From Introduction: "Experimental investigations of the combustion characteristics of diborane, pentaborane, and pentaborane-hydrocarbon blends in modified turbojet combustors have been conducted at this laboratory at the request of the Bureau of Aeronautics, Department of the Navy, as part of Project Zip. Results of these single-combustor tests are presented in references 2 to 5."

Boundary-layer-transition and heat-transfer measurements were obtained from flight tests of blunt and sharp cones having apex angles of 50 deg. The test Mach number range was from 1.7 to 4.7, corresponding to free-stream Reynolds numbers, based on cone base diameter, of 18. 3 x 10(exp 6) and 32.1 x 10(exp 6), respectively. Transition on both models occurred at a local Reynolds number of 1 x 10(exp 6) to 2 X 10(exp 6) based on distance from the stagnation point. Transition Reynolds numbers based on momentum thickness were between 320 and 380 for the blunt cone. The model surface roughness was 25 rms microinches or greater. Turbulent heat transfer to the conical surface of the blunt cone at a Mach number of 4 was 30 percent less than that to the surface of the sharp cone. Available theories predicted heat-transfer coefficients reasonably well for the fully laminar or turbulent flow conditions.

"An experimental radial-survey investigation of the J71-97 three-stage turbine equipped with a first stator having a throat area 87 percent of the design value was conducted at one turbine operating point. The first-, second-, and third-stage mass-averaged efficiencies were 0.897, 0.843, and 0.755, respectively. The corresponding over-all turbine efficiency was 0.856" (p. 1).

Memorandum presenting an investigation of a swept-wing fighter-type airplane not equipped with an automatic pitch damper that made pulse maneuvers at altitudes from 10,000 to 40,000 feet over a Mach number range from 0.36 to 1.45 to determine the longitudinal stability characteristics and derivatives for an original-wing and an extended wing-tip configuration. Results regarding the original wing, extended wing, and influence of wing-tip extensions are provided.

From Summary: "A flight investigation was conducted to determine the effects of inlet modification and rocket-rack extension on the longitudinal trim and low-lift drag of the Douglas F5D-1 airplane. The investigation was conducted with a 0.125-scale rocket-boosted model between Mach Numbers of 0.81 and 1.64. This paper presents the changes in trim angle of attack, trim lift coefficient, and low-lift drag caused by the modified inlets alone over a small part of the test Mach number range and by a combination of the modified inlets and extended rocket racks throughout the remainder of the test."

Report presenting an investigation of several combustor configurations to determine if the length of the engine could be reduced. Testing indicated that when using a highly reactive fuel in the low subsonic region of the diffuser, part of the engine length can be eliminated.

Memorandum presenting a determination of the static lateral stability of six delta wings at subsonic speeds. In addition, two of the wings with 82.5 degree and 75 degree sweep of the leading edge were oscillated in yaw about the 50-percent point of the root chord in order to determine the effects of frequency and amplitude on the combination lateral stability derivatives resulting from the motion. Results regarding the static characteristics and oscillatory characteristics are provided.

Report presenting testing of a transonic compressor rotor with double-circular-arc blade sections and inlet guide vanes turning counter to the direction of rotor whirl to determine the effect of blade-row interaction on the performance of a transonic rotor. Results regarding overall performance, guide-vane performance, rotor-inlet conditions, rotor-outlet conditions, consideration of radial equilibrium, blade-element performance, and axial asymmetry in rotor-outlet flow are provided.

"Preliminary tests made by the General Electric Company indicated that aerodynamic loads might cause large enough distortions in the thin sheet-metal rings of a nuclear fuel element to result in structural failure. The magnitude of the distortions in a test fuel element was determined from strains measured with airflow conditions simulating those expected during engine operation. The measured vibratory strains were low enough to indicate the improbability of failure by fatigue. A conservative estimate of the radial deflection that accompanied peak strains in the outer ring was +0.0006 inch" (p. 1).

Memorandum presenting an evaluation of the performance increase resulting from the addition of 20 percent fluorine to the oxygen-RP-1 propellant combination in a 5000-pound-thrust rocket engine at a chamber pressure of 650 pounds per square inch absolute. Runs were made with the engine water cooled and regeneratively cooled.

An investigation of the performance increase resulting from the addition of 20 percent fluorine to the oxygen-RP-1 propellant combination in a 5000-pound-thrust rocket engine at a chamber pressure of 650 pounds per square inch absolute.

