This report contains a selected list of Government sponsored research projects on related aircraft materials in effect during the calendar year 1947. Information is contained on titles, description, sponsoring and conducting agencies.

"An investigation at medium to high subsonic speeds has been conducted in the Langley low-turbulence pressure tunnel to determine the static stability and control characteristics and to measure the fin normal forces and moments for a model of a wingless fin-controlled missile. With the horizontal-fin deflection limited to a maximum of 6 degrees, longitudinally stable and trimmed flight could not be maintained beyond an angle of attack of 17 degrees for a Mach number of 0.88 and beyond 20 degrees for a Mach number of 0.50 for any center-of-gravity location without the use of some auxiliary stability or control device such as jet vanes" (p. 1).

The present paper summarizes and correlates broadly some of the research results applicable to fin-stabilized ammunition. The discussion and correlation are intended to be comprehensive, rather than detailed, in order to show general trends over the Mach number range up to 7.0. Some discussion of wings, bodies, and wing-body interference is presented, and a list of 179 papers containing further information is included. The present paper is intended to serve more as a bibliography and source of reference material than as a direct source of design information.

Data are presented showing compliance of C-54D with Army and Navy lateral and directional stability and control specifications. The airplane met requirements except for the rolling effectiveness pb/2V, the aileron forces in rolling, and the rudder forces in the asymmetric power conditions which were marginal. Also, the results of special tests concerning asymmetric power, asymmetric loading, and pitch due to yaw requested by the Airplane Handling Qualities Subcommittee of the Air Transport Association are presented.

Report presenting an investigation of the altitude operational characteristics of a prototype model of the J47D turbojet engines, which includes an afterburner, a variable-area exhaust nozzle, and an integrated electronic control in an altitude wind tunnel. Results regarding compressor stall, compressor unstall, combustor blow-out during acceleration, stall and blow-out protection, acceleration characteristics, deceleration characteristics, and altitude starting characteristics, afterburner operational characteristics are provided.

Report presenting the results of an investigation of the internal dynamics of a ramjet engine and the steady-state and dynamic performance characteristics of a number of ramjet controls. Three types of engine control systems were investigated: (1) shock positioning, (2) direct control of diffuser-exit pressure, and (3) an optimalizing control designed to obtain peak pressure recovery from the diffuser. Results regarding the engine steady-state performance, engine dynamics, and controls investigations are provided.

Report presenting an investigation made in the stability tunnel to determine the effectiveness with which the dynamic characteristics of a low-speed slowly spinning fin-stabilized rocket could be studied by a free-oscillation technique and to study certain peculiarities of behavior. Results regarding the stability of the original model, effect of reversing direction of the arming propeller, effect of increasing size of reversed-rotation of the arming propeller, effect of removing the arming propeller, effect of adding a spoiler nose ring to the basic model, and the effect of changes in spin rate are provided.

Report presenting an investigation to determine the effectiveness of studying the dynamic characteristics of a low-speed slowly spinning fin-stabilized rocket with a free-oscillation technique and to study certain types of behavior that have been observed in this type of missile. Results regarding the stability of the original model, the effect of reversing direction of arming propeller, the effect of increasing the size of the reversed-rotation arming propeller, the effect of removing the arming propeller, the effect of adding a spoiler nose ring to a basic model, and the effect of changes in the spin rate are provided.

Report presenting an investigation in the free-flight tunnel to study the dynamic longitudinal stability of equal-size models coupled in tandem with a single joint providing freedom in pitch. Results regarding the characteristics of the model motions, effect of elevator gearing ratio, effect of weight ratio, and effect of static stability of the front model are provided.

"A study of the data obtained in a flight investigation of an R-2800-21 engine in a P-47G airplane was made to determine the effect of the flight variables on the engine cooling-air pressure distribution. The investigation consisted of level flights at altitudes from 5000 to 35,000 feet for the normal range of engine and airplane operation. The data showed that the average engine front pressures ranged from 0.73 to 0.82 of the impact pressure (velocity head). The average engine rear pressures ranged from 0.50 to 0.55 of the impact pressure for closed cowl flaps and from 0.10 to 0.20 for full-open cowl flaps" (p. 1).

Report presenting a review of the present status of research and development on high-energy fuels for ramjet propulsion. It also presents experimental investigations on the use of high-energy fuels in ram jets that include the materials aluminum, boron, boron hydrides, carbon, coal and coal-light metal compositions, liquid hydrogen, and magnesium. A comparison of the fuels in terms of heating values, combustion temperatures and specific impulse, and availability of fuels are provided.

