Memorandum presenting Mach number histories of the motion experienced by a hypothetical, small, straight-wing aircraft accelerating at various rates through an assumed controls-fixed pitch-down balance change in the transonic range. Two approximate analytical solutions of the longitudinal equations of motion are developed which are based on certain simplifying assumptions indicated by the differential-analyzer results.

Report presenting results of an exploratory free-flight investigation at zero lift of several rocket-powered drag research models equipped wing wing tanks at a range of Mach numbers. The tanks, which were slender bodies of revolution, were mounted on 34 degrees sweptback, nontapered wings of 2.7 aspect ratio. Results regarding drag and trim change are provided.

This report presents an analysis of a compound engine operating with manifold pressures ranging from 60 to 110 lb/sq in. absolute and discusses the effects of engine limits (peak cylinder pressure and turbine-inlet temperature) and component efficiency.

Report presenting an investigation of the performance and general operating characteristics of a small single-cylinder, two-stroke-cycle, loop-scavenged engine using compression ignition at low compression ratios, high inlet-manifold temperatures and high inlet-manifold and exhaust-gas pressures. Results regarding the scavenging characteristics, power output, cylinder pressures, thermal efficiency, and exhaust measurements are provided.

Report presenting an experimental investigation of the downwash and sidewash flow angles in a transverse plane behind a cruciform-wing and body combination. The wing-body combination had a cruciform arrangement of two identical triangular wings of aspect ratio 2.31 corresponding to a leading-edge sweep angle of 60 degrees placed on a body of fineness ratio of 16. The investigation was conducted at a specified Mach and Reynolds number and a range of angles of bank and attack.

"Pressure-distribution measurements and load-coefficient data at low speeds obtained in flight for a conventional front and rear sliding canopy are presented. The load-coefficient data indicate that the highest net aerodynamic load for the front canopy was in the exploding direction and occurred with the front and rear canopies closed. The highest net load for the rear canopy was in the crushing direction with the front canopy open and the rear canopy closed" (p. 1).

Report discussing static testing on 3 NACA two-blade propellers with design lift coefficients of 0, 0.3, and 0.5. Information about the effect of camber on the static-thrust figure of merit, the effect of camber on the stall-flutter speed, thrust coefficient, and blade flutter is provided.

Report presenting an investigation in the free-flight tunnel to determine the dynamic lateral stability and control characteristics of a coupled airplane configuration with simplified fighter models attached to the wing tips of a simplified bomber model. The configuration is meant to represent fighter airplanes carried on the wing tips of a bomber airplane to provide fighter protection for the bomber or for in-flight fueling. Results regarding the fighters attached with freedom in roll, with freedom in roll and pitch, and with freedom in roll, pitch, and yaw are provided.

Report presenting an investigation to determine the effects of taper ratio and body indentation on the aerodynamic loading characteristics of a 45 degree sweptback wing in the presence of a body in the transonic pressure tunnel for a range of Mach numbers and angles of attack. Results regarding the effect of wing-body-juncture seals, general effects of the variables, effect of taper ratio, effects of body indentation, and comparisons with other data are provided.

Report presenting an investigation to obtain the effects of a 20-percent-semispan all-movable wing-tip control on the longitudinal stability characteristics of a twisted and cambered 60 degree sweptback-wing-indented-body configuration. Testing occurred over a range of angles of attack and Mach numbers. Results regarding the effects on drag coefficient and lift-drag ratio are also provided.

Report presenting zero-lift experimental flutter data in a range of Mach numbers on a 1.5-percent-thick, untapered, unswept, solid steel wing with hexagonal airfoil sections and wing length-to-chord ratios of 1.61 and 1.73. The wing was tested as a cantilever with and without a half-body-of-revolution fuselage. Results regarding the calculated flutter speeds and frequencies, effect of fuselage, variation of wing flutter characteristics with Mach number, results of analytic solutions, and variation of wing flutter characteristics with mass ratio are provided.

Report presenting flutter data over a range of Mach numbers in free-flight testing of several wing-body combinations as part of a general zero-lift drag investigation. The wings all had the same streamwise airfoil sections and the plan-form variations consisted of delta wings, diamond wings, and an arrow wing. Time histories of model speed, Mach number, and air density are provided for each model as well as flutter frequency, amplitude, and reduced-frequency parameter plotted as functions of model speed.

Report presenting a flight investigation over a range of altitudes and lift to determine the wing loads of the Bell X-5 research airplane at a sweep angle of 58.7 degrees at subsonic and transonic Mach numbers. Testing indicated that wing loads exhibit nonlinear trends over the angle-of-attack range from zero to maximum wing lift.

Memorandum presenting an investigation in the 7- by 10-foot tunnel of the static longitudinal and lateral stability characteristics of a model with an unswept wing and several different tail arrangements. The shapes tested include a Y-tail, a cruciform tail, and a more conventional T-tail. Results regarding wing-body characteristics, effects of stabilizer incidence on lateral characteristics, T-tail characteristics, Y-tail characteristics, X-tails, estimated tail contribution, and characteristics referred to the body-axis system are provided.

Report presenting shadowgraphs of flow patterns through the blade passage and ahead of a compressor rotor by shining parallel light rays approximately radially onto a rotor hub and upstream inner ring, which was painted white to serve as a screen. The flow patterns were used in conjunction with measured data to analyze the performance of two axial-flow supersonic compressors over a range of Mach numbers in Freon-12. The shadowgraph was found to be a useful tool for comparing the flow patterns within rotors and cascade sections and improving compressor analysis.

Report presenting pressure-distribution data on fuselage surfaces which extended downstream of a jet exit and were subject to the influence of a heated propulsive jet. Testing occurred at a range of free-stream Mach numbers, jet pressure ratios, and jet-exit temperatures.

The performance of a mixed-flow impeller in combination with a semivaneless diffuser were experimentally investigated. The diameter of the impeller was 11.0 inches and a maximum tip diameter of 14.74 inches. The semivaneless diffuser had an overall diameter of 28.00 inches. The performance properties of the mixed-flow impeller were also investigated with a 34.00 inch vane loss diffuser having a transition section of the same geometry as the semivaneless diffuser.