Report presenting the performance characteristics of a 20-inch ramjet opeerating with preheated unleaded 62 octane fuel. The results of the investigation indicated an improvement in the combustion efficiency and operating range of the ramjet when using preheated fuel.

Report presenting an investigation in the free-flight tunnel to determine the low-speed, power-off dynamic stability and control characteristics of a model with a 35 degree sweptback wing. The investigation consisted of force and flight tests of the model and calculations of the lateral oscillatory stability with wing-tip fuel tanks off and on.

An investigation has been made in the Langley full-scale tunnel of a 47.5 degree sweptback wing-fuselage combination equipped for boundary-layer control by suction. The wing aspect ratio was 3.5, the taper ratio was 0.5 and the airfoil sections normal to the quarter-chord line were NACA 61(sub 1)-A112. Tests included the plain wing and the wing with various combinations of extensible leading-edge and split flaps.

From Summary: "A supersonic free-jet facility (Mach number 3) capable of accommodating full-scale ram-jet engines has been constructed and evaluated. A 24-inch circular nozzle produces a jet of sufficiently uniform velocity that a good simulation of the engine internal flow is obtained. An annular diffuser placed around the engine recovers part of the total pressure of the jet flow passing outside the engine so that the pressure ratios which must be imposed across the facility to start and maintain the jet are kept to reasonable values."

Report presenting an experimental investigation to determine the performance of side inlets with external compression ramps and rectangular cowls mounted on the fuselage forebody of a proposed supersonic airplane. Results regarding supersonic Mach number range, subsonic Mach number of 0.63, and static or take-off conditions are provided.

Report presenting information about spoiler-type ailerons, which are of interest because they give high reversal speeds for the thin, flexible wings now used. A bibliography on spoiler-type controls is also provided.

Report presenting an investigation conducted in the 8-foot transonic tunnel to determine the longitudinal stability and control characteristics of a 0.09-scale model of the Bell X-5 research airplane. Lift, drag, pitching-moment, elevator hinge-moment, and pressure-distribution results are presented for a range of Mach and Reynolds numbers. Results regarding lift and drag characteristics, longitudinal stability and control characteristics, dynamic-response characteristics, elevator hinge-moment characteristics, and mass-flow characteristics and pressure distributions are provided.

Report presenting testing of the subsonic and transonic handling qualities of the Douglas D-558-II research airplane using several configurations of mid-semispan external stores in the altitude region of 20,000 to 40,000 feet. The configurations had an underslung pylon on each wing, pylons plus simulated 1000-pound bombs, and pylons with 150-gallon fuel tanks. Results regarding longitudinal stability and control characteristics, low-speed characteristics, and lateral stability and control characteristics are provided.

Report presenting testing of two identically constructed 2024-T3 aluminum-alloy multiweb-wing structures, models MW-2-(2) and MW-2-(3), under aerodynamic conditions similar to those encountered in supersonic flight at Mach number 2. Results regarding model temperatures, Stanton number, model pressures, model strains, behavior of Model MW-2-(2), and behavior of Model MW-2-(3) are provided.

Report presenting an investigation at high subsonic speeds of a complete model with a highly tapered wing and several tail configurations. The complete model was tested with a wing-chord-plane tail, a T tail, and a biplane tail. A discussion regarding the lateral derivatives and sideslip characteristics is provided.

"This paper is concerned primarily with the application of the "area rule" to the interpretation and improvement of the drag-rise characteristics of wing-body combinations at transonic and moderate supersonic speeds. Consideration of the general physical nature of the flow at transonic speeds, together with comparisons of the flow fields and drag-rise characteristics for wing-body combinations and bodies of revolution has led to the conclusion that near the speed of sound the drag rise for a thin low-aspect-ratio wing-body combination is primarily dependent on the axial distribution of cross-sectional area normal to the airstream (ref. 1). (The drag rise, sometimes referred to as pressure drag, is the difference between the drag level near the speed of sound and the drag level at subsonic speeds where the drag is due primarily to skin friction.) In order to illustrate the concept, figure 1 shows a wing-body combination and a body of revolution" (p. 1).

Report presenting testing of four multiweb wing structures similar to those on an airplane or missile at Mach number 2, sea-level static pressure, a 0 degree angle of attack, and stagnation temperature of 500 degrees Fahrenheit. Three models were made of 2024-T3 aluminum alloy and one was made from SAE 1010 steel; internal structure and skin thickness varied across the models. Results regarding model behavior, model temperatures, calculated skin temperatures, strain-gage results, model pressures, and calculated pressures are provided.

"An analysis of the estimated high-speed flying qualities of the Chance Vought XF7U-1 airplane in the Mach number range from 0.40 to 0.91 has been made, based on tests of an 0.08-scale model of this airplane in the Langley high-speed 7- by 10-foot wind tunnel. The analysis indicates longitudinal control-position instability at transonic speeds, but the accompanying trim changes are not large. Control-position maneuvering stability, however, is present for all speeds. Longitudinal lateral control appear adequate, but the damping of the short-period longitudinal and lateral oscillations at high altitudes is poor and may require artificial damping" (p. 1).

Report presenting testing of half-span models of two wings of different plan form as both all-movable and fixed surfaces in the presence of a half fuselage. All-movable surfaces are being considered for supersonic aircraft as possible angle-of-attack indicators, control surfaces, and all-movable wings. Results regarding the lift characteristics, center of pressure, and drag of the wings are provided.