by National Aeronautics and Space Administration, National Technical Information Service, distributor in [Washington, DC], [Springfield, Va .
Written in English
|Other titles||Three dimensional water droplet trajectory code validation using an ECS inlet geometry.|
|Statement||Marlin D. Breer and Mark P. Goodman.|
|Series||NASA contractor report -- 191097., NASA contractor report -- NASA CR-191097.|
|Contributions||Goodman, Mark P., United States. National Aeronautics and Space Administration.|
|The Physical Object|
Seven codes are described: 1. a code used to debi^ and plot body surface description data, 2. a code that processes the body surface data to yield the potential flow field, 3. a code that computes flow velocities at arrays of points in space, 4. a code that computes water drop trajectories from an array of points in space, 5. a code that. Three-dimensional numerical simulations of water droplet dynamics in a PEMFC gas channel Article in Journal of Power Sources (1) . applied to it. The importance of the inlet geometry and inlet conditions was pointed out in an experimental study by Kiock et al. () where the same blade shape was examined in four wind tunnels and it was shown that only two of the tunnels exhibited two-dimensional inlet flow. An AGARD report on test cases for. using boundary conditions within an inviscid Cartesian ﬂow solver is presented. This ap-proach couples with both CAD systems and legacy geometry to provide an automated tool suitable for parameter studies. The method is validated using two- and three-dimensional test problems which are compared with both theoretical and experimental results. The.
To increase the prediction speed of ice accretion on the 3D engine inlet, the Proper Orthogonal Decomposition (POD) method was introduced. Taking the ice shapes from CFD numerical calculation results as samples, in view of the change of icing temperature, the procedures of predicting the ice shapes by POD method were introduced, which used ice shapes’ Author: Xiao Bin Shen, Zuo Dong Mu, Gui Ping Lin, Yue Zhou. work is to develop a numerical code to analyze the scramjet inlet flow field. A two-dimensional code has been developed initially to gain under- standing of some features of the inlet flow. The two-dimensional Navier-Stokes equations in conservative . Diﬀerential geometry of immersed surfaces in three-dimensional normed spaces and for this theory we refer to the book . In this short section we brieﬂy explain the basic ideas and concepts; for proofs the reader can consult the mentioned book. A water tank is designed and installed in order to perform water entry tests. The tank dimensions are selected large enough such that the wall effects on the flow field are negligible, i.e. a cross section of × m 2 and 9 m long. A launching system for providing projectile velocity, a high speed camera, a lighting system, a computer for image processing, and the test tank are Cited by:
Intensive studies have been carried out on generations of waverider geometry and hypersonic inlet geometry. However, integration efforts of waverider and related air-intake system are restricted majorly around the X43A-like or conical flow field induced configuration, which adopts mainly the two-dimensional air-breathing technology and limits the judicious visions of Cited by: 6. prescribed using a suitable linear combination of the running time average (from zero to time t) of the inlet fluctuations and the fluctuating field at time t. The influence of different integral lengths, time scales and amplitudes of the turbulent inlet boundary conditions is investigated. The paper is organized as follows. The internal three-dimensional velocity field with transverse flow in droplet is revealed and analyzed in detail. When the substrate is hydrophobic, it is found that there is slight deformation but strong flow circulation inside the droplet, and the droplet rolling is Cited by: We present a three-dimensional numerical simulation of the aerobreakup of a spherical water droplet in the ﬂow behind a normal shock wave. The droplet and surrounding gas ﬂow are simulated using the compressible multicomponent Euler equations in a ﬁnite-volume scheme with shock and interface capturing. The aerobreakup.