Report discussing an investigation to determine the aileron effectiveness and damping in roll of the Hughes Falcon missile, D configuration at several Mach numbers. Information about the rolling-moment coefficient, damping-in-roll derivative, and drag coefficient is provided.

From Introduction: "The present report gives an analysis of the design point performance of nuclear powered liquid-metal turbojet engines. The effect of varying the assumptions necessary to calculate gross weight and reactor heat release from engine data is presented."

Report presenting an analysis of the nuclear powered liquid-metal turbojet cycle for a wide range of engine operating conditions at a range of flight Mach numbers and altitudes. The method of analysis and working charts are presented to facilitate investigations beyond the scope of this report.

"An investigation has been conducted in the Langley 300 MPH 7- by 10-foot tunnel to determine the static stability characteristics at low speeds of complete models with various swept wings so that comparisons might be made with available theoretical and empirical methods of predicting the stability characteristics. Longitudinal and lateral stability characteristics, flaps up and down, were obtained for models having 0 degree, 15 degrees, 30 degrees, and 45 degrees sweptforward and sweptback wings. The results of the investigation indicate that static stability characteristics can be estimated with reasonable accuracy in the low-lift range by means of existing theories" (p. 1).

The results of tests at a Mach number of 1.94 of an ogives-nose cylindrical pitot-static tube and similar tests at Mach numbers of 1.93 and 1.62 of a service pitot-static tube to determine body static pressures and indicated Mach numbers are presented and discussed. The radial pressure distribution on the cylindrical bodies is compared with that calculated by an approximate theory.

Report presenting drag measurements made on a 10-percent-thick wing and 8-percent-thick tail and a 8-percent-thick wing, 6-percent-thick tail version of the X-1 airplane at a variety of Mach numbers. The drag of the thicker wing was found to be much higher than that of the thinner wing. The fuselage was found to cause interference with the wing of both models, making the separation of wing and fuselage drag difficult to determine.

From Summary: "This report presents the results of a wind-tunnel investigation conducted to determine the effects of Mach number on the aerodynamic characteristics of a wing of triangular plan form."

Report presenting a wind-tunnel investigation at a range of Mach numbers with a constant Reynolds number of a semispan model of a thin, unswept wing of aspect ratio 4 and taper ratio 0.5 with a constant-chord aileron and a modified diamond profile. Results regarding lift and rolling-moment characteristics and aileron effectiveness are provided.

Memorandum presenting analyses based on theoretical results of NACA Report 1041 to determine the plan forms of unbalanced trailing-edge flap-type controls with minimum hinge moments due to deflection and requiring minimum work to overcome the hinge moments due to deflection at supersonic speeds. Results of the analyses for longitudinal controls show high-aspect-ratio untapered controls to possess maximum ratios of lift to hinge moment. Results regarding ratios of lift to hinge moment, ratios of lift to deflection work, ratios of rolling moment to hinge moment, and ratios of rolling moment to deflection work are provided.

Memorandum presenting a comparison between the force data obtained on a wing in air and Freon-12 at a low supersonic Mach number as obtained from the pressure coefficients measured at three spanwise stations on a 45 degree sweptback wing. Results regarding pressure distributions and force and moment conversion factors are provided.

Report presenting an investigation of an axially symmetric spike-type nose inlet suitable for a nacelle power-plant installation in the 8- by 6-foot supersonic tunnel at a range of Mach numbers and angles of attack. The inlet was designed to attain a mass-flow ratio of unity a Mach number 2.0. Results regarding the performance of inlet A and inlet B, which differed based on subsonic diffuser area variation, are provided.

Report presenting an investigation to determine the directional characteristics of a sharp-nosed fuselage through a large angle-of-attack range at zero angle of sideslip. The fuselage was found to experience a large increase in yawing moment as the angle of attack increases. The results also indicated that a ring or other roughness used on the nose caused a large decrease in the yawing moment obtained at high angles of attack.

Report presenting an investigation in the 300 mph tunnel to determine the applicability of spoilers as lateral-control devices on thin delta wings. The wing used in testing had a thickness ratio of 1.5 percent at the root and a maximum ratio of 4.5 percent at 66.7 percent wing semispan, 60 degree sweepback at the leading edge, 0 degree sweep of the trailing edge, an aspect ratio of 2.31, and a taper ratio of 0. Results regarding the effect of spoiler location and angular placement, effect of spanwise location, effect of spoiler projection, and effect of slots and perforations are presented.

Memorandum presenting a comparison made between the incremental aerodynamic root bending moments on the horizontal tail of a jet-powered bomber airplane measured during a flight investigation over a range of Mach numbers and the bending moments calculated by using available theoretical models in conjunction with measured loads, elevator positions, and elevator and stabilizer twists. Results regarding abrupt maneuvers, gradual turn maneuvers, and effects of downwash are provided.

Report presenting an investigation in the high-speed 7- by 10-foot tunnel to determine the effects of a wing leading-edge modification on the effectiveness of a spoiler-slot-deflector control. The modification consisted of a chord extension over the outboard 35 percent of the semispan in combination with a full-span leading-edge flap deflected 6 degrees.

Report presenting a free-flight investigation over a range of Mach numbers near zero lift to determine the aileron effectiveness and damping in roll of the full-scale Hughes Falcon missile, D configuration.

Report presenting normal-force and pressure distributions for a body of revolution consisting of a fineness-ratio-3, circular-arc, ogival nose tangent to a cylindrical afterbody 7 diameters long. Comparisons of theoretical and experimental distributions indicate that available theoretical methods are only accurate for angles of attack up to about 5 degrees.

Report presenting an investigation conducted in the 4- by 4-foot supersonic pressure tunnel at Mach number 1.41 and 2.01 to determine the static lateral and directional stability and control characteristics of a scale model of the Republic F-105 airplane. Results regarding the static lateral and directional stability and lateral and directional control are provided.

Report presenting an investigation of the low-speed stability and control characteristics of a modified scale model of the MX-1554A design. It employs a triangular wing and triangular stabilizing surfaces. The modifications of the design included an increase in slotted-flap span, a redesigned tip aileron, fuselage tail cone, and speed brakes.

"A high-speed wind-tunnel investigation of the aerodynamic characteristics of a full-scale model of the Consolidated Vultee Lark indicates that the missile possesses satisfactory longitudinal-stability and-control characteristics throughout the Mach number range from 0.2 to 0.85, but that the maximum lift coefficients developed are not high enough to insure interception of the target at high altitudes. A reduction in wing loading appears advisable. Although the static longitudinal stability at zero angle of attack changes with Mach number and with lift coefficient, satisfactory control should be possible at all times as the tails retain their relatively large effectiveness throughout the range of Mach numbers and lift coefficients tested" (p. 1).

"A Westinghouse 24C-2 combustor was investigated at conditions simulating operation of the 24C Jet engine at zero ram over ranges of altitude and engine speed. The investigation was conducted to determine the altitude operational limits, that is, the maximum altitude for various engine speeds at which an average combustor-outlet gas temperature sufficient for operation of the jet engine could be obtained. Information was also obtained regarding the character of the flames, the combustion efficiency, the combustor-outlet gas temperature and velocity distributions, the extent of afterburning, the flow characteristics of the fuel manifolds, the combustor inlet-to-outlet total-pressure drop, and the durability of the combustor basket" (p. 1).