:Spin tests have been performed in the Langley 20-foot free-spinning tunnel on a 1/18-scale model of the Fairchild XNQ-1 airplane. The spin and recovery characteristics of the model were determined for the normal gross-weight loading and for two variations from this loading - center of gravity moved rearward and relative mass distribution increased along the fuselage. These tests were performed for two vertical-tail plan forms. The investigation also included simulated pilot-escape tests and rudder-force tests" (p. 1).

Memorandum presenting a wind-tunnel investigation made in the stability tunnel to determine the effects of lift flaps on the static lateral stability derivatives and the yawing derivatives of an untapered 45 degree sweptback wing at low speeds. Results regarding straight flow and yawing characteristics are provided.

Report discussing an investigation of the low-speed characteristics of a wing with a triangular plan form, 60 degrees of sweepback at the leading edge, and 10-percent-thick biconvex airfoil sections. The purpose of the investigation was to determine the effects of semispan and full-span leading-edge and trailing-edge flaps on the longitudinal aerodynamic characteristics of the wing and the effects of a vertical fin on the lateral stability characteristics.

Memorandum presenting an investigation conducted to study the performance of a single-stage axial-flow compressor using blades with an NACA 5509-34 airfoil section. Static- and total-pressure, total-temperature, and flow-angle surveys were taken in the compressor inlet and outlet and between blade rows to study the overall performance and individual blade-row performance.

Report presenting an investigation to determine the maximum quantity of water that could be injected either into or ahead of a single can-type combustor without reducing the attainable combustor-outlet temperature below the value required for engine operation and without the appearance of liquid water at the combustor outlet. Water was injected from spray nozzles at four different stations along the combustor.

Memorandum presenting the flammability limits of 18 high-boiling hydrocarbons at reduced pressures in a closed flame tube with hot-wire ignition. Characteristic two-lobe flammability-limit curves were demonstrated by all of the hydrocarbons. The rich limit, lean limit, and flammability range were found to decrease as the number of carbon atoms increased.

"Tests have been made in the Langley 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1.41, 1.61, and 2.01 of various arrangements of a 0.04956-scale model of the Convair F-102A airplane with faired inlets. Tests made of the model equipped with a plain wing, a wing with 6.4 percent conical camber, and a wing with 15 percent conical camber. Body modifications including an extended nose, a modified canopy, and extended afterbody fillets were evaluated" (p. 1).

Report presenting flight testing of a rocket-powered model of a cruciform canard missile configuration with a low-aspect-ratio wing and blunt nose. Results regarding the lift coefficient, dynamic stability, static stability, control effectiveness, and drag are provided.

Report presenting testing of a full-scale rocket-powered model of a cruciform canard missile configuration with a low-aspect-ratio wing and blunt nose. Static and dynamic longitudinal stability and control derivatives were determined at low angles of attack and for a range of Mach numbers.

Report presenting flight testing and analog-computer studies using flight-test results of a swept-wing jet fighter in the landing condition to determine the factors that influence a pilot to select the minimum approach speed for carrier-type landings. Many factors that influenced the pilot occurred in approximately the same speed range, and the quantitative determination of the influence of each factor was not possible. Results regarding measurement of airplane and engine characteristics, field-carrier landings, and analog simulation of airplane and hypothetical autopilot in high-dip maneuver at constant thrust are provided.

"Rocket-boosted free-flight tests of two models of an airplane configuration having a 45 degree swept wing and a low horizontal-tail position have provided lateral stability derivatives and control effectiveness data for a Mach number range from 0.8 to 1.7. The experimental lateral stability derivatives presented are corrected to rigid conditions and compared with theoretically calculated rigid derivatives. The results are presented without detailed analysis" (p. 1).

"The linearized theory of Tulin and Burkart for two-dimensional supercavitating hydrofoils operating at zero cavitation number is applied to the derivation of two new low-drag configurations. These sections were derived by assuming additional terms in the vorticity distribution of the equivalent airfoil; in particular, three and five terms were considered. A simplified calculation of the location of the cavity boundary streamline for arbitrary configurations is also presented" (p. 1).

Report presenting a blade-element analysis of a compressor rotor with blade sections with NACA A(sub 2)I(Sub 8b) mean lines and 65-series thickness distributions in Freon-12 gas. Results regarding blade loss, angle of attack associated with minimum loss, peak efficiencies, and comparison with other transonic rotors are provided.

Report presenting a determination of the characteristics velocity of liquid oxygen and gaseous hydrogen as a function of mixture ratio in a nominal 200-pound-thrust variable-length rocket engine. Fourteen injectors, which varied mixing and oxygen atomization, were investigated. The four types of injector designs included triplets of two hydrogen jets impinging on one oxygen jet, concentric injection with hydrogen surrounding a jet of oxygen, radial injection of oxygen with variations in hydrogen injection, and oxygen atomization by two impinging jets with variations in hydrogen injection.

Report presenting an investigation of the off-design performance of fixed- and variable-geometry divergent ejectors. Results regarding fixed geometry and low secondary flow, fixed geometry and high secondary flow, variable geometry and low secondary flow, variable geometry and high secondary flow, and ejectors with full afterburning are provided.

"The off-design performance of fixed- and of variable-geometry divergent ejectors was investigated. The ejectors, which were designed for turbojet operation at Mach 3, were investigated in the Mach number range of 0.8 to 2. The performance of a fixed-geometry ejector with high secondary-flow rates was competitive with that of more complex variable-geometry ejectors. Variable-geometry ejectors with compromises to reduce mechanical complexity produced performance reasonably close to that of an ideal variable ejector" (p. 1).

Report presenting some experimental free-flight data at a range of Mach numbers regarding the normal force and pitching effectiveness of several small pulse rockets in the fuselage of a rocket propelled model. Wing-damping data was also obtained from the wing bending response to the pulse-rocket excitations, and longitudinal stability data was determined from the model response. Results regarding pulse-rocket effectiveness, wing damping, and model stability data are provided.

Report presenting an exploratory study of the screaming tendency of the gaseous-hydrogen-liquid-oxygen propellant combination in 200-pound-thrust rocket engines. Four injector classes in a total of 12 different configurations were tested in a variety of chamber lengths over the usable mixture-ratio range. Results regarding acoustic oscillations, unclassified oscillations, driving and damping mechanisms, and effects of screaming on heat transfer are provided.

Memorandum presenting an investigation in an altitude test chamber to evaluate the use of highly reactive chemicals injected into a turbojet afterburner to promote the combustion process, which was inhibited by water vapor from compressor-inlet injection. The chemicals evaluated were commercial hydrogen and aluminum trimethyl. Results regarding the effects of hydrogen injection on afterburner performance and effect of aluminum trimethyl afterburner fuel additive on performance are provided.

Report presenting an investigation in an altitude test chamber to evaluate the use of highly reactive chemicals injected into a turbojet afterburner to promote the combustion process. The chemicals evaluated were commercial hydrogen and aluminum trimethyl. Results regarding the afterburner efficiency, afterburner stability limits, afterburner-outlet total temperature, and an application of the results to other systems are provided.