Field and depot maintenance : magnetos, ignition, assemblies, 2920-593-6456 and 2920-640-7743 (American Bosch types MRE6A43 and MRE6A41), end item application, engine, gasoline, 6-cylinder, continental models AOI-402-5 ... 12-cylinder, continental models AV-1790-5B ....

"April 1959."

The resistance of the air and aviation experiments conducted at the Champ-de-Mars laboratory,

Mode of access: Internet.

NASA technical report.

Description based on: R-180; title from cover.

The slow motion of a permanently magnetized sphere in an electrically conducting medium,

"Research supported by the McDonnell Aircraft Corporation under Contract no. 6140-20 P.O. 7S4899-R and by the Purdue Research Foundation."

Airborne simulation for the SST.

Cover title.

On the use of impact theory for slender configurations exhibiting flow separation /

Photocopy.

Quasi-three-dimensional supersonic viscid/inviscid interactions including separation effects : final report for period, 1 October 1972- 30 September 1975 /

Bibliography: p. 77-83.

Nonsteady discharge of subcritical flow /

At head of title: Project SQUID, a cooperative program of fundamental research as related to jet propulsion, Office of Naval Research, Department of the Navy. Contract Nonr 1858 (25), NR-098-038.

Investigation of small surface protuberances upstream of turbulent boundary layer separation produced by a skewed shock wave at Mach 3 /

"Interim report for period January 1976-February 1976."

A new method for providing continuous high-temperature air flow for hypersonic research,

"AFOSR-TN-56-236."

Study of hypersonic contaminated wake by an exact numerical solution.

"Work performed under contract DA-30-069-ORD-1955, administered by Bell Telephone Laboratories, Whippany, N. J."

Comparison of turbulent wake characteristics with different eddy viscosity coefficients,

At head of title: Space Sciences Laboratory. Aerophysics Section.

Parametric Optimization of Inductively Driven Liner Compression Driver System

Thesis (Master's)--University of Washington, 2016-06

Experimental tests of quantum nonlinear dynamics in atom optics

Cold atoms in optical potentials provide an ideal test bed to explore quantum nonlinear dynamics. Atoms are prepared in a magneto-optic trap or as a dilute Bose-Einstein condensate and subjected to a far detuned optical standing wave that is modulated. They exhibit a wide range of dynamics, some of which can be explained by classical theory while other aspects show the underlying quantum nature of the system. The atoms have a mixed phase space containing regions of regular motion which appear as distinct peaks in the atomic momentum distribution embedded in a sea of chaos. The action of the atoms is of the order of Planck's constant, making quantum effects significant. This tutorial presents a detailed description of experiments measuring the evolution of atoms in time-dependent optical potentials. Experimental methods are developed providing means for the observation and selective loading of regions of regular motion. The dependence of the atomic dynamics on the system parameters is explored and distinct changes in the atomic momentum distribution are observed which are explained by the applicable quantum and classical theory. The observation of a bifurcation sequence is reported and explained using classical perturbation theory. Experimental methods for the accurate control of the momentum of an ensemble of atoms are developed. They use phase space resonances and chaotic transients providing novel ensemble atomic beamsplitters. The divergence between quantum and classical nonlinear dynamics is manifest in the experimental observation of dynamical tunnelling. It involves no potential barrier. However a constant of motion other than energy still forbids classically this quantum allowed motion. Atoms coherently tunnel back and forth between their initial state of oscillatory motion and the state 180 out of phase with the initial state.

Three-component force measurements on a large scramjet in a shock tunnel

A stress-wave force balance for measurement of thrust, lift, and pitching moment on a large scramjet model (40 kg in mass, 1.165 in in length) in a reflected shock tunnel has been designed, calibrated, and tested. Transient finite element analysis was used to model the performance of the balance. This modeling indicates that good decoupling of signals and low sensitivity of the balance to the distribution of. the load can be achieved with a three-bar balance. The balance was constructed and calibrated by applying a series of point loads to the model. A good comparison between finite element analysis and experimental results was obtained with finite element analysis aiding in the interpretation of some experimental results. Force measurements were made in a shock tunnel both with and without fuel injection, and measurements were compared with predictions using simple models of the scramjet and combustion. Results indicate that the balance is capable of resolving lift, thrust, and pitching moments with and without combustion. However vibrations associated with tunnel operation interfered with the signals indicating the importance of vibration isolation for accurate measurements.