Wind tunnel testing of swept wing fighter aircraft model for determining drag and static longitudinal and lateral stability and control characteristics. Results regarding performance, longitudinal stability, lateral stability, and strakes are provided.

Memorandum presenting a design and experimental investigation of a single-stage supersonic turbine. The turbine was designed for a rotor entering relative Mach number of 2. Results regarding the overall turbine performance, outer-wall static-pressure variation, momentum-loss considerations, effect of rotor modifications, and supersonic starting are provided.

Memorandum presenting an experimental investigation of an internal-contraction, axially symmetric inlet with isentropic compression surfaces on both the cowl and centerbody conducted over a range of Mach numbers from 2.0 to 2.7 at angles of attack from 0 to 6 degrees. The study was made to determine the optimum bleed system, together with a method of controlling the inlet.

Report presenting measurements in a wind tunnel of the subsonic static and dynamic-rotary stability derivatives of a model of an airplane designed to fly at high supersonic speeds and high altitudes. The effects of flaps and landing gear, speed brakes, and several model components are included in the results as well as the stability characteristics of the model.

Report presenting a wind-tunnel investigation of the low-speed aerodynamic characteristics of an airplane configuration designed to obtain high lift-drag ratios at hypersonic speeds. The power-off landing of this aircraft would be difficult due to the high sinking speeds inherent in the design. Results regarding the longitudinal characteristics, lateral characteristics, and landing considerations are provided.

Report presenting wing loads and load distributions obtained by differential-pressure measurements between the upper and lower surfaces of the wing of the Douglas X-3 research airplane with various leading-edge-flap deflections. The load and hinge-moment characteristics of the leading-edge flap are presented for a range of Mach numbers with and without flap deflection. Results regarding chordwise load distributions, wing-section and wing-panel characteristics, span load and pitching-moment distributions, leading-edge-flap characteristics, and a comparison with wind-tunnel data are provided.

Report presenting an investigation of the effect of screens in a dump-type diffuser in the 2- by 2-foot supersonic wind tunnel at Mach number 3.85. Results of a slanted half screen of 0.41 solidity, positioned 0.263 inlet diameter from the cowl lip, are presented on a range basis, as this configuration allows for shortening of the subsonic diffuser.

Report presenting the results of an experimental investigation on the ablation of a number of promising materials for heating conditions comparable to those which maybe encountered by unmanned reentry satellite vehicles or heating conditions associated with reentry ballistic missiles. Results regarding exploratory tests, further Teflon tests, and graphite testing are provided.

Memorandum presenting the performance of a variable-internal-contraction inlet without boundary-layer removal measured at Mach numbers of 2.00, 2.50, and 2.92. The total-pressure recovery at the design Mach number, 2.50, was 0.78. Results regarding total-pressure recovery and contraction ratio, flow unsteadiness and distortion, and summary data correlations are provided.

"An investigation has been made in the Langley Unitary Plan wind tunnel at Mach numbers of 1.60, 1.80, and 2.00 to determine the aerodynamic characteristics of a 0.03-scale model of the Avro CF-105 airplane. The investigation included the determination of the static longitudinal and lateral stability, the control and the hinge-moment characteristics of the elevator, rudder, and aileron, as well as the vertical-tail-load characteristics. Although the data are presented without analysis, a limited inspection of the longitudinal control results indicates a loss in maximum lift-drag ratio due to trimming of about 1.8 because of the large static margin" (p. 1).

Report presenting the effects at Mach number 2.01 of various changes in nose and afterbody shape on the static aerodynamic characteristics of a body of revolution with a fineness ratio of 11 with an ogive nose, a cylindrical center section, and a boattail or cylindrical afterbody. Some body conditions were tested in combination with a vertical tail. Results regarding the effects of nose and afterbody modifications and vertical tail-on configurations are provided.

Report presenting an investigation to determine the effects on performance of positioning normal shocks in or upstream of both a long and a short subsonic annular diffuser. Results regarding the entrance flow conditions, performance for subsonic-entrance flows, and performance with choked- and supersonic-entrance flows are provided.

