"The method of Poggi is employed for the determination of the effects of compressibility upon the flow past an obstacle. A general expression for the velocity increment due to compressibility is obtained. The general result holds whatever the shape of the obstacle; but, in order to obtain the complete solution, it is necessary to know a certain Fourier expansion of the square of the velocity of flow past the obstacle. An application is made to the case flow of a symmetrical Joukowski profile with a sharp trailing edge, fixed in a stream of an arbitrary angle of attack and with the circulation determined by the Kutta condition" (p. 197).

The following memorandum discusses experiments and methods to recover uranium from Colorado-Utah sandstone and leaving the vanadium in the tails, improving filterability.

The two-dimensional, incompressible potential flow past a lattice of airfoils of arbitrary shape is investigated theoretically. The problem is treated by usual methods of conformal mapping in several stages, one stage corresponding to the mapping of the framework of the arbitrary line lattice and another significant stage corresponding to the Theodorsen method for the mapping of the arbitrary single wing profile into a circle. A particular feature in the theoretical treatment is the special handling of the regions at an infinite distance in front of and behind the lattice. Expressions are given for evaluation of the velocity and pressure distribution at the airfoil boundary. An illustrative numerical example is included.

"An analysis is made of the stability of an airplane with ailerons free, with particular attention to the motions when the ailerons have a tendency to float against the wind. The present analysis supersedes the aileron investigation contained in NACA Technical Report no. 709. The equations of motion are first written to include yawing and sideslipping, and it is demonstrated that the principal effects of freeing the ailerons can be determined without regard to these motions" (p. 255).

"A high-speed wind-tunnel investigation of the aerodynamic characteristics of a full-scale model of the Consolidated Vultee Lark indicates that the missile possesses satisfactory longitudinal-stability and-control characteristics throughout the Mach number range from 0.2 to 0.85, but that the maximum lift coefficients developed are not high enough to insure interception of the target at high altitudes. A reduction in wing loading appears advisable. Although the static longitudinal stability at zero angle of attack changes with Mach number and with lift coefficient, satisfactory control should be possible at all times as the tails retain their relatively large effectiveness throughout the range of Mach numbers and lift coefficients tested" (p. 1).

From Summary: "This report presents the results of a wind-tunnel investigation conducted to determine the effects of Mach number on the aerodynamic characteristics of a wing of triangular plan form."

Report presenting drag measurements made on a 10-percent-thick wing and 8-percent-thick tail and a 8-percent-thick wing, 6-percent-thick tail version of the X-1 airplane at a variety of Mach numbers. The drag of the thicker wing was found to be much higher than that of the thinner wing. The fuselage was found to cause interference with the wing of both models, making the separation of wing and fuselage drag difficult to determine.

Report presenting a wind-tunnel investigation at a range of Mach numbers with a constant Reynolds number of a semispan model of a thin, unswept wing of aspect ratio 4 and taper ratio 0.5 with a constant-chord aileron and a modified diamond profile. Results regarding lift and rolling-moment characteristics and aileron effectiveness are provided.

"An investigation has been conducted in the Langley 300 MPH 7- by 10-foot tunnel to determine the static stability characteristics at low speeds of complete models with various swept wings so that comparisons might be made with available theoretical and empirical methods of predicting the stability characteristics. Longitudinal and lateral stability characteristics, flaps up and down, were obtained for models having 0 degree, 15 degrees, 30 degrees, and 45 degrees sweptforward and sweptback wings. The results of the investigation indicate that static stability characteristics can be estimated with reasonable accuracy in the low-lift range by means of existing theories" (p. 1).

The results of tests at a Mach number of 1.94 of an ogives-nose cylindrical pitot-static tube and similar tests at Mach numbers of 1.93 and 1.62 of a service pitot-static tube to determine body static pressures and indicated Mach numbers are presented and discussed. The radial pressure distribution on the cylindrical bodies is compared with that calculated by an approximate theory.

"A Westinghouse 24C-2 combustor was investigated at conditions simulating operation of the 24C Jet engine at zero ram over ranges of altitude and engine speed. The investigation was conducted to determine the altitude operational limits, that is, the maximum altitude for various engine speeds at which an average combustor-outlet gas temperature sufficient for operation of the jet engine could be obtained. Information was also obtained regarding the character of the flames, the combustion efficiency, the combustor-outlet gas temperature and velocity distributions, the extent of afterburning, the flow characteristics of the fuel manifolds, the combustor inlet-to-outlet total-pressure drop, and the durability of the combustor basket" (p. 1).