Report presenting a preliminary investigation in a duct system with fully developed pipe flow to determine the effectiveness of vortex generators in improving the performance of a 21-inch-diameter straight-outer-wall annual diffuser with an overall equivalent conical expansion angle of 15 degrees and a and 1.9:1 area ratio. The vortex generators used were rectangular noncambered airfoils that varied in chord, span, angle of attack, number, and location. Results regarding a diffuser with no vortex generators, a diffuser with vortex generators on inner body, and a comparison of the diffuser performance with and without vortex generators are provided.

Report discussing the stability and control characteristics and drag of a canard or tail-first configuration explored using the free-fall method. Information about the basic flight characteristics, experimental coefficients, zero-lift drag configurations, and longitudinal stability and trim characteristics is provided.

Memorandum presenting a transonic flutter investigation of models of the T-tail of the Blackburn NA-39 airplane. The investigation is to be considered preliminary in that only estimated airplane properties were available for the scaling. Results regarding interpretation of results, presentation of data, and a discussions are provided.

Memorandum presenting tests of a scale model of a B-36J/RF-84F tip-coupled airplane in the 19-foot pressure tunnel in order to evaluate the flutter characteristics where bomber-body freedoms are allowed and to obtain an indication of the dynamic stability characteristics of the configuration. The variables studied in the investigation included skew angle of the fighter-bomber coupling, fighter longitudinal position, fighter and bomber loading, angle of sideslip, degrees of body freedom, and the number of fighters.

Report presenting a supersonic flight investigation of a roll-stabilized acceleration control missile for a Mach number range from 1.4 to 1.7. The control system operation was found to be satisfactory and applicable to some present-day missiles using linear acceleration commands. Results regarding analysis, preflight simulator results, a comparison between simulator and analytical results, flight test results, and a comparison between the flight test and preflight simulator results are presented.

Report discussing a transonic flutter investigation of models of the T-tail of the Blackburn NA-39 airplane. The investigation was made at a variety of Mach numbers at simulated altitudes extending to below sea level. The Mach numbers at which asymmetric flutter and symmetric oscillations occur are presented.

Report presenting an experimental investigation of a scale model of the forebody of a proposed supersonic fighter to determine the internal performance and configuration drag of various twin-side inlets. External-compression ramp and bump inlets with various types and combinations of boundary-layer bleed were tested. Results regarding performance charts and flow characteristics are provided.

Report presenting a general analysis that allows the rolling motions of an aircraft using a displacement-response, flicker-type automatic pilot to be determined. The system is not ideal for many stabilization problems due to inherent residual oscillations, but it offers a simple and economical solution in situations in which steady state oscillations are not a problem. Results regarding some general remarks, transient and steady states, stabilization boundaries, amplitude equations, and period equations are provided.

Report presenting an investigation of large-chord flap-type controls with sweptback hinge lines and with various sizes and shapes of horn balances on a triangular wing of aspect ratio 2. Changes in the following elements were investigated: shielding of the horn balance, percentage of horn balance, trailing-edge thickness, flap nose seal, contour of the horn balance, and Reynolds number.

As a part of this investigation, the acceleration characteristics of the engine, using the standard engine fuel-control system, were obtained for conditions simulating flight at altitudes of 35,000 and 50,000 feet with a flight Mach number of 0.4. Rapid and wave-off type accelerations were made at each flight condition, and the transient performance of the engine was recorded with a multiple-channel oscillograph. The parameters are presented graphically in the form of time histories, augmented by short segments of the oscillograph recordings, in order to more completely describe the behavior of the engine parameters when surge was encountered.

Report presenting an investigation in a duct system with fully developed pipe flow to determine the effects of vortex generators on the performance of a diffuser with whirling inlet flow. Testing was made with three different inlet whirl angles and rectangular, noncambered airfoils that varied in chord, span, angle setting, number, and location. Results for the 20.6 degree inlet whirl angle, 15.2 degree inlet whirl angle, 0 degree inlet whirl angle, and effect of inlet whirl angle on diffuser performance are provided.

Memorandum presenting a survey and evaluation of flutter research and flutter engineering, with particular emphasis placed on the design of primary fixed surfaces and primary controls. Analyses are made of recent flutter occurrences to delineate past and future problems, and detailed appraisals are given of the status of the various engineering branches involved in the analytical and experimental prediction of flutter.

"Strain-gage measurements were taken under operating conditions from blades of various stages of the 19XB axial-flow compressor in an effort to determine the reason for failures in the seventh and tenth stages. First bending-mode vibrations were detected in the first five stages of the compressor caused by each integral multiple of rotor speed from three through ten. Lead-wire failures in the last five stages resulted in incomplete data" (p. 1).