Accession Number : AD1017208

Title :   Quasi-Steady Simulations for the Efficient Generation of Static Aerodynamic Coefficients at Subsonic Velocity

Descriptive Note : Technical Report,01 Dec 2014,01 Apr 2015

Corporate Author : US Army Research Laboratory Aberdeen Proving Ground United States

Personal Author(s) : Silton ,Sidra I

Full Text :

Report Date : 01 Sep 2016

Pagination or Media Count : 54

Abstract : A quasi-steady sweep procedure that allows determination of the static aerodynamic coefficients for a range of angles of attack in a single simulation is extended to subsonic Mach numbers. Given a steady-state solution, the procedure can be used to generate multiple numerical simulations over a select range of angles of attack for a given set of flight conditions using the time-accurate Reynolds-Averaged NavierStokes equations. Computational Fluid Dynamics simulations are completed for a canard-controlled, fin-stabilized projectile at Mach 0.65 for a moderate range of angles of attack using a quasi-steady sweep procedure. Separate steady-state solutions are also computed at various angles of attack for comparison. Comparison of the results showed that the quasi-steady sweep procedure can provide accurate static aerodynamic coefficients efficiently if convergence at each time step is ensured.

Descriptors :   aerodynamics , computational fluid dynamics , airframes , mach number , navier stokes equations , coefficients , flight , flow fields , velocity

Subject Categories : Military Aircraft Operations
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE