Engineering topics

Caruso, Steven C.

Publications and source records attributed to Caruso, Steven C..

4 records

NASA NTRS1993

LEWICE droplet trajectory calculations on a parallel computer

A parallel computer implementation (128 processors) of LEWICE, a NASA Lewis code used to predict the time-dependent ice accretion process for two-dimensional aerodynamic bodies of simple geometries, is described. Two-dimensional parallel droplet trajectory calculations are performed to demonstrate the potential benefits of applying parallel processing to ice accretion analysis. Parallel performance is evaluated as a function of the number of trajectories and the number of processors. For comparison, similar trajectory calculations are performed on single-processor Cray computers, and the best parallel results are found to be 33 and 23 times faster, respectively, than those of the Cray XMP and YMP.

Caruso, Steven C.↗

NASA NTRS1992

Automatic grid generation for iced airfoil flowfield predictions

This paper describes a flowfield mesh generation procedure which has been developed specifically for dealing with geometrically complex and time-dependent leading edge ice accretions on airfoils. The method produces an unstructured mesh using an automatic node point generation scheme that requires minimal user input. Flowfield predictions are obtained by solving the Navier-Stokes equations on an unstructured, triangular mesh. Laminar and turbulent flowfield calculations are presented which demonstrate the new method's ability to produce suitable meshes for such computations.

Caruso, Steven C.↗

NASA NTRS1990

Development of an unstructured mesh/Navier-Stokes method for aerodynamics of aircraft with ice accretions

An advanced flowfield prediction method for airfoils with leading edge ice accretions was developed and applied. The method is intended to be eventually used in an aircraft icing analysis. The flowfield is obtained by solving the Euler or Navier-Stokes equations on an unstructured triangular mesh. A new method has been developed to permit efficient mesh generation while providing high grid resolution near complicated airfoil ice accumulations. Unstructured-mesh Euler calculations are presented for clean and iced airfoils; the results are compared to similar structured-mesh calculations to demonstrate the new method's accuracy and efficiency.

Caruso, Steven C.↗

NASA NTRS1987

Concepts for radically increasing the numerical convergence rate of the Euler equations

Integral equation and finite difference methods have been developed for solving transonic flow problems using linearized forms of the transonic small disturbance and Euler equations. A key element is the use of a strained coordinate system in which the shock remains fixed. Additional criteria are developed to determine the free parameters in the coordinate straining; these free parameters are functions of the shock location. An integral equation analysis showed that the shock is located by ensuring that no expansion shocks exist in the solution. The expansion shock appears as oscillations in the solution near the sonic line, and the correct shock location is determined by removing these oscillations. A second objective was to study the ability of the Euler equation to model separated flow.

Nixon, David↗