Memorandum presenting an investigation of coolant-flow rates for a turbine rotor blade with return-flow type of coolant-passage configuration formed by fins within a capped blade shell with both hydrogen and methane fuels as coolants. Results regarding spanwise blade and coolant temperature distributions, effects of coolant inlet temperature on hydrogen-coolant-flow requirements, comparison of return-flow-blade coolant requirements, effect of fin thickness and fin height, comparison of hydrogen and methane as coolants, and feasibility of fuel-cooled turbines are provided.

Memorandum presenting an experimental investigation of the cooling characteristics of a small air-cooled turbine blade for use in a turboprop engine in a static cascade facility. Three test blades were studiued at three combustion-gas temperatures. Results regarding gas-flow conditions in cascade test section, correlation of temperature data, and application of correlated data to the typical engine are provided.

Turbojet thrust augmentation with fuel-rich afterburning of hydrogen, diborane, and hydrazine was computed. Results regarding takeoff thrust augmentation and flight thrust augmentation are provided.

Memorandum presenting an investigation to determine the internal flow performance of a fixed 14 degree ramp inlet from zero to 20 degrees angle of attack conducted at three free-stream Mach numbers. The inlet was mounted in three circumferential fuselage locations and utilized inlet throat and fuselage boundary-layer removal.

"Flutter models of the upper and lower vertical tails of an air-to-ground missile have been tested in the Mach number range from 0.5 to 3.0. It was found that the upper surface exhibited more or less conventional flutter behavior throughout the Mach number range, whereas the lower surface experienced a sudden change in flutter mode at a Mach number of about 1.18. This change in flutter mode was accompanied by a decrease of about 50 percent in the density required for flutter to occur" (p. 1).

Report presenting lightweight design concepts, which were developed and tested in a full-scale turbine wheel with a tip diameter of 34.3 inches and a tip speed of 1190 feet per second. It consisted of a rotor of two thin alloy disks attached with spacers and bolts and hollow turbine blades. Testing indicated that it would be particularly applicable to an expendable missile engine.

Note presenting the incompressible boundary-layer theory of Truckenbrodt extended using a modified Stewartson-type transformation to include compressible boundary-layer development over insulated surfaces. The method is applicable to two-dimensional and axisymmetric, laminar and turbulent boundary layer, and accounts for the pressure gradient along the wall for both compressible and incompressible flow. Some experimental measurements of the boundary layer on small axisymmetric bodies on the wall of a supersonic wind tunnel compared with theoretical predictions.

Report presenting an analysis to ascertain the feasibility of using the device to produce high-temperature air. The production of high temperature is associated with the leakage of the hot outlet air through the tip clearance to the inlet and the subsequent mixing with the supply air. The calculated performance of the unit is very sensitive to the assumed value of Stanton number.

Note presenting results of several experimental investigations which indicate the effects of rapid heating on the bending strength of multiweb beams and ring-stiffened cylinders. Thermal stresses are shown to reduce the bending load carried at buckling by both beams and cylinders.

"The influence of joint conductivity and internal radiation on temperature distribution and thermal stresses has been discussed. Joints of poor conductivity can occur in normal fabrication procedure and greatly alter temperature distributions and increase thermal stresses. On the other hand, internal radiation tends to make the temperature distributions more uniform and thereby relieves thermal stress" (p. 1).

A simple and practical method for evaluating the onset of permanent buckling in plates in the presence of combined thermal and compressive load stresses is outlined. A particular application of the method shows reasonable agreement with tests of 17-7 PH stainless-steel square tubes. The results indicate that the compressive load stress which the plate can support at the onset of permanent buckling is substantially reduced as the temperature difference of the plate and adjoining members increases.

"Thermal stresses, which may result from transient heating, can cause changes in the effective stiffness of wing structures. Some effects of this change in stiffness were investigated experimentally by radiantly heating three types of simple wing structures: a uniform plate, a solid double-wedge section, and a circular-arc multiweb-wing section. Changes in stiffness were determined by measuring the changes in natural frequency of vibration during transient heating. Some comparisons are made between theoretical calculations and the measured data" (p. 1).