Memorandum presenting an investigation conducted in the 7- by 10-foot tunnel of the static longitudinal and lateral stability characteristics of a model with a 45 degree sweptback wing of aspect ratio 4 and with several different tail arrangements. The tail configurations studied had unswept, rectangular surfaces and included a T-tail and conventional fuselage-mounted horizontal and vertical tails. Results regarding wing-fuselage characteristics, effects of afterbody shape, effect of tail configuration on stability, and comparison of swept- and unswept-wing configurations are provided.

Report presenting flight tests on an FJ-3 airplane to determine the flight characteristics of a carrier-type airplane with area-suction and blowing boundary-layer control on the trailing-edge flaps. Measurements were made of lift, drag, and bleed-air requirements for the different types of boundary-layer control systems. Results regarding lift, drag, flow requirements, performance, pilots' opinions, and approach-speed criteria are provided.

Report presenting a flight test of pentaborane fuel in an air-launched ramjet engine with a design free-stream Mach number of 1.8. The ramjet used in the investigation had a revised spray bar-flameholder configuration. Results regarding propulsive thrust and propulsive-thrust specific fuel consumption are provided.

Flight investigation of pentaborane fuel in 9.75- inch-diameter ramjet engine with downstream fuel injection.

"Skin temperatures and surface pressures have been measured on a slightly blunted cone-cylinder-flare configuration to a maximum Mach number of 9.89 with a rocket-propelled model. The cone had a total angle of 25 deg and the flare had a 10 deg half-angle. Temperature data were obtained at eight cone locations, four cylinder locations, and seven flare locations; pressures were measured at one cone location, one cylinder location, and three flare locations" (p. 1).

Memorandum presenting an investigation in the 20-foot free-spinning tunnel on a 1/25-scale model of the McDonnell F3H-2N airplane. The effects of control settings and movements on the erect and inverted spin and recovery characteristics of the model were determined for the clean condition. Results regarding erect spins, engine gyroscopic moments, inverted spins, spin-recovery parachute, and landing condition tests are provided.

Memorandum presenting a full-scale free-jet investigation of a two-shock side-inlet diffuser at Mach umber 2.75 in an altitude test chamber. Data were obtained over ranges of free-stream total pressure and temperature. Results regarding diffuser mass-flow ratio, critical pressure recovery, diffuser static-pressure variation, and diffuser-outlet flow conditions are provided.

"A highly polished hemisphere-cone having a ratio of nose radius to base radius of 0.74 and a half-angle of 14.5 degrees was flight tested at Mach numbers up to 4.70. Temperature and pressure data were obtained at Mach numbers up to 3.14 and a free-stream Reynolds number of 24 x 10(exp 6) based on body diameter. The nose of the model had a surface roughness of 2 to 5 microinches as measured with an interferometer" (p. 1).

Report presenting testing on six blunt-nose models at angles of attack ranging from 0 to 5 degrees in order to evaluate the heat transfer and pressure on their surfaces. Information about transition, proper design, and locations of greatest and least heat transfer is provided.

Memorandum presenting an investigation to determine the performance of the J65-B-3 turbojet engine with JP-4 and gaseous-hydrogen fuels. With JP-4 fuel, the maximum altitude for stable combustion was from about 60,000 to 65,000 feet, and the ultimate blowout limit was at an altitude of about 75,000 feet. The steady-state performance with either fuel decreased considerably with increasing altitude.

Report presenting an investigation to determine the performance of the J65-B-3 turbojet engine with JP-4 and gaseous-hydrogen fuels. With JP-4 fuel, the maximum altitude for stable combustion was from about 60,000 to 65,000 feet and the ultimate blowout limit was at an altitude of about 75,000 feet. Combustion with hydrogen was found to be stable up to the facility altitude limit of 89,000 feet.

Report presenting an investigation to determine the control hinge-moment characteristics at two Mach numbers for a series of 18 controls, including the effects of various tabs and fences, on a 60 degree delta wing. Testing covered a range of angles of attack, control deflection, and tab deflection. Results regarding the basic variation of hinge-moment coefficients, tip controls, and trailing-edge controls are provided.

Memorandum presenting various reports regarding the use of hydrogen for turbojet and ramjet powered flight. Some of the characteristics considered include the combustion properties, potential fueling problems, and flight experience with hydrogen on-board.