Report presenting an investigation of the effect of wing-tip mounted tanks on the rolling characteristics of a wing, aspect ratio 3 with the quarter-chord line swept back 35 degrees, through a range of Mach numbers and angles of attack using the free-roll method.

Report presenting an investigation of a submerged air scoop consisting of a conventional scoop located in a dimple in the fuselage surface at low speeds. Results regarding a study of the basic inlet without suction, a comparison of arrangements using boundary-layer control, the performances of the most desirable configurations with a certain boundary layer, and variation of boundary-layer thickness are provided.

Report summarizing physical studies on Redox solutions and metal waste solutions, including refractometric investigations.

From Introduction: "A comparison is also made of the actual performance of two contemporary jet engines with estimated performance, assuming the engines were equipped with adjustable-angle stators and adjustable exhaust nozzles. Charts are presented that aid in estimating the performance of adjustable-stator turbines."

A comparison of available results from heat-transfer investigations on cascades of turbine blades is presented using the Nusselt equation. The conventional correlation procedure is modified by defining the Reynolds number by the average of the velocities and the pressures around the blades. The correlation of the results from impulse blades was improved by using the Reynolds number defined by the average velocity and pressure. The final comparison indicated that several variables, which possibly influence heat transfer, should be investigated.

A theoretical investigation has been made to determine the effect on the lateral stability of the Douglas D-58-II airplane of an autopilot sensitive to yawing velocity. The effects of inclination of the gyro spin axis to the flight path and of tire lag in the autopilot were also determined. The flight conditions investigated included landing at sea level, approach condition at 12,000 feet, and cruising at 50,000 feet at Mach numbers of 0.80 and 1.2. The results of the investigation indicated that the lateral stability characteristics of the D-558-II airplane for the flight condition discussed should satisfy the Air Force - Navy period-damping criterion when the proposed autopilot is installed. Airplane motions in sideslip subsequent to a disturbance in sideslip are presented for several representative flight conditions in which a time lag in the autopilot of 0.10 second was assumed.

A flight test was made a t high subsonic, transonic, and supersonic speeds and at high Reynolds numbers to determine the zero-lift drag of a 1/14-scale model of the Northrop MX-775B pilotless aircraft with small small body. The triangular wing of the model had 67.5 deg leading-edge sweep and 15 deg. trailing-edge sweep, The wing airfoil sections were modified NACA 0004 sections. The drag coefficient based on total wing area was 0.0107 at Mach number 1.60. At transonic speeds the maximum drag coefficient was 0.0125. The force-break Mach number was 0,98.

Report presenting time histories of horizontal-tail loads, elevator loads, and deformations on a jet-powered bomber airplane at wind-up turns. Results regarding total tail loads, elevator loads and elevator positions, stabilizer and elevator twist, and fuselage deflection are provided.

Theoretical analysis of performance of a ducted-fan power plant designed both for high-output, high-altitude operation at low supersonic Mach numbers and for good fuel economy at lower fight speeds is presented. Performance of ducted fan is compared with performance (with and without tail-pipe burner) of two hypothetical turbojet engines. At maximum power, the ducted fan has propulsive thrust per unit of frontal area between thrusts obtained by turbojet engines with and without tail-pipe burners. At cruise, the ducted fan obtains lowest thrust specific fuel consumption. For equal maximum thrusts, the ducted fan obtains cruising flight duration and range appreciably greater than turbojet engines.

Report presenting an investigation to determine the effect of sweep, taper ratio, and aspect ratio on the aerodynamic characteristics of nine semispan wings with NACA 65A006 airfoil sections with and without split flaps. Lift, drag, pitching-moment, and wing-root bending-moment characteristics are presented for a range of Reynolds numbers.

Summaries of low-temperature self-ignition data of various rocket fuels with mixed acid (nitric plus sulfuric) are presented. Several fuels are shown to have shorter ignition-delay intervals and less variation in delay intervals at moderate and sub-zero temperatures than crude N-ethylaniline (monoethylaniline),a rocket fuel in current use.

