A set of modified NACA 65-series blower blades designed for axial inlet velocity, high inlet Mach number, and high blade loading was investigated for trailing-edge thickness of 0.015, 0.030, and 0.045 inch to determine the effect of trailing-edge thickness on single-stage axial-flow-compressor performance. Trailing-edge thickness effects were small except at the highest tip speed investigated (915 ft/sec). Trailing-edge thickness up to 30 percent of maximum blade thickness were used without sacrifice of performance of NACA 65-series blades.

Memorandum presenting results obtained during Air Force testing of the Northrop X-4 airplane. Information is included on the stalling characteristics, the static and dynamic longitudinal and lateral-stability characteristics, and the lateral-control characteristics.

Report presenting a study of the pressure-drag reduction obtained by projecting a high-energy jet of air from the nose of a prolate spheroid at transonic speeds. Results regarding the pressure distribution on the body, pressure drag, shadowgraphs, and some notes regarding the slope of the body and level of shear at the jet exit are provided.

Report presenting an investigation at low speed to determine the lateral-control and hinge-moment characteristics of a 20-percent-chord unsealed partial-span outboard aileron with several plan forms. Results regarding the wing aerodynamic characteristics are also provided.

Report presenting an investigation to determine the aerodynamic characteristics of deflectable wing-tip ailerons on a sweptback wing in the Langley high-speed tunnel by means of the transonic bump technique. Three ailerons were investigated, one with a basic wing-plan form and two with an extended-tip plan form. Results regarding the longitudinal aerodynamic characteristics, rolling-moment data, control effectiveness, and lift effectiveness are provided.

Report discussing the spin and spin-recovery characteristics of a model of the Douglas X-3 airplane in a free-spinning tunnel. The pitching-moment characteristics of the scale model were not found to be typical of larger scale results. The results indicated that at an altitude range of 15,000 to 30,000 feet, the X-3 will not exhibit unusual trim tendencies and it will be difficult to obtain erect spins unless the ailerons are full with the spin.

Memorandum presenting the tail-pipe fuel ratio, mass flow of combustion gas, and radial fuel flow distribution on cooling requirements of tail-pipe burner with annular cooling-air passage.

The effects of tail-pipe fuel-air ratio (exhaust-gas temperatures from approximately 3060 degrees to 3825 degrees R), radial distribution of tail-pipe fuel flow, and mass flow of combustion gas and the inside wall were determined for an experimental tail-pipe burner cooled by air flowing through and insulated cooling-air to combustion gas mass flow from 0.066 to 0.192 were also determined. Results regarding the reproducibility of combustion-gas temperature profiles, effect of variables on average longitudinal profiles of combustion-gas temperature, variation of gas temperatures near the wall with cooling-air flow and temperature, and effects of variables on transverse gas temperatures are provided.

Memorandum presenting an investigation at transonic speeds in the high-speed 7- by 10-foot tunnel to determine the hinge-moment and other aerodynamic characteristics of an inboard plug-type spoiler on a 45 degree sweptback wing of aspect ratio 3. The results indicated that the spoiler would be overbalanced at low projections through the speed range investigated and the for the same rolling moment, the spoiler hinge moments would be small in comparison with those of a plain-flap-type control.

Report presenting tests at low speeds in the low turbulence pressure tunnel and the stability tunnel in order to determine the extent of any resulting oscillations of a model mounted with freedom in yaw and to demonstrate the extent to which directional fluctuations in an air stream can be responsible for the oscillations.

Report presenting an investigation in the high-speed tunnel on a 45.58 degree sweptback wing to determine the effects of a paddle balance on the control characteristics of a full-span flap-type control. The wing had an aspect ratio of 3, a taper ratio of 0.5, and an NACA 64A010 airfoil section measured in a plane at 45 degrees to the plane of symmetry. Results regarding the hinge-moment characteristics, lift characteristics, and rolling moment-characteristics are provided.

Report presenting pressure-distribution tests on an ogive-cylinder configuration with and without longitudinal spoilers at Mach number 4.04. Spoilers were not found to cause any noticeable change in the body pressures in regions that contribute the largest amount of normal body force. Results regarding a comparison of experimentation and theory, flow separation, and cross-flow effects are also provided.

