Report presenting data to determine the component and overall engine performance up to an altitude limit for the J71-A-11 (600-B36) turbojet engine. Engine operation using JP-4 fuel at Mach number 0.8 was satisfactory up to an altitude of about 60,000 to 65,000 feet, and engine operation with marginal combustion stability was maintained to an altitude of about 80,000 feet. Results regarding the altitude operating limits, component performance, overall engine performance, contribution of individual component losses to overall engine performance losses, exhaust-nozzle-area requirements, and altitude performance at rated engine conditions are provided.

Memorandum presenting an investigation of the J71-A-11 (600-B36) turbojet engine conducted in an altitude wind tunnel, and more specifically the component and overall engine performance up to the altitude limit imposed by the use of MIL-F-5624A, grade JP-4, fuel. The data were then extended to higher altitudes by the use of gaseous-hydrogen fuel. Results regarding altitude operating limits, component performance, overall engine performance, contribution of individual component losses to overall engine performance losses, exhaust-nozzle-area requirements, and altitude performance at rated engine conditions are provided.

"A 49 degree swept-wing complete model equipped for high-pressure blowing full span at two chordwise locations at the leading edge of a full-span wing and over a half-span flap has been tested in the Langley full-scale tunnel to determine the effectiveness of blowing at the leading edge as a supplementary leading-edge stall control at high lift coefficients." The effect of blowing on the lift characteristics, pitching-moment characteristics, and drag characteristics of this particular model is described.

Report presenting an investigation in the transonic tunnel to determine the aerodynamic loading characteristics of a 3-percent-thick, aspect-ratio-2.06, 60 degree delta-wing-body combination at a range of Mach numbers and angles of attack. Results regarding pressure distributions, spanwise loadings, integrated wing coefficients, and tabulated pressure coefficients are provided.

A full-scale turbojet engine was operated with pentaborane fuel continuously for 22 minutes at conditions simulating flight at a Mach number of 0.8 at an altitude of 50,000 feet. This period of operation is approximately three times longer than previously reported operation times. Although the specific fuel consumption was reduced from 1.3 with JP-4 fuel to 0.98 with pentaborane, a 13.2-percent reduction in net thrust was also encountered. A portion of this thrust loss is potentially recoverable with proper design of the engine components. The boron oxide deposition and erosion processes within the engine approached an equilibrium condition after approximately 22 minutes of operation with pentaborane.

Report presenting a flight-test program investigating a modification to an interceptor system. Results indicate that a significant improvement in the overall response characteristics of the system. The modification minimizes the interaction between the antenna and interceptor motions, which can have a serious influence on flight path stability during a lead-collision attack.

Report presenting an evaluation of a 1/4-sector of an annular combustor designed for use with pentaborane fuel at a simulated altitude condition. Results regarding the pentaborane performance, combustor development, and the JP-5 fuel performance are provided.

Memorandum presenting a turbojet engine with a two-stage turbine operated with pentaborane fuel continuously for 11.5 minutes at a simulated altitude of 55,000 feet at a flight Mach number of 0.8. The engine incorporated an NACA combustor designed specifically for use with pentaborane fuel. Results regarding oxide formation and deposition, engine operating point, effect of oxide deposits on component performance, effect of oxide deposition on overall performance, and some operational comments are provided.

From Summary: "The primary objectives of the investigation reported herein were to determine the effect of this new combuster design on boric oxide deposition on engine parts and to determine the effect of boric oxide on the performance of multistage turbine. Pentaborance fuel (approx. 130 lb) was used in the engine performance evaluation reported herein. The data presented herein show the engine component and over-all performance deterioration with operation on pentaborane fuel".

Report presenting an investigation of the ejection release characteristics of the MB-1 rocket from the missile bay of a model of the Convair F-106A airplane with its fin tips retracted at a simulated altitude of 18,670 feet. Successful ejections of the rocket were made at supersonic speeds by applying a combination of ejection velocity and nose-down pitching moment at release.

Report presenting an investigation of the ejection release characteristics of the MB-1 rocket from the missile bay of a Convair F-106A airplane. Results regarding pitching moment, ejections, release conditions, and missile trajectory are provided.