From Introduction: "The present report gives an analysis of the design point performance of nuclear powered liquid-metal turbojet engines. The effect of varying the assumptions necessary to calculate gross weight and reactor heat release from engine data is presented."

Report presenting an analysis of the nuclear powered liquid-metal turbojet cycle for a wide range of engine operating conditions at a range of flight Mach numbers and altitudes. The method of analysis and working charts are presented to facilitate investigations beyond the scope of this report.

Report presenting an investigation of an axially symmetric spike-type nose inlet suitable for a nacelle power-plant installation in the 8- by 6-foot supersonic tunnel at a range of Mach numbers and angles of attack. The inlet was designed to attain a mass-flow ratio of unity a Mach number 2.0. Results regarding the performance of inlet A and inlet B, which differed based on subsonic diffuser area variation, are provided.

Abstract: "The transformation of metastable beta uranium crystals was found to proceed by a martensitic reaction at room temperature. The features of the transformation of particular interest were that individual uranium martensite plates formed isothermally and grew at a slow rate isothermally."

Report presenting an investigation to determine the directional characteristics of a sharp-nosed fuselage through a large angle-of-attack range at zero angle of sideslip. The fuselage was found to experience a large increase in yawing moment as the angle of attack increases. The results also indicated that a ring or other roughness used on the nose caused a large decrease in the yawing moment obtained at high angles of attack.

Memorandum presenting a comparison between the force data obtained on a wing in air and Freon-12 at a low supersonic Mach number as obtained from the pressure coefficients measured at three spanwise stations on a 45 degree sweptback wing. Results regarding pressure distributions and force and moment conversion factors are provided.

Memorandum presenting analyses based on theoretical results of NACA Report 1041 to determine the plan forms of unbalanced trailing-edge flap-type controls with minimum hinge moments due to deflection and requiring minimum work to overcome the hinge moments due to deflection at supersonic speeds. Results of the analyses for longitudinal controls show high-aspect-ratio untapered controls to possess maximum ratios of lift to hinge moment. Results regarding ratios of lift to hinge moment, ratios of lift to deflection work, ratios of rolling moment to hinge moment, and ratios of rolling moment to deflection work are provided.

Report presenting an investigation in the 300 mph tunnel to determine the applicability of spoilers as lateral-control devices on thin delta wings. The wing used in testing had a thickness ratio of 1.5 percent at the root and a maximum ratio of 4.5 percent at 66.7 percent wing semispan, 60 degree sweepback at the leading edge, 0 degree sweep of the trailing edge, an aspect ratio of 2.31, and a taper ratio of 0. Results regarding the effect of spoiler location and angular placement, effect of spanwise location, effect of spoiler projection, and effect of slots and perforations are presented.

The conventional volumetric micro-determination of phosphate depends upon the precipitation of phosphomolybdate, filtration and washing of the precipitate, and titration with standard base. The method is slow and tedious, subject to many interferences, and is not applicable to samples containing less than 1-2 mg of phosphate. Other weak acid anions, such as carbonate or acetate, interfere in the method. Strong acid anions, such as nitrate, sulfate, and chloride do not interfere.

Report presenting an investigation of the low-speed stability and control characteristics of a modified scale model of the MX-1554A design. It employs a triangular wing and triangular stabilizing surfaces. The modifications of the design included an increase in slotted-flap span, a redesigned tip aileron, fuselage tail cone, and speed brakes.

"Theoretical pressure distributions on nonlifting circular-arc airfoils in two-dimensional flows with high subsonic free-stream velocity are found by determining approximate solutions, through an iteration process, of an integral equation for transonic flow proposed by Oswatitsch. The integral equation stems directly from the small-disturbance theory for transonic flow. This method of analysis possesses the advantage of remaining in the physical, rather than the hodograph, variable and can be applied in airfoils having curved surfaces" (p. 1).

Report presenting normal-force and pressure distributions for a body of revolution consisting of a fineness-ratio-3, circular-arc, ogival nose tangent to a cylindrical afterbody 7 diameters long. Comparisons of theoretical and experimental distributions indicate that available theoretical methods are only accurate for angles of attack up to about 5 degrees.

Memorandum presenting a comparison made between the incremental aerodynamic root bending moments on the horizontal tail of a jet-powered bomber airplane measured during a flight investigation over a range of Mach numbers and the bending moments calculated by using available theoretical models in conjunction with measured loads, elevator positions, and elevator and stabilizer twists. Results regarding abrupt maneuvers, gradual turn maneuvers, and effects of downwash are provided.