Report presenting results for a canard bomber-type configuration designed for supersonic cruise flight at Mach numbers 2.50 and 2.87 and over a range of angles of attack and angles of sideslip. Results regarding longitudinal characteristics and lateral stability are provided. The original configuration was directionally unstable at low angles of attack, but satisfactory directional stability could be obtained using upper-surface vertical fins.

A wind-tunnel investigation to determine the effects of both single and twin jets on base drag of a cylindrical body has been conducted at Mach numbers from 0.6 to 1.4. The plane of the jet exit was varied with respect to that of the afterbody. Jet total-pressure ratio ranged up to 20. Significant improvements in base drag were obtained by extending the plane of the jet exits beyond the afterbody base and by venting the base cavity to the external stream.

Memorandum presenting a transonic flutter investigation of models of the T-tail of the Blackburn NA-39 airplane. The investigation is to be considered preliminary in that only estimated airplane properties were available for the scaling. Results regarding interpretation of results, presentation of data, and a discussions are provided.

Report discussing a transonic flutter investigation of models of the T-tail of the Blackburn NA-39 airplane. The investigation was made at a variety of Mach numbers at simulated altitudes extending to below sea level. The Mach numbers at which asymmetric flutter and symmetric oscillations occur are presented.

Memorandum presenting a transonic flutter investigation of models of the wing of a current fighter airplane. The models were dynamically and elastically scaled in accordance with criteria which include a flutter safety margin. Results regarding the presentation of data, interpretation of results, wings without leading-edge chord-extensions, and wings with leading-edge chord-extensions are provided.

Report presenting a transonic flutter investigation of models of the wing of a fighter airplane. Results regarding the wings with and without leading-edge chord-extensions, and scaling of the stiffness are presented. The flutter boundary was found to remain below sea level with or without the leading-edge extensions.

From Summary: "An approximate analysis of the nonlinear effects of initial twist and large deflections on the torsional stiffness of a cantilever plate subjected to a nonuniform temperature distribution is presented. The Von Karman large-deflection equations are satisfied through the use of a variational principle. The results show that initial twist and applied moments can have significant effects on the changes in stiffness produced by nonuniform heating, particularly in the region of the buckling temperature difference. Results calculated by this approximate analysis are in satisfactory agreement with measured torsional deformations and changes in natural frequency."

Engine dynamics were investigated for supercritical operation of the ram jet at Mach 2.75 over a range of simulated altitudes from 68,000 to 82,000 feet. Indicial-and frequency-response tests were conducted with fuel flow as the input variable. For a wide range of operating points, the response of static or total pressure to fuel flow consisted of a dead time followed by a response form that generally approximated a linear, first-order, lead-lag. The dead time varied significantly only with distance from the combustion zone. The rise ratio and the time constant of the lead-lag function were nearly independent of the pressure sensed.

Memorandum presenting a study of the effect of oxide-depositing fuels on engine starting, operation, and performance by using a modified production turbojet engine operated using a trimethyl borate azeotrope as a fuel. Results regarding boric oxide deposition, engine operation and performance, effect of turbine-inlet temperature, and dissipation of boric oxide deposits are provided.

Report presenting testing of a modified production turbojet engine using a trimethyl borate azeotrope as a fuel. Operation with this fuel for 100 minutes produced a 2-percent deterioration in engine speed and only a 1-percent increase in combustor total-pressure loss with the best engine configuration investigated. Results regarding boric oxide deposition, engine operation and performance, effect of turbine-inlet temperature, and dissipation of boric oxide deposits are provided.

Memorandum presenting a mechanism for the thermal decomposition of sodium, lithium, beryllium, magnesium, aluminum, and boron alkyls and for the reverse reaction, the addition of olefins to metal hydrides. The reactions are shown to be nonradical and to probably proceed through a cyclic intermediate.

From Introduction: "The feasibility of closed-loop control of ram-jet-engine thrust is demonstrated in references 1 and 2. The dynamic behavior of a 28-inch-diameter ram-jet engine designed to operate in Mach number range of 2.35 to 2.70 is evaluated herein."