Transonic similarity rules are applied to the correlation of experimental data for a series of related rectangular wings of varying aspect ratio, thickness, and camber. The data correlation is presented in two parts: the first part presents the correlation for a series of 22 wings having symmetrical NACA 63a-series sections; the second part is concerned with a study of one type of camber by correlation of the data for a series of 18 cambered wings having NACA 63a2xx and 63a4xx 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."

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.

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.

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.

"An analytical investigation was made of the performance of isolated ram-jet engines in the flight Mach number range from 3 to 7 for two types of diffuser, a high-efficiency diffuser, and a normal-shock diffuser. The fuel was assumed to be a hydrocarbon similar to gasoline. The conclusions reached are: (1) a design altitude of about 100,000 feet is desirable for a high-efficiency high Mach number ram jet on the basis of engine construction and performance; and (2) although greater thrust could be obtained with other fuels, gasoline provides sufficient energy release for maximum engine efficiency in the flight Mach number range investigated. The maximum engine efficiency calculated was 0.47, which occurred at a Mach number of 5. At a Mach number of 7, the maximum propulsive-thrust coefficient was 0.57" (p. 1).

Examination of published data for some 52 isotopes indicates that the neutron energy for which the first resonance occurs is related to the magnitude of the thermal absorption cross section. The empirical relation obtained is in qualitative agreement with the results of a simplified version of the resonance theory of the nucleus of Breit-Wigner.

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 Summary: "A full-scale ejector cooling investigation was made on a turbojet engine - afterburner installation in the NACA Lewis altitude wind tunnel. Ejector performance was studied at primary exhaust-gas temperatures from 2700 degrees to 3400 degrees R (corresponding to ejector temperature ratios from 2.0 to 5.0), primary pressure ratios from 1.79 to 3.4, secondary air flows up to 29 percent of the primary gas flow, and for diameter ratios from 1.08 to 1.42 and spacing ratios from 0.04 to 1.16. In addition, variations were made in the primary exhaust-nozzle area."

Report presenting the results of pressure-distribution and force tests of two cone-cylinder configurations and a comparison with theoretical calculations. The first series was made up of three configurations with 20 degree conical noses and cylindrical afterbodies with 0, 2, and 4 diameter lengths and the second was made up of cylindrical afterbodies with a diameter length and conical noses with apex angles of 10 to 180 degrees. Results regarding the pressure distributions, aerodynamic forces, and Schileren photographs are provided.

Report presenting an investigation of combined compressor coolant injection and tailpipe burning as a means of turbojet engine thrust augmentation at sea-level, zero ram conditions on a 4000 pound thrust, axial-flow-type turbojet engine. Water-alcohol injection flows from 2 to 5 pounds per second were introduced into the compressor in conjunction with tail-pipe burner fuel-air ratios from 0.017 to stoichiometric. Results regarding engine performance and operational characteristics are provided.

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 an investigation of a solid half body modified to mount a scoop inlet and a submerged inlet while maintaining the same entrance geometry, afterbody, and diffuser for both inlets. Comparative pressure-recovery, pressure-distribution, and drag data were obtained for the two inlet types.

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.

Preliminary investigation was made of conical cooling air ejector at primary pressure ratios from 1 to 10. The cooling-air flow was maintained at zero and the resulting pressure variation in the shroud indicated pumping ability. The cooling-air flow was maintained at zero and the resulting pressure variation in the shroud indicated pumping ability.

Report presenting an application of the transonic similarity law to the correlation of the zero-lift drag of rectangular wings obtained by means of free-fall and rocket techniques. Results regarding the basic data, the modified similarity rule, correlation of data, and similarity law for swept wings are provided.

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 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.

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.

The following report is a study of the separating qualities of a loop-type separator that can obtain separation with a smaller pressure drop.

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.

Summary of research progress conducted on subjects such heavy element energy cycles and scattering.

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

"The wave drag of a combination of slender bodies of revolution at zero angle of attack is studied with a view to determining the arrangements for which the total drag is a minimum. Linearized theory is used to calculate the pressure distribution in the field surrounding the bodies. The interference drag coefficient is computed for different arrangements. The special cases of two bodies and of a three-body combination with bilateral symmetry are considered" (p. 1).