"The lateral-directional-stability derivatives of a body in combination with several triangular wings were determined at subsonic and supersonic speeds. The wings used in the investigation were of aspect ratios 2 and 4 and thickness ratios of 3 and 5 percent. One of the wings of aspect ratio 2 was cambered and twisted. The results indicate that at supersonic speeds the effects of plan form on the lateral-directional-stability derivatives for the plane wings were predicted satisfactorily by linearized theory and that the effects of thickness were small" (p. 1).

Report presenting an investigation in the transonic tunnel to determine the effects of varying Reynolds number on the pressure distribution on a transonic body of revolution at angles of attack through the transonic speed range. The effect of change in sting cone angle on the pressure distributions and a comparison of experimental incremental pressures with theory is also provided.

Report discussing an investigation of two 45 degree swept blades in low-speed cascade tunnels at a range of angles of attack and various combinations of inlet-air angle and solidity. The isolated wing method used to design the blade predicted the twist distribution and camber shape necessary to obtain an almost uniform spanwise loading.

Report presenting testing of a configuration with a body of fineness ratio 16.6, an unswept horizontal tail of aspect ratio 2.7, and a highly swept vertical tail, which were aeropulsed continuously in pitch during free flight with and without a sustainer rocket motor operating. Results regarding the pitching response, cross coupling, sustainer motor, angle of attack at zero normal force and tail flip, model aerodynamic center, induced jet effect are provided.

A theoretical analysis is presented for obtaining, by use of Theodorsen's propeller theory, the load distribution along a propeller radius to give the optimum propeller efficiency for any design condition. The efficiencies realized by designing for the optimum load distribution are given in graphs, and the optimum efficiency for any design condition may be read directly from the graph without any laborious calculations. Examples are included to illustrate the method of obtaining the optimum load distributions for both single-rotating and dual-rotating propellers.

From Summary: "A theoretical analysis is presented that permits estimation of the changes in piston-temperature distribution induced by variations in the crown thickness, the ring-groove-pad thickness, and the undercrown surface heat-transfer coefficient. The analysis consists of the calculation of operating temperatures at various points in the piston body on the basis of the experimentally determined surface heat-transfer coefficients and boundary-region temperatures, as well as arbitrarily selected surface coefficients."

Report presenting an investigation to determine the effects of taper ratio, body indentation, fixed transition, and afterbody shape on the transonic aerodynamic characteristics of a 45 degree sweptback wing-body combination with an aspect ratio of 4. Results were obtained at a variety of Mach numbers, angles of attack, and Reynolds numbers. Drag, lift, and stability characteristics are provided.

Report presenting tests conducted on models with 45 degree sweptback wings with varying degrees of flexibility to determine the effective lift-curve slopes in order to evaluate the usefulness of a general method for predicting effective lift ratio by a comparison of predicted values with test results.

Report presenting an investigation in the transonic tunnel to study the effects of body indentation and afterbody shape on the aerodynamic characteristics of an unswept-wing-body combination. Body indentation for a boattail configuration resulted in a considerable reduction in drag up to the highest lift coefficients tested. Results regarding the lift and pitching-moment characteristics are also provided.

"Dynamic yawing effects on vertical-tail loads are considered by a theory of flat yawing maneuvers. A comparison is shown between computed loads and the loads measured in flight on a fighter airplane. The dynamic effects were investigated on a large flying boat for both an abrupt rudder deflection and sinusoidal rudder deflection" (p. 91).

Report presenting a supersonic wind-tunnel investigation of the origin and distribution of store interference in the 4- by 4-foot supersonic pressure tunnel at Mach number 1.61. Separate forces on a store, a swept wing, and a swept-wing-fuselage combination were measured. This report presents data on a configuration that simulated a fighter-bomber airplane with a large and a small external store.

Report presenting an investigation with the objective of eliminating destabilizing changes of pitching moment through the use of wing modifications for two airplane models with triangular wings of aspect ratio 2 and 3. Models were tested with horizontal tails above the extended wing chord plane and with the tail off.

This report is a compilation of many of the pertinent research data acquired by the National Advisory Committee for Aeronautics on fuel performance in piston engines. The original data for this compilation are contained in many separate NACA reports which have in the present report been assembled in logical chapters that summarize the main conclusions of the various investigations. Complete details of each investigation are not included in this summary; however, such details may be found, in the original reports cited at the end of each chapter.

Report discussing factors influencing flight range and aerodynamic heating for hypersonic boost-glide aircraft. The possibility and advantages of flight at very high altitude to reduce aerodynamic heating and encourage the preservation of laminar flow on the surface of the aircraft is explored.