A brief review is presented of the basic methods of gust alleviation. Some results obtained in flight tests of a gust-alleviation system are included.

Note presenting an investigation of a straight outer-wall annular diffuser with a center-body length of one-half the outer-body diameter and an area ratio of 1.9:1 for mean inlet flow angles of 0 and 19.5 degrees in order to determine the effect of area suction applied on the inner wall. The entrance shape, number, and location of the openings through which the air was removed were varied. Results regarding inlet flow conditions, visual-flow observations with axial flow, performance with axial flow, and performance with whirling flow are provided.

"A theoretical study is made of the influence of tire hysteresis effects on the rolling motion and wheel shimmy of landing gears. The results of this study indicate that hysteresis forces and moments have a noticeable secondary influence on the landing-gear rolling behavior. Comparisons of the available experimental data with the corresponding theoretical predictions provide a fair confirmation of the theory" (p. 1).

A study of the effect of induction-vacuum-melting procedure on the high-temperature properties of a titanium-and-aluminum-hardened nickel-base alloy revealed that a major variable was the type of ceramic used as a crucible. Reactions between the melt and magnesia or zirconia crucibles apparently increased high-temperature properties by introducing small amounts of boron or zirconium into the melts. Heats melted in alumina crucibles had relatively low rupture life and ductility at 1,600 F and cracked during hot-working as a result of deriving no boron or zirconium from the crucible.

Results of an investigation at low speeds to determine the gust-alleviation capabilities (reduction in lift-curve slope) of spoilers and deflectors on a 35 degree swept-wing model of high aspect ratio and on a 1/4-scale model of the X-5 airplane with 35 degree swept wings indicate that deflector and spoiler-deflector types of controls can be designed to provide considerable gust alleviation for a swept-wing airplane while still maintaining stability and control.

Note presenting the equations for development of the compressible laminar boundary layer over a yawed infinite cylinder. The results indicate that the effect of yaw on the heat-transfer coefficient at the stagnation line depends markedly on the free-stream Mach number.

Note presenting a consideration of the equations of motion and energy for the laminar boundary layer flow in an expansion wave of finite width moving into undisturbed fluid, such as in a shock tube. Solutions in the form of infinite power series for velocity and local enthalpy functions were indicated and the first three terms of each series were numerically evaluated. Results regarding numerical information, a discussion of the results, a comparison with the solution of the zero-thickness expansion wave, and singularities in the flow field are provided.

"Separate investigations have dealt with the critical crack length of flat sheets or of unstiffened cylinders and with the type of rupture experienced by stiffened cylinders. These investigations are correlated, supplemented by new tests, and combined into a uniform scheme for predicting critical crack length and type of rupture in stiffened pressurized cylinders" (p. 1).

"The results of compressive-buckling tests of steel sandwich plates are given, and the significant parameters which affect the strength of the plates are discussed. The various types of sandwich construction are shown to be comparable on a weight-strength basis with conventional high-strength aluminum-alloy construction" (p. 1).

Note presenting the results of some theoretical and experimental investigations of delta-wing vibrations. Experimental nodal-line patterns and frequencies for a 60 degree thick-skin delta wing are shown. Comparisons of the different investigations have shown that the idealized-strucutre type of method as proposed by Levy gives excellent results for thin-skin wings provided that corrections are made for the effects of transverse shear.

Note presenting an investigation conducted in the high-speed 7- by 10-foot tunnel to determine the effects of varying the horizontal-tail position relative to the wing chord plane on the aerodynamic characteristics in pitch of a general research model having a 45 degree sweptback wing of aspect ratio 4, taper ratio 0.30, and NACA 65A006 airfoil sections. The investigation also included the effects of a wing modification consisting of a full-span leading-edge flap deflected 6 degrees and an outboard partial-span chord-extension.

Report presenting an investigation in the high-speed 7- by 10-foot tunnel using the transonic bump method to determine the gust-alleviation capabilities of spoilers and deflectors when mounted on a 35 degree swept semispan wing with NACA 65A006 airfoil sections. Testing was conducted over a range of Mach numbers and angles of attack.