Report presenting an investigation in the low-turbulence pressure tunnel to determine the lift, drag, and pitching-moment characteristics of a 45 degree sweptback wing with a 6-percent-thick symmetrical airfoil section designed for maximum lift at low speeds. Results regarding low-speed testing and high-speed testing are provided. Testing indicated that the new airfoil sections provided substantial improvements at low speeds without compromising performance at high speeds.

From Introduction: "During previous investigations of afterburning conducted at the NACA Lewis laboratory (references 1 to 4, for example), the objective of obtaining high exhaust-gas temperatures and, consequently, maximum thrust augmentation was compromised to some extent in order to alleviate the problem of afterburner shell cooling. The primary objective of the investigation reported herein was therefore the attainment of maximum exhaust-gas temperature imposed by the cooling techniques previously used, a secondary flow of cooling air was provided around the afterburner shell."

Memorandum presenting an empirical cooling correlation for an experimental high-performance afterburner. The correlation relates the average combustion-chamber wall temperature at a station near the combustion-chamber outlet to the temperatures of the cooling air and combustion gas, and to the mass flows of the cooling air and combustion gas.

Report presenting an empirical cooling correlation for an experimental high-performance afterburner. The correlation equation is useful for shortening the experimental investigation of afterburner cooling characteristics inasmuch as it provides a method for interpolating the critical wall temperatures for other combinations of operating variables.

Report presenting tests to evaluate the usefulness of available theory for the calculation of lift-curve slope and center of pressure of low-aspect-ratio, triangular, and rectangular cruciform wings in combination with a long slender body. Tests were made over a range of Mach and Reynolds numbers based on model length.

Report presenting a wind-tunnel investigation of two full-span and two semispan models with 45 degrees of sweepback, an aspect ratio of 5.5, and a taper ratio of 0.53. The lift and drag data obtained from tests of the semispan agreed well with data obtained on the full-span model. Results regarding a comparison of the data for the full-span and semispan models, full-span model data, and effect of surface roughness are provided.

"This report presents results of an investigation of effects of externally mounted missile models on the aerodynamic characteristics of a triangular wing of aspect ratio 3 at both subsonic and supersonic Mach numbers. The lift, drag, and pitching moment of the wind-fuselage model fitted with the missile models are presented for Mach numbers of 0.6, 0.9, 1.2, 1.4, and 1.7 at a Reynolds number of 4.8 million. Similar data are presented for the basic wing" (p. 1).

Report presenting a theoretical investigation of the longitudinal dynamic characteristics of an automatically stabilized supersonic canard missile configuration with a target seeker sensitive to changes in pitch altitude. Variables explored include seeker gain, time delay, and non-linearities, including dead spots in the seeker.

Memorandum presenting the effective downwash characteristics of a wing-body configuration and the body alone determined from lift measurements of a horizontal tail located 0.333 and 0.479 wing semispan above the body center line. The wing had a sweepback angle of 47 degrees, an aspect ratio of 3.5, a taper ratio of 0.2, and a thickness ratio of 0.06.

Report presenting an investigation of a swept, rectangular, supersonic scoop inlet designed to have low external drag at the design Mach number of 2.7. The inlet was tested with two simulated fuselages with circular and rectangular cross sections. Results regarding shadow photographs, pressure recovery, wedge effects, drag, boundary-layer control, Mach number distribution in diffuser, wedge loads, aspect-ratio effects, and applicability of results are provided.

Report presenting a brief investigation conducted to determine the effects of a 60-40 air flow distribution to the twin inlet ducts of an axial-flow turbojet engine. Data were obtained over a range of exhaust gas temperatures at several altitudes at Mach number 0.64. Results regarding the effect on pressure and temperature patterns, compressor performance, effect on combustor and turbine performance, engine pumping characteristics, and operational characteristics are provided.

Report presenting a review of the literature pertaining to the use of orthotoluidine and triethylamine in rocket propellant combinations and a summary with particular emphasis on ignition delay investigations and fuel mixture applications. The survey indicated that orthotoluidine is about as good a rocket fuel as aniline with respect to cost, performance, and ignition characteristics, but it has a wider temperature application because of its lower freezing point.