynamic data fields enable also a complete flow field visualisation. The presentation shows a missile configuration with a wingless fuselage, canards and six tail stabilisers. The aerodynamic surfaces of the stabiliser have a pre-set incidence angle to produce a turning moment for the rolling airframe.

2024年3月1日 · The goal of the investigation in this article is to collect and compare data relating to the aerodynamic characteristics of CFD simulations of circular, square and triangular cross sectioned missiles designed at the U.S. Air Force Academy (USAFA) with nose and tail fins to assess the accuracy of computational methods and to understand how body ...

l fluid dynamics (CFD) throughout the missile development process. A suite of CFD codes is regularly used to predict the performance of conceptual missiles, support and supplement wind tunnel tests, aid in the development of flight-cr.

This report presents the results of the first viscous CFD calculations made involving a missile with grid fins. The results are validated by comparing them against wind tunnel data provided by DERA (Simpson 1997). Simulations of the missile body alone and with planar fins were also performed as part of the validation process. 2. Numerical Approach

Computational Fluid Dynamics (CFD) predictions are compared with the wind-tunnel tests for a missile consisting of ogive-nose cylindrical body, four wings and four in-lined tail panels at nominal supersonic Mach Nos. 2, 3, 4 and 5 and at angles-of-attack ranging from 0 to 35 deg with and without a lateral jet thruster with thrust ratios of 1 and 4.