Report gives an account of an investigation conducted to determine the feasibility of artificially thickening a turbulent boundary layer on a flat plate. A description is given of several methods used to thicken artificially the boundary layer. It is shown that it is possible to do substantial thickening and obtain a fully developed turbulent boundary layer, which is free from any distortions introduced by the thickening process, and, as such, is a suitable medium for fundamental research.

The methods used to prepare and purify 19 hydrocarbon derivatives of cyclopropane are discussed. Of these hydrocarbons, 13 were synthesized for the first time. In addition to the hydrocarbons, six cyclopropylcarbinols, five alkyl cyclopropyl ketones, three cyclopropyl chlorides, and one cyclopropanedicarboxylate were prepared as synthesis intermediates. The melting points, boiling points, refractive indices, densities, and, in some instances, heats of combustion of both the hydrocarbon and nonhydrocarbon derivatives of cyclopropane were determined. These data and the infrared spectrum of each of the 34 cyclopropane compounds are presented in this report. The infrared absorption bands characteristic of the cyclopropyl ring are discussed, and some observations are made on the contribution of the cyclopropyl ring to the molecular refractions of cyclopropane compounds.

Memorandum presenting a corrosion investigation conducted with molten sodium flowing at a velocity of 25 feet per second in a toroid of AISI type 347 stainless steel with an insert consisting of seven Globeiron tubes in parallel at the hot zone. A 500-hour test was run at a nominal outer wall temperature of 500 degrees Fahrenheit with a temperature difference between the hot and cold sections of 40 degrees.

From Summary: "A matrix method is presented for determining the longitudinal-stability coefficients and frequency response of an aircraft from arbitrary maneuvers. The method is devised so that it can be applied to time-history measurements of combinations of such simple quantities as angle of attack, pitching velocity, load factor, elevator angle, and hinge moment to obtain the over-all coefficients. Although the method has been devised primarily for the evaluation of stability coefficients which are of primary interest in most aircraft loads and stability studies, it can be used also, with a simple additional computation, to determine the frequency-response characteristics. The entire procedure can be applied or extended to other problems which can be expressed by linear differential equations."

"In the development of high temperature materials of the brittle category, the need to improve their impact strength for some applications has brought with it a demand for a simple machine for measuring impact resistance, both at room and elevated temperatures, and preferably one in which corrections such as the toss energy are negligible. This report describes such a machine and presents the results of some preliminary tests on the effect of temperature on impact strength of several alloys and cermets. A comparison is also given between the impact resistance of notched and unnotched specimens" (p. 1).

"The method of superposition of linearized conical flows has been applied to the calculation of the aerodynamic properties, in supersonic flight, of thin flat, swept-back wings at an angle of attack. The wings are assumed to have rectilinear plan forms, with tips parallel to the stream, and to taper in the conventional sense. The investigation covers the moderately supersonic speed range where the Mach lines from the leading-edge apex lie ahead of the wing" (p. 1147).

Report presenting experimental results showing the static longitudinal-stability and -control characteristics of a model of a fighter airplane with a low-aspect-ratio unswept wing and an all-movable horizontal tail. The investigation was made over a Mach number range from 0.60 to 0.90 and from 1.35 to 1.90. Results regarding the pitching moment at zero lift, longitudinal stability, and longitudinal control are provided.

From Summary: "An investigation was made in the Langley low-turbulence pressure tunnel to determine the effect of size and location of a sandpaper type of roughness on the Reynolds number for transition. Transition was observed by means of a hot-wire anemometer located at various chordwise stations for each position of the roughness. These observations indicated that when the roughness is sufficiently submerged in the boundary layer to provide a substantially linear variation of boundary-layer velocity with distance from the surface up to the top of the roughness, turbulent "spots" begin to appear immediately behind the roughness when the Reynolds number based on the velocity at the top of the roughness height exceeds a value of approximately 600. At Reynolds numbers even slightly below the critical value (value for transition), the sandpaper type of roughness introduced no measurable disturbances into the laminar layer downstream of the roughness. The extent of the roughness area does not appear to have an important effect on the critical value of the roughness Reynolds number."

Report presenting an investigation of an annular nose inlet equipped with a remotely controlled translating spike and variable bypass in the supersonic wind tunnel. The inlet performance was explored with the airflow controlled by an operating J34 engine and with the engine simulated by a choked plug. Results regarding the performance of the inlet, corrective action that should be applied to avoid pulsing, performance of the subsonic portion of the diffuser, supersonic performance, radial-flow profiles, and other flow profiles are provided.

Report presenting information on the engine performance variations resulting from bleeding air from the compressor for turbine cooling, which is currently lacking. A thermodynamic-cycle investigation was conducted to determine the magnitude of the performance variations for a wide range of operating conditions for turboprop engines and for both afterburning and nonafterburning turbojet engines.