Enhancement of aircraft cabin comfort studies by coupling of models for human thermoregulation, internal radiation, and turbulent flows

Scientific enhancement of the analysis of thermal comfort aspects in aircraft cabins is the subject of the current investigation. For this purpose, three important processes are identified that play a significant role in thermal comfort, viz. the human response to its thermal environment which is also known as thermoregulation, the actual...

A study of grid convergence issues for the simulation of the massively separated flow around a stalled airfoil using DES and related methods

A systematic grid convergence study is conducted for the Detached-Eddy Simulation (DES) of the massively separated flow around a NACA0021 airfoil at high angle of attack. In order to study the convergence characteristics of DES/LES problems, velocity fields using a series of grids must be generated that demonstrate sufficient dynamic similarity...

A Symmetry and Dispersion-Relation Preserving High-Order Scheme for Aeroacoustics and Aerodynamics

A new high-order, finite-volume scheme is presented that preserves the symmetry property and the dispersion relation of the convective operator. The scheme is applied to large-eddy simulation of compressible, turbulent flow and to the solution of the linearized Euler equations for aeroacoustic applications. For large-eddy simulation, the...

Development of numerical algorithms for end-user applications in aerospace

In this paper, a cross-section of numerical algorithm development at NLR for end-user applications in aerospace is presented. Aerospace is characterized by high safety requirements and standards, complex development programs and operational processes, and challenging multi-physics phenomena. An example is the certification or qualification of...

A Simple, Robust and Fast Algorithm to Compute Deformations of Multi-Block Structured Grids

A grid deformation method has been developed for the movement of multiblock, structured grids due to surface deformation arising from aeroelastics or design optimisation. The method uses a volume spline interpolation technique to compute the deformation of block vertices and block edges. After that, the deformation of block-faces is computed by...

Computations of three-dimensional unsteady supersonic cavity flow to study the effect of different downstream geometries

Computations of three-dimensional unsteady supersonic cavity flow are performed for a freestream Mach number of 1.2. Two cavity geometries are considered: (i) a simple rectangular cavity of length-to-depth (L/D) and length-to-width (L/W) ratios of 4.5, and (ii) a cavity with a 45° ramp attached to the downstream wall of the simple rectangular...

Leading edge vortex flow computations and comparison with DNW-HST wind tunnel data

Computations are presented for the vortical flow around a sharp-edged cropped delta wing with 65° leading edge sweep using a computational method based on the Reynolds-averaged Navier-Stokes equations. It is demonstrated that turbulence modelling plays a crucial role in the ability to capture the vortical structures. Standard one- and two...

An Industrially applicable solver for compressible, turbulente flows