Report presenting rolling effectiveness and drag tests of spoilers on unswept wings over a range of Mach numbers using rocket-propelled test vehicles in free flight. The wings tested had an aspect ratio of 3.7, were unswept and untapered, had thickness ratios of 3, 6, and 9 percent, and covered a range of flexibilities. Results regarding the rolling effectiveness and drag are provided.

Report presenting an investigation of an 18-foot-radius helicopter rotor powered by tip-mounted ramjet engines in the helicopter test tower. The engine performance is compared with the performance determined in a previous investigation of a 9-foot-radius rotor with the same engines at similar speeds but with twice the centrifugal forces. Results regarding the propulsive characteristics, minimum specific fuel consumption and corresponding propulsive thrust, and operational characteristics are provided.

"An investigation of the Reynolds number for transition and the skin-friction drag at zero lift of eight cone-cylinder bodies having various fineness ratios has been made at Mach numbers of 1.62, 1.93, and 2.41 over a Reynolds number range from 0.3 x 10(exp 6) to 10 x 10(exp 6). The accuracy of the skin-friction data was not sufficient to permit any general conclusions to be drawn. The Reynolds number for transition was found to be dependent upon both the tunnel stagnation pressure and Mach number" (p. 1).

Report presenting an investigation of an ogive-cylinder nacelle in various spanwise locations in a vertically symmetric position on a small-size 45 degree sweptback wing of aspect ratio 6 with and without a fuselage. Results regarding the drag characteristics, lift-drag ratios, lift characteristics, pitch characteristics, and lateral center of pressure are provided.

Memorandum presenting a wind-tunnel investigation at low speed to determine the path and motion of a scale model of the Douglas XF4D-1 escape capsule without the drogue parachute when jettisoned by jet ejection. The investigation included determination of the vertical and horizontal accelerations of the capsule. Results regarding the ejection at zero airspeed, ejection at 570 feet per second, and at 863 feet per second are provided.

The performance and operational characteristics of the J71-A2 turbojet-engine afterburner were investigated for a range of altitudes from 23,000 to 60,000 feet at a flight Mach number of 0,9 and at flight Mach numbers of 0.6, 0.9, and 1.0 at an altitude of 45,000 feet. The combustion performance and altitude operational limits, as well as the altitude starting characteristics have been determined.

Report discussing an experimental investigation of the low-speed rolling stability derivatives of a model of the Douglas A4D-1. The model was tested under a variety of conditions, including in clean and landing configurations and with the horizontal and vertical tails on and off, and the study also explored the effects of slats and flaps on the derivatives of the wing. No analysis of the data is provided.

Report presenting an experimental investigation to determine the low-speed rolling stability derivatives of a scale model of the Douglas A4D-1. The model was tested in clean and landing configurations with horizontal and vertical tails on and off. The data is presented without analysis.

From Summary: "During a flight investigation of the lateral stability characteristics of a high-speed delta-wing airplane, violent cross-coupled lateral and longitudinal motions were encountered. The maneuver which produced these motions was an abrupt, rudder-fixed aileron roll performed at a Mach number of 0.75 at about 40,000 feet. The motions were characterized by extreme variations in angle of attack and angle of sideslip which caused the airplane to exceed the normal and transverse acceleration limitations."

Report presenting a flight investigation on a roll-stabilized ram-jet test vehicle over a range of Mach numbers from 2.3 to 2.7, a range of fuel-air ratio from 0.038 to 0.050, and an altitude range from 3,000 to 40,000 feet. Results regarding test conditions, engine performance, and roll autopilot performance are provided. The engines operated satisfactorily over the test time and the roll-control system operated satisfactorily at the beginning of testing.

Report presenting a flight investigation on a roll-stabilized ramjet test vehicle to determine engine performance over a range of Mach numbers, a range of fuel-air ratio, and an altitude range. Results regarding engine performance and roll autopilot performance are provided.

Report presenting flight tests to measure the directional stability of a fighter-type airplane over a range of Mach numbers. Testing occurred at two altitudes and used three vertical tails of varying aspect ratio or area.

From Summary: "The effect of engine momentum on the longitudinal and directional stability of aircraft in steady rolling maneuvers has been investigated. The results presented indicate that the gyroscopic moments produced on the aircraft by rotating engine in rolling maneuvers can have an appreciable effect on the range of rolling velocities for which longitudinal or directional instability might occur."

Report presenting an investigation of the transonic flutter characteristics at zero lift of a model of a wing for a new fighter airplane. The characteristics were found to be similar to those of a comparable systematic plan-form series of models described in previous reports. Results regarding visual observations, damping, flutter-speed ratio, and ratio of experimental sustained flutter speeds to reference flutter speeds are provided.