Report discussing testing on a scale model of the Convair XF2Y-1 airplane with solid-fuel rocket motors that simulate full-scale turbojet-engine characteristics at a height of 35,000 feet with full afterburning at Mach number 1.53. The model was found to have dynamic lateral instability, but these results were not likely to be found in a full-scale airplane. Information about the pitching moment, directional stability, lift-curve slope, and drag coefficients is provided.

Report presenting component performance data for one modification of a 16-stage compressor and a 3-stage turbine to determine the matched performance characteristics of an engine with those components. The compressor surge line and infinite exhaust-nozzle-area equilibrium operating line restricted the region of matched compressor-turbine operation. Results regarding the engine operation with modified compressor and three-stage turbine, effect of leakage on engine operation, component efficiencies, and operation in the surge region are provided.

Report presenting measurements made on the Bell X-1 airplane to determine the pressures on the fuselage base and rear portion of the fuselage during level flight. Measurements were made in the power-off condition and with the engine operating. Information about the power-off pressures and jet effects is provided.

Report presenting measurements of the intensity of buffeting experienced by the Douglas D-558-II research airplane at a range of Mach numbers. Buffeting was encountered at both subsonic and supersonic Mach numbers and the intensity of the buffeting varied with Mach number and airplane normal-force coefficient.

The effects of one type of camber on the aerodynamic characteristics of rectangular wings at high subsonic and transonic speeds have been studied by applying the transonic similarity rules to the correlation of experimental data for a series of 18 cambered wings having NACA 63A2XX and 63A4XX sections, aspect ratios from 1 to 4, and thicknesses from 4 to 8 percent. The data were obtained by use of a transonic bump over a Mach number range of 0.6 to 1.1.

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.

Flight testing at transonic speeds occurred on two rocket-propelled models of an airplane configuration with 45 degree sweptback wings of aspect ratio 4 and with different stiffnesses. Longitudinal stability, lift, and drag characteristics were determined by analysis of the response of the models to disturbances in pitch. Results regarding lift, model vibrations, aeroelastic effects on lift, static stability, damping in pitch, and drag are provided.

Report presenting comparisons of the aerodynamic characteristics and flow phenomena at transonic speeds for two unswept zero-taper-ratio wing-body combinations. The first had a cylindrical afterbody, while the second had an indented afterbody in the region of the wing-body juncture. Results regarding force characteristics, flow surveys, and an interpretation of the results are 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 the results of testing of bodies and wing-body combinations by the free-fall method in order to provide information about drag characteristics of airplanes and their component parts at transonic speeds. Two models with a fineness-ratio-12 body of revolution with 45 degree sweptback wings located at different positions were dropped and equipped with improved drag measuring instrumentation and pressure measuring orifices on the portion of the body expected to be influenced by the presence of the wing. Results regarding pressure data and drag data are provided.

Report presenting a determination of the individual stage performance for a 10-stage axial-flow compressor from circumferentially fixed radial rake measurements of total temperature and total pressure obtained at the discharge of each stage. Results regarding compressor performance, stage performance, and some general remarks are provided.

Report presenting an investigation of the effects of wing and tail modifications on the low-speed stability characteristics of a model with thin 40 degree swept wings of aspect ratio 3.5. The main purpose was to improve some of the undesirable longitudinal stability characteristics observed in flight of several airplanes with similar wing geometry. The use of flaps, the position of the horizontal tail, and the use of chord extensions are all explored as possible solutions.

Report presenting an investigation in the high-speed tunnel to determine the static longitudinal and static lateral stability characteristics of a wing-fuselage combination with a triangular wing with an aspect ratio of 2.31 and an NACA 65A003 airfoil section. The tests occurred over a range of Mach numbers from 0.40 and 0.95 and separate testing was also conducted with small notches added to the leading edge of the wings.

"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).

"An investigation was made of the trim and dynamic response characteristics of the free-floating horizontal tail of a 1/7-scale model of the complete tail of the Grumman XF10F-1 airplane in the Langley 8-foot transonic tunnel at Mach numbers up to 1.13. The complete tail was mounted in the tunnel on a 3 degree conical support body. Various configurations were investigated. A loss in damping of the horizontal tail at transonic speeds was shown by both tunnel and flight tests" (p. 1).

From a theory developed on a quasi-one-dimensional-flow basis, it is found that the stability of the ram jet is dependent upon the instantaneous values of mass flow and total pressure recovery of the supersonic diffuser and immediate neighboring subsonic diffuser. Conditions for stable and unstable flow are presented. The theory developed in the report is in agreement with the experimental data of NACA-TN-3506 and NACA-RM-L50K30. A simple theory for predicting the approximate amplitude of small pressure pulsation in terms of mass-flow decrement from minimum-stable mass flow is developed and found to agree with experiments.

From Summary: "A simplified analysis of the velocity and deceleration history of ballistic missiles entering the earth's atmosphere at high supersonic speeds is presented. The results of this motion analysis are employed to indicate means available to the designer for minimizing aerodynamic heating. The heating problem considered involves not only the total heat transferred to a missile by convection, but also the maximum average and local time rates of convective heat transfer."

"Under the assumption that a wing, body, or wing-body combination is slender or flying at near sonic velocity, expressions are given which permit the calculation of pressure in the immediate vicinity of the configuration. The disturbance field, in both subsonic and supersonic flight, is shown to consist of two-dimensional disturbance fields extending laterally and a longitudinal field that depends on the streamwise growth of cross-sectional area. A discussion is also given of couplings, between lifting and thickness effects, that necessarily arise as a result of the quadratic dependence of pressure on the induced velocity components" (author).