Memorandum presenting an investigation in the 27- by 27-inch preflight jet of the ejection release characteristics of the MB-1 rocket from the missile bay of a 0.04956-scaled model of the Convair F-106A. The MB-1 rocket was ejected with its fin tips retracted, for a simulated altitude of 18,670 feet at a Mach number of 1.59.

Report presenting the performance of two translating-double-cone inlets with contrasting rates of turning on the spike shoulder and corresponding cowl projected frontal areas of 40 and 20 percent of maximum compared over a range of Mach numbers. Results regarding internal-flow performance, external-flow performance, inlet airflow patterns, and propulsive-thrust comparison are provided.

Report presenting an investigation to study the origin and development of leading-edge cracking in turbine buckets made of six materials: S-816, M-252, Inconel 550, Inconel 700, Hastelloy R-235, and Jetalloy 1570. Some of the buckets were also given certain stress-relief treatments. Results regarding the development of leading-edge cracks, development of bucket fractures, comparison of performance for the material tested, macro- and microexamination of unfractured and fractured buckets,

Report presenting a procedure for integrating equations involving pressure, temperature, and density in order to analyze an expansion process that occurs when boric oxide from fuels condenses during expansion. An example is provided to illustrate the manner in which the equations can be used to analyze a one-dimensional expansion with phase equilibrium.

"An investigation has been completed in the Langley 20-foot free-spinning tunnel on a l/18-scale model of the Ryan X-13 airplane to determine its spin, recovery, and tumbling characteristics, and to determine the minimum altitude from which a belly landing could be made in case of power failure in hovering flight. Model spin tests were conducted with and without simulated engine rotation. Tests without simulated engine rotation indicated two types of spins: one, a slightly oscillatory flat spin; and the other, a violently oscillatory spin" (p. 1).

Report presenting a flight investigation to determine the effectiveness of three fuselage indentations for reducing the pressure drag of a 45 degree sweptback-wing-body configuration at a range of Mach numbers. The results indicate that the supersonic area rule can be used to determine indentations with low pressure drag over a Mach number range in which the blunt leading edge is subsonic. Information about total drag and pressure drag is provided.

Report presenting the results of an investigation of wing-body juncture interference effects at high subsonic and transonic speeds. Three different model series were used: one with a swept wing of aspect ratio 6 and two with swept wings of aspect ratio 3. Results regarding drag, lift, pressure distributions, and tests with the body alone are provided.

Memorandum presenting an investigation of performance estimates of aircraft nuclear propulsion (ANP) systems. This paper includes a relation of current estimated ANP performance to the future requirements that nuclear propulsion systems will be required to meet.

Report presenting a comparison of performance estimates of aircraft nuclear propulsion (ANP) systems and an attempt to determine the manner in which the estimated nuclear propulsion system performance in conjunction with the estimated airframe performance will lead to a useful military airplane.

Report presenting a low-amplitude free-oscillation investigation at zero angle of attack of the damping in yaw and directional stability of a fuselage-tail configuration through a range of reduced frequency. The damping in yaw was found to decrease with Mach numbers above 0.8 and became the lowest at about 1.0. An increase in reduced frequency was observed to cause a decrease in damping in yaw and directional stability for the test frequency range.

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."

Memorandum presenting a study of the performance of swirl-can combustor elements for an experimental short-length turbojet combustor utilizing hydrogen fuel at high-altitude operating conditions. Fuel was injected into each element through a tangential, sonic orifice that created a swirling fuel-air mixture within each element. Results regarding combustor blowout, combustion efficiency, outlet temperature distribution, and preliminary performance of multielement combustor are provided.

Report presenting a study of the performance of "swirl-can" combustor elements for an experimental short-length turbojet combustor utilizing hydrogen fuel at high-altitude operating conditions. Fuel was injected into each element through a tangential , sonic orifice that created a swirling fuel-air mixture within the element. Results regarding combustor blowout, combustion efficiency, outlet temperature distribution, and preliminary performance of the multielement performance of multielement combustor are provided.