Report presenting a free-flight investigation of a rocket-powered research model to determine the hinge-moment and normal-force characteristics of a trailing-edge control on a delta wing between Mach numbers of 0.50 and 1.26. The hinge-line location of 40 percent control chord satisfactorily reduced the high hinge moments associated with plain flap-type controls. Results regarding hinge moments and normal force are provided.

Report presenting a pressure-distribution investigation of a parabolic body of revolution with a fineness ratio of 12.2, which was performed in the 4- by 4-foot supersonic tunnel at Mach number 1.59 and Reynolds number 3.6 x 10(sub 6), based on body length, for a range of angles of attack. Results regarding basic pressures, aerodynamic coefficients, asymmetrical pressures, comparison of experimental and theoretical pressures, artificial roughness, section coefficients, and body coefficients are provided.

From Summary: "Flight measurements of the aerodynamic wing loads on the D-558-II airplane have been made in the Mach number range from 1.0 to 2.0. Nonlinear wing-panel characteristics occurred with variations in angle of attack. These nonlinear characteristics were apparent primarily at the lower supersonic speeds."

Report presenting chordwise pressure distributions measured over the left wing of the Convair XF-92A delta-wing airplane to determine the effect of lift on the wing characteristics at subsonic and transonic Mach numbers. Results regarding the chordwise pressure distributions, wing-section aerodynamic characteristics, spanwise distributions, and elevon-section loads are provided.

Report presenting an investigation of boundary-layer bleed through a slot placed at the juncture of the suction surface and end wall to determine whether bleed in this manner could be used to prevent the local accumulation of boundary-layer fluids due to secondary flows. Results regarding the effect of bleed pressure, effect of bleed-slot height, and effect of slot length and position are provided.

The effect of the design characteristics of various condensing chambers on magnesium build-up at the chamber inlet was investigated. The condensing chambers are used in the vapor-condensation process for making magnesium slurries. A complete description of the various chamber designs and the procedure used in testing the chambers is given. The results are evaluated on the basis of clogging and total magnesium distilled per run. Orifice design was also considered.

Report discussing the aerodynamic characteristics in pitch and sideslip of a model of a Douglas D-558-II airplane with and without a yaw-damper vane at Mach number 2.01. A revised model was tested using a canopy and modified vertical tail. The revised configuration was found to have higher directional stability, trim lift coefficients, drag, and more positive effective dihedral than the original configuration.

Report presenting chordwise pressure distributions measured over the left wing of the Convair XF-92A delta-wing airplane to determine the effect of lift on the wing characteristics at subsonic and transonic Mach numbers. Results regarding the chordwise pressure distributions, wing-section aerodynamic characteristics, spanwise distribution, and elevon-section loads are provided.

Report presenting an investigation in the Langley Unitary Plan wind tunnel to determine the drag and static longitudinal and lateral stability characteristics of a model of the Grumman F11F-1F airplane at Mach numbers 1.56, 1.76, 2.06, and 2.53. The investigation included the effects on performance and stability of modifications, including a wing-root leading-edge fillet and horizontal tails with negative dihedral of 10 degrees and 30 degrees. Information regarding net external minimum drag coefficients, neutral points, directional stability, and positive effective dihedral is provided.

Memorandum presenting the results of an investigation directed at determining the effectiveness of various amounts and spanwise extents of conical camber on the aerodynamic characteristics of a wing-body-tail combination employing a triangular wing of aspect ratio 2.2. Five cambered wings were tested, all of which were designed for a Mach number of 1.0. Results regarding drag characteristics and lift and moment characteristics are provided.

Memorandum presenting an investigation at high subsonic speeds of a model of a twin-engine swept-wing fighter-type airplane. The model was tested with several different tail configurations and with several wing and engine inlet modifications. Results regarding pitching-moment characteristics, lift and drag characteristics, and lateral derivatives are provided.

Report presenting the overall performance and rotating stall characteristics of a single-stage compressor with a hub-tip ratio of 0.76 and a symmetrical velocity diagram over a wide range of weight flow for several different design speed percentages. No discontinuities in performance were noted at an operating condition. Results regarding the overall performance, types of rotating stall observed, circumferential extent of stall zones, flow fluctuations incited by rotating stall, rotating-stall hysteresis, and a theoretical analysis 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 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 an investigation to determine the effect of several seeker-nose configurations on the static longitudinal stability, canard control characteristics, and lift and drag at Mach number 1.60 of a canard-type ramjet missile with 70 degree delta canard control surfaces and 70 degree delta wings. The tests indicate that, for the most part, the configurations tested exhibited no significant difference in static longitudinal stability or horizontal-canard control effectiveness.

Report presenting an investigation of the rolling-stability derivatives for a model of the Republic F-105 airplane over a range of Mach numbers and angles of attack. The model retained damping in roll through the test ranges, but values of the damping varied considerably with angles of attack. Derivatives of yawing moment and lateral force due to rolling generally followed previously indicated trends.

"Tests have been made in the Langley 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1.41, 1.61, and 2.01 of various arrangements of a 0.04956-scale model of the Convair F-102A airplane with faired inlets. Tests made of the model equipped with a plain wing, a wing with 6.4 percent conical camber, and a wing with 15 percent conical camber. Body modifications including an extended nose, a modified canopy, and extended afterbody fillets were evaluated" (p. 1).

Report presenting an investigation to determine the static stability characteristics of five hypersonic missile configurations. Testing was performed at a range of Mach and Reynolds numbers. Results regarding the effect of base block, longitudinal stability, directional stability, and Reynolds number effect are provided.

Report presenting flight testing of a rocket-powered model of a cruciform canard missile configuration with a low-aspect-ratio wing and blunt nose. Results regarding the lift coefficient, dynamic stability, static stability, control effectiveness, and drag are provided.

Report presenting an investigation to experimentally determine the effectiveness of air cooling several turbine-blade configurations in a turbojet engine. The results obtained with the first configuration, which was a hollow blade shell with 10 tube inserts, are presented. A description of factors leading to the design are provided as well as the correlated cooled-blade temperatures, solid-blade temperatures, cooling-air-temperature increase through radial passages, and blade failure are provided.

Report discussing an investigation into the performance of several modifications of a side-inlet ramjet engine diffuser. Total-pressure-recovery profiles, Mach number profiles, longitudinal wall static pressure distributions, and variation of the average-static to average-total pressure are presented.

From Summary: "Calculated velocity and temperature distributions, as well as relations among Nusselt number, Reynolds number, and friction factor, are presented."

Forces and moments of store-pylon combination mounting on swept wing-fuselage configuration in supersonic pressure tunnel. The results of the investigation indicate that the most important source of store-pylon side forces is the pylon itself.