The effect of air, nitrogen, helium, argon, and a mixture of twenty volume percent of hydrogen in argon on the wetting of a stainless steel (Type 446), a two percent chromium-one half percent molybdenum type steel, and a plain carbon type steel by liquid bismuth was investigated

Report presenting flight measurements using the Douglas D-558-II airplane in order to determine the longitudinal stability and control characteristics in steady and accelerated flight. Results are given for various flap positions, especially in regards to degrees of instability present.

Report presenting aerodynamic parameters and operation techniques for a fin-actuated jet-vane system for the stabilization of a rocket-powered model by means of static and flight tests. Static testing was used to obtain lift, hinge moment, and center-of-pressure location of the jet vane, while the longitudinal stability characteristics of a simplified model were determined from the results of a flight test.

From abstract: The estimation of beryllium oxide in beryllium metal depending on the differential solubilities of the two material in dilute hydrochloric acid is presented. The results compare favorably with the present beryllium chloride volatilization procedure. Alternate methods are described, and the limitations and possible errors are discussed.

The results of pressure-distribution and force tests of four wings at a Mach number of about 6.9 and a Reynolds number of 0.98 x 10(6) in the Langley 11-inch hypersonic tunnel are presented. The wings had a square plan form, a 5-percent-chord maximum thickness, and diamond, half-diamond, wedge, and half-circular sections.

From Introduction: "This report shows correlation between actual transient data obtained from the engine and solutions to a simulated system set up on an analog computer. Data are presented for response of engine speed to changes in set speed when the power plant was being controlled by a relay-type electronic governor that acted to maintain set speed by varying propeller pitch. Correlation obtained for sea-level conditions between actual time data and analog solutions is discussed."

A semiempirical method, in which potential theory is arbitrarily combined with an approximate viscous theory, for calculating the aerodynamic pitching moments for bodies of revolution is presented. The method can also be used for calculating the lift and drag forces. The calculated and experimental force and moment characteristics of 15 bodies of revolution are compared.

Memorandum presenting an investigation of internal film cooling of the combustion chamber of a 1000-pound-thrust liquid-ammonia-liquid-oxygen rocket engine. The three coolants studied were water, ethyl alcohol, and liquid ammonia. Results regarding heat-transfer results, liquid film-cooled length, correlation of heat-transfer data, and effect of film cooling on performance are provided.

Report discussing progress made by the Metallurgy Division of the Physics of Solids Institute during the quarter ending January 31, 1951.

Report presenting a wind-tunnel investigation to evaluate the effects of Mach and Reynolds number on the characteristics of the internal and external flow about an E-type cowling suitable for a turbine-propeller power-plant installation. Results regarding the pressure-coefficient distributions, critical Mach number, cowl-gap flow, ham recovery, and wake-survey drag are provided.

Memorandum presenting an investigation in the 20-foot free-spinning tunnel on a 1/20-scale model to determine the effect of two alternate nose designs on the spin and recovery characterstics of the McDonnel XF3H-1 airplane. The results indicated that, in order to insure satisfactory recovery from any developed spin obtained in the airplane with either of the two alternate nose designs, it may be necessary to use ailerons deflected with the spin in conjunction with rudder reversal, as was the case for the original nose design.

Report presenting the results of an experimental investigation of the downwash and longitudinal stability characteristics of a semispan, triangular-wing airplane model with a horizontal tail. Lift, drag, and pitching-moment data re presented for the wing-fuselage combination. Results indicated that the model with the tail on or below the wing-chord plane possessed satisfactory stability characteristics throughout the test range of lift coefficient.

Report presenting the effect on drag of varying the chordwise position of a nacelle at the wing tip of a 45 degree sweptback wing and body combination as determined through transonic flight tests at zero lift. The drag of the configuration with nacelles in the rear chordwise positions was equal to or less than the drag of the configuration without nacelles over most of the speed range.