Engine dynamics and controls data are presented for a ram-jet engine which was operated in a free-jet facility at a Mach number of 2.76 and altitudes from 68,000 to 82,000 feet. The predominant engine dynamic characteristics was dead time, with values ranging from 0.018 to 0.053 sec. The control systems were designed to hold a constant ratio of a diffuser static pressure to an inlet-cone reference static pressure.

Memorandum presenting a supersonic wind-tunnel investigation of the origin and distribution of store interference performed in the 4- by 4-foot supersonic pressure tunnel at Mach number 1.61 in which separate forces on a store, a fuselage, a swept wing, and a swept-wing-fuselage combination were measured. The report presents data on a configuration which simulated a heavy-bomber airplane with stores of several shapes and sizes.

Report presenting an investigation at two Mach numbers to examine the flow, force, and moment characteristics associated with spoilers mounted on a flat plate at a range of sweep angles. Pressure measurements were obtained over the plate and spoiler faces. The pressures were integrated to determine the spoiler lift, pitching-moment, drag, and hinge-moment characteristics.

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. The separate forces on a store, a fuselage, a swept wing, and a swept-wing-fuselage combination were measured. Results regarding drag, lift, pitching moment, side force, and yawing moment are provided.

An investigation has been made at Mach numbers of 1.61 and 2.01 and Reynolds numbers from 1.7 X 10 to 7.6 X 10 to determine the pressure distributions over a 60 deg. delta wing having 20 different control configurations. Measurements were made at angles of attack from 0 deg to 15 deg for control deflections from -30 deg to 30 deg. This report presents the complete tabulated pressure data for the range of test conditions.

Memorandum presenting an investigation conducted to determine the feasibility of increasing the tip-section blade-element efficiency of a transonic rotor by reducing the blade loading for a given design inlet relative Mach number. This report primarily discusses the overall and blade-element performances of the modified rotor and compares them with the performance of the original rotor.

From Introduction: "Range in more or less steady level flight depends directly on aerodynamic lift-drag ratio at high supersonic speeds, just as it does at lower speeds. This result follows from the classical Breguet range equation in the case of powered flight, and it may be easily deduced from the equations of motion for unpowered or gliding flight (see refs. 1 and 2)."

Report describing an experiment to obtain heat-transfer and pressure-drop data for the air side of a liquid-metal to air, shell-and-tube heat exchanger. Testing was conducted in a 500 kilowatt facility using sodium as the shell-side heating fluid. Results regarding the shell-and-tube heat exchanger and finned-tube heat exchanger friction factor are provided.

Report presenting a brief series of airplane-wing aerodynamic-noise and boundary-layer-profile measurements made in flight as part of an extended investigation of boundary-layer noise. Results regarding the boundary layer data and ratio of root-mean-square sound pressure to the dynamic pressure are provided.

From Summary: "Data were obtained with five exhaust-nozzle areas and with the variable-area exhaust nozzle interlinked with the control system at conditions simulating flight at a Mach number of 0.8 and altitudes of 35,00 and 45,000 feet. Data simulating operation at zero flight Mach number at an altitude of 15,000 feet are also included. Engine component performance data are presented in addition to the overall engine performance."

Report presenting a theoretical study of the possibility of improving the lifting efficiency of aircraft flying at supersonic speeds using indirect lift, which can be induced on the wing by the fuselage shape and/or wing end plates. Results indicated that lifting efficiency of a planar wing may be improved by favorable interference induced by lateral forces on the end plates or on the sides of the fuselage.

Note presenting tables of thermal properties of molecular nitrogen that have been prepared in an NBS-NACA series and grouped together for convenient use. Some of the properties include the thermodynamic functions for the gas, both real and ideal, the transport properties for the gas, and the vapor pressure of the liquid and the solid.

Note presenting tables based on the Lennard-Jones 6-12 potential for nonpolar molecules to be used in the representation of second and third virial coefficients and equation-of-state corrections for enthalpy, entropy, specific heats at constant volume and at constant pressure, the ratio of specific heats, the isentropic expansion coefficient, and the velocity of sound.

Report presenting the effect of leading-edge geometry on transition position, recovery-factor distribution, boundary-layer profile, and the roughness required to induce transition at Mach number 3.1 for a hollow cylinder aligned with the air stream. Results regarding leading-edge effect, roughness elements in laminary boundary layer, surface-heat condition effects, and effect of stream total temperature are provided.

Note presenting a theoretical analysis of the relations between wake characteristics and total-pressure defect for the incompressible flow across a two-dimensional cascade of compressor blades. Results indicated that the total-pressure-loss coefficient for unseparated flow varied almost directly with the ratio of wake momentum thickness to blade chord length and with the solidity, and inversely with the cosine of the air outlet angle.

Note presenting large downstream movements of transition observed when the leading edge of a hollow cylinder or a flat plate is slightly blunted are explained in terms of the reduction in Reynolds number at the outer edge of the boundary layer due to the detached shock wave. The hypothesis is made that transition Reynolds number is substantially unchanged when a sharp leading edge or tip is blunted.

Memorandum presenting wind tunnel tests performed on a family of missiles. This paper summarizes some of the performance and stability and control characteristics of the missiles.

Report presenting a summary of NACA research on afterburners for turbojet engines during the past 5 years. The references present over 1000 afterburner configurations and about 3500 hours of operation. The report covers the following topics: burner-inlet diffusers, fuel-injection systems, flameholders, combustion space, combustion instability, starting and transient performance, effects of diluents, and burner-shell cooling.

"An investigation has been made at Mach numbers of 1.61 and 2.01 and Reynolds numbers from 1.7 x 10(exp 6) to 7.6 x 10(exp 6) to determine the pressure distributions over a 60 degree delta wing having 20 different control configurations. Measurements were made at angles of attack from 0 to 15 degrees for control deflections from -30 to 30 degrees. This report presents the complete tabulated pressure data for the range of test conditions" (p. 1).

"This presentation is intended to reflect the current general approach of the NACA to the problems of high-temperature structures research facilities. The facilities and problems discussed apply to flight in the Mach number range from 2 to about 20. It is emphasized that this field is one in which the thinking is rapidly changing and the facilities investigations discussed, particularly for the higher temperature range, are in the exploratory stage" (p. 1).

Report presenting chemical and physical properties determined from a sample of boron-carbon-hydrogen fuel Z-244.

Experimental investigation of engine dynamics and controls for 48-inch ramjet engine in free jet facility at Mach number 2.76 and altitudes 68,000 to 82,000 feet. The engine data presented include steady-state performance, indical response, frequency response, and ignition characteristics. Ignition data are presented for representative fuel-air ratios which show that the normal shock overshoots its final position by several feet during ignition transients.

Report discussing testing on the drag, longitudinal stability, and lateral stability characteristics of a model of the McDonnell F4H-1 airplane. The minimum drag coefficients, neutral point, horizontal-tail-incidence range, static directional stability, and effective dihedrals are presented.

Report presenting an investigation of a method for producing hypersonic flow in a wind tunnel by using the hot gaseous products obtained from the thermal decomposition of nitrous oxide. Testing was conducted at a variety of temperatures and pressures.