Report presenting an investigation of various external-store configurations on a model of a tailless airplane with a sweptback wing over a range of Mach numbers. The investigation was performed out of a desire to reduce the drag interference caused by external stores as much as possible. Results regarding the aerodynamic characteristics in pitch, lift-drag ratios, effect of Mach number, variation of control effectiveness, aerodynamic characteristics in yaw, and variation of stability parameters are provided.

Memorandum presenting wind-tunnel testing of a jet-engine nacelle on a semispan wing with the leading edge swept back 37.25 degrees made to determine the effects of the nacelle on the aerodynamic characteristics of the wing. In comparison with the force characteristics of the wing alone, the addition of the nacelle to the wing in each position resulted in favorable interference on the maximum-lift and pitching-moment characteristics and in a small increase in drag.

"Pressure-distribution measurements were made during a lateral-control investigation of a semispan wing with the NACA 0012-64 section and a 20-percent-chord plain aileron. The results are presented as tables of pressure coefficients for Mach numbers from 0.60 to 0.85. No analysis of the results is included" (p. 1).

Report presenting flight measurements in sideslips of the static lateral and directional stability characteristics of the Douglas D-558-II airplane. It is part of an investigation to determine the stability and control characteristics and aerodynamic loads acting on the wing and horizontal tail of an airplane from stalling speed up to a maximum Mach number of 0.90. Results regarding variations of rudder, total aileron, elevator control positions and control forces, aileron position, and aerodynamic hinge moments are provided.

Report presenting the aerodynamic properties of a model of a jettisonable nose section with a circular cross section as determined at low speed from an investigation in the 20-foot free-spinning tunnel. The results indicated that the aerodynamic characteristics of the nose were greatly affected by proximity to the fuselage. Even for a stabilized nose, it may be necessary to eject the nose forward forcibly in order to prevent high accelerations along the backbone of the pilot.

Report presenting force testing on an NACA 3-(3)(05)-05 eight-blade dual-rotating propeller at a range of blade angles. Results indicated that good efficiencies can be obtained at high subsonic forward Mach numbers by operation at high blade angle. Results regarding the propeller characteristics, individual power coefficients, effect of forward Mach number on the maximum efficiency of the dual propeller, and effect of small changes in the rear-propeller blade angle on the dual-propeller characteristics are also provided.

"A theoretical investigation has been made to determine the effect of nonlinear stability derivatives on the lateral stability of an airplane. Motions were calculated on the assumption that the directional-stability and the damping-in-yawing derivatives are functions of the angle of sideslip. The application of the Laplace transform to the calculation of an airplane motion when certain types of nonlinear derivatives are present is described in detail" (p. 1009).

Memorandum presenting an investigation made at a Mach number of 1.93 to determine lift, drag, pitching-moment, and average downwash characteristics of several