Skip to Content
Our misssion: to make the life easier for the researcher of free ebooks.

Aerospace and Ocean Engineering Ebooks

Environmental Friendly Transport Aircraft

Almost all scenarios for the development of air traffic show that a further growth of transport capacity can be anticipated in the future. Solutions to handle the increased traffic are constrained by economical and environmental issues which may lead to quite different or even completely new aircraft configurations. In the past, it was tried to minimize the environmental impact after the configuration had already been developed mainly based on cost and performance requirements. In the future, environmental issues will have a stronger influence at the component level, but also on the arrangement of the aircraft components and thus on the configurations. Increased transport capacity can be provided by:
1. increasing the number of aircraft,
2. reducing the turn around time at the airport and separation between flights,
3. enlarging the aircraft capacity, and
4. increasing the cruise speed of aircraft.

A two-parameter wind tunnel rigging system

In January of 1935, definite steps were taken in a two part program to modernize the ten-foot wind tunnel of the Guggenheim Aeronautical Laboratory at the California Institute of Technology. Part one of the program was the design and construction of a new wind tunnel rigging system based on concepts originally laid down by Dr. A. L. Klein, Associate Professor at the same institution. Part two of the program, to be carried on intensively immediately after completion of part one, will be the development of an entirely new force measuring system to replace the present modified steelyard type balances.

The R-F thermal radiation from the sun

With the "velocity distribution" method of the kinetic theory of gas the mean number of collisions per second between the particles is found. From this the absorption coefficient for the radiation is obtained. For the intensity of the emitted radiation the equation of transfer is solved in a three dimensional medium. In the solution the emissivity is eliminated by means of a modified form of Kirchhoff's law of radiation where the index of refraction is generalized to include absorption as well. For the path of the rays the equation of the iconal of geometrical optics is considered in a refracting and absorbing medium. The solution does not exhibit the phenomenon of total reflection, present in purely refracting media.

On the burning of single drops of monopropellants

A simplified theoretical treatment has been developed for the burning of single drops of monopropellants. Evaporation constants and the ratios of flame to droplet radii have been calculated for the following monopropellants burning in an inert atmosphere: hydrogen peroxide, nitromethane, hydrazine, ethylene oxide, ozone and nitrous oxide. Compared with the results of similar calculations for fuels burning in air, much smaller flame radii were obtained, while the evaporation constants were found to fall in the same range as before.

Magnetohydrodynamic surface waves

This is an experimental and theoretical study of deep water gravity-like waves which are induced in a liquid metal by a changing magnetic field. The dominant feature of such waves is the emission of Alfven waves from the free surface. A linearized theory is derived and compared with experiments.

Characteristics of propagating stall in axial-flow compressors

Both small and large amplitude propagating stalls have been observed experimentally and their characteristics distinguished. The characteristics of the small amplitude propagating stall are such that the phenomenon can be described well by linearized theory. The characteristics of the large amplitude stall (which is the propagating stall phenomenon generally found in compressors) are such that the linearized theory is not adequate to describe the stall.

An experimental study of a turbulent vortex ring

An apparatus has been constructed to study the formation and dynamics of vortex rings. The rings are formed in water by a momentary jet discharge downward into a glass tank from an orifice in a submerged plate. The necessary impulse is provided by a pressurized reservoir and is controlled by a fast programmable solenoid valve.

Airplane takeoff performance

In this paper a general equation for calculating the takeoff performance of landplanes is developed in terms of the usual airplane parameters.

The analysis enables the ground effect, wind and atmospheric conditions, altitude, and the use of flaps to be taken into account. A simple and rapid method is presented for the determination of the best flap angle to be used for takeoff.

Aerodynamic control and mixing with ramp injection

Experiments have been conducted in the GALCIT Supersonic Shear Layer Facility (S3L) to investigate the behaviour of a flow and geometry with many features that are potentially useful for a Supersonic Combustion Ramjet (SCRAMJET) engine - a recirculation zone for flameholding, enhanced mixing between fuel and air, and low total-pressure losses. In a subsonic diffuser configuration with no mass injection, the exit velocity and guidewall static-pressure profiles collapse over a large range of inlet Reynolds numbers. Significant control of exit velocity and guidewall pressure profiles is possible via injection through a perforated ramp into the freestream. The control authority on the overall pressure coefficient increases with increasing inlet Reynolds number. Simple control volume models put bounds on the overall pressure coefficient for the device.

Supersonic diffuser instability

Steady operation of supersonic diffusers near critical mass flow is interrupted by a transient process known as buzz. This phenomenon consists of a random sequence of individual relaxation cycles. Mass flow entering the diffuser during steady operation is suddenly cut off by a strong interaction between the subcritical shock and boundary layer on the surface of the external compression generator, which blocks the inlet. Air in the plenum chamber, stored at high pressure, then ?blows down? until the inlet can restart. The subsequent supercritical flow entering the diffuser exceeds the flow rate at the exit and the plenum chamber is re-charged to the original condition.

Syndicate content