Memorandum presenting a study of an acceleration-limiting control on a turbojet engine in order to determine its feasibility as an acceleration control. A proportional-plus-integral type of controller was used in the investigation. Results regarding the one-loop control and two-loop control are provided.

Memorandum presenting an acceleration-limiting control used on a turbojet engine to study the feasibility of its use as an acceleration control. A proportional-plus-integral type of controller was used in this investigation. Results regarding one-loop control and two-loop control are provided.

Low cowl drag, external compression inlet with subsonic dump diffuser for high Mach number application.

Report presenting an investigation of a zero-cowl-drag, all-external-compression inlet with an abrupt area discontinuity or subsonic dump diffuser for high Mach number application. Results regarding the diffuser performance characteristics, effect of spike retraction, a comparison with other inlets, and some theoretical calculations related to the results are provided.

Report presenting an investigation conducted to determine the relative advantages and limitations of a number of fluids for use as either heat sinks or coolants for hypersonic aircraft. The feasibility of the fluids tested as heat sinks and cooling in the high-level and low-level regions is described.

Memorandum presenting theoretical rocket performance for both equilibrium and frozen composition during expansion, which was calculated for the propellant combination of liquid ammonia with liquid oxygen at two chamber pressures and a wide range of pressure ratios and oxidant-fuel ratios. Some of the performance parameters explored include specific impulse, specific impulse in vacuum, combustion-chamber temperature, nozzle-exit temperature, molecular weight, molecular-weight derivatives, characteristic velocity, coefficient of thrust, ratio of nozzle-exit area to throat area, specific heat at constant pressure, isentropic exponent, viscosity, thermal conductivity, Mach number, and equilibrium gas compositions.

The magnitude and the effects of boundary-layer separation on normal-force-curve slopes, centers of pressure, pressure distributions, and lift and drag coefficients were determined for various bodies of revolution with conical tail flares at Mach numbers from 3.0 to 6.3. Some of the experimental results are compared to theoretical predictions of the aerodynamic characteristics of the bodies.

Report presenting a small-scale apparatus for simulating the motion and heating of ballistic missiles and its elements of design and operation. Experiments demonstrate that conditions for simulation are fulfilled according to theoretical requirements. Results regarding the application to full-scale missiles, shadowgraph observations, observations of recovered models, and spectroscopic observations are provided.

Memorandum presenting an investigation of the effects of modifying a twin side-inlet duct system on an interceptor airplane as recorded and analyzed over an altitude range from about 25,000 to 51,000 feet throughout the transonic speed range to a Mach number of about 1.2. The modifications consisted primarily of redesigning the inlet lip, increasing the cross-sectional area of the inlet and diffuser, and adding a region of duct contraction ahead of the engine.

Report presenting the effects of modifying a twin side-inlet duct system on an interceptor airplane over a range of altitudes throughout the transonic speed range to Mach number 1.2. The primary modifications were redesigning the inlet lip, increasing the cross-sectional area of the inlet and diffuser, and adding a region of duct contraction ahead of the engine.

Memorandum presenting a wind-tunnel investigation of the three types of lateral control devices on a low-aspect-ratio trapezoidal wing. Tip ailerons, a plain spoiler, and a vented spoiler were investigated to ascertain the relative characteristics of each system. The results indicated the superiority in roll power of the tip ailerons over the plain and vented ailerons.

Report presents a comparison of the theoretical and experimental expressions of lift, drag, and center of pressure of supercavitating hydrofoils. The results obtained from both methods appear to agree well with one another. The application of cavitation number to a variety of situations and speeds is also provided.

"A two-spool turbojet engine was operated in the Lewis altitude wind tunnel to study the inception of compressor surge. In addition to the usual steady-state pressure and temperature measurements, the compressors were extensively instrumented with fast-response interstage pressure transducers. Thus it was possible to obtain maps for both compressors, pressure oscillations during rotating stall, effects of stall on efficiency, and stage-loading curves" (p. 1).

Report presenting zero-lift drag data for a flare-stabilized bluff body of fineness ratio 4.4 alone and with conical and flat windshields at a range of Mach and Reynolds numbers. The model with the flat windshield was found to have the lowest drag at Mach numbers up to 1.05, but there was little difference in drag among the models above 1.05.

Report presenting an investigation to determine the effect of frequency of sideslipping motion on the lateral stability derivatives of a 60-degree delta-wing airplane configuration. Results regarding the steady-state tests, oscillation-in-sidestep tests, comparison of oscillation data for delta wings with a round edge versus a sharp edge, and effect of sideslip oscillatory derivatives are provided.

Memorandum presenting an investigation to study the effect of ground proximity on the aerodynamic characteristics of two jet vertical-take-off-and-landing airplane models in which the fuselage remains in a horizontal attitude for the take-off and landing. Results regarding the flow surveys and force tests are provided.

Memorandum presenting total-pressure surveys made in the slipstreams of two full-scale three-blade supersonic propellers in the 16-foot transonic tunnel at Mach numbers up to 1.04 to determine the effects of camber on supersonic-propeller characteristics. The two propellers were similar except that one of them had symmetrical blade sections and the other had cambered blade sections and a slightly different pitch distribution. Over the complete range of the tests, the cambered propeller maintained higher thrust and efficiency.

Report presenting a temperature survey for two bodies with wings swept 39 and 75 degrees for an angle of attack of 7 degrees, Mach numbers up to 4.86, and a designated Reynolds number. Effects of wing-body interference on heating and the difference in heating on windward and leeward sides at a designated angle of attack are explored. Pressure coefficients are also presented for two different stations on the body.

Memorandum presenting a determination of the effect of nose shape on the normal-force, pitching-moment, and axial-force coefficients of a body of revolution with a fineness ratio of 10.94 as determined at subsonic speeds. Six nose shapes were investigated, which included flat-faced noses with various corner radii, a hemispherical nose, and two ogival noses.

Report presenting data showing the effect of a jet on base pressure for a series of conical afterbody-jet-nozzle combinations with a range of boattail angles and base-to-jet diameter ratios. Generally, base pressure increased for increasing values of boattail angle, nozzle angle, jet temperature, and jet total pressure and for decreasing values of base-to-jet diameter ratio, jet Mach number, and free-stream Mach number.

Report presenting a free-flight investigation to determine the hinge-moment characteristics of a trailing-edge control on a swept and tapered wing using a rocket-powered model. Results regarding normal force and pitching moments are also provided.

Report presenting an investigation of the transonic flutter characteristics of a 64 degree delta wing with spars along constant-percent chord lines and streamwise ribs. The data was compared to a previously published report on a similar wing with spanwise spars and orthogonal streamwise ribs.

Report discussing the use of cones as stabilizing and control surfaces, which seems to be promising. Information about preliminary considerations, range of cone angles of probable interest, effects of Mach number on the shift in lift advantage from flat plate to cone, comparison of cone with more competitive lifting surfaces, and comparison in terms of producing the same restoring force for complete configuration is presented.

The flow fields near a 45 degree swept-wing-fuselage combination at moderate angles of sideslip (plus-or-minus 8 degrees), as determined experimentally at low speed, are presented as variations with chordwise distance for various spanwise and vertical locations and angles of attack. The results indicated that for positions close to the fuselage (on and near the plane of symmetry) changes in the angle of sideslip caused large changes in the flow-field characteristics and particularly in the local angles of sideslip, which in some cases were nearly double the static angle of sideslip.