An analysis is presented whereby the free-space oscillating pressures associated with a rotating propeller may be determined at any point in space. This analysis is based on the fundamental Gutin equations without some of the simplifying assumptions. Static tests for several different propellers were conducted in the tip Mach number rang 0.45 to 1.00. Charts are given for estimating free-space pressures for a given propeller. The response of the fuselage to these oscillating pressures is also treated and some factors to be considered in solving the problems of fuselage vibration and noise are indicated.

Measurements of free-space oscillating presssures near a static propeller in the region where a wing might be located are presented for the tip Mach number range of 0.50 to 1.20 and these results are compared with available theory. Some measurements are also presented which were made near the tipes in the region where a fuselage might be located in order to extend the range of existing data from a tip Mach number of 1.00 to 1.20. In addition to a description of the free-space pressure field, meausrements are given from some of the same field points with a wing in place.

Room-temperature stress-strain curves are presented for compression, tension, and shear loadings of four compositions of titanium carbide with nickel binder. Values of ultimate strength, modulus of elasticity, modulus of rigidity, Poisson's ratio in the elastic region, density, and hardness for the four materials are tabulated.

In transpiration cooling of various structural elements in gas turbines, the coolant has to be ducted within passages to the porous walls through which it is ejected into the gas stream. The passages, often arranged in rotating parts, have to be designed in such a way as to ensure the proper local distribution of the coolant. In this report, a method is presented by which either the local permeability can be predicted. The method is based on a one-dimensional treatment of the gas flow through a rotating channel with varying cross section and partially porous walls. The inlet pressure into the channel and the outside pressure along it are assumed prescribed. It is also stipulated that the passage ends blindly. However, the method can easily be extended to cover the situation where a certain mass flow leaves the open end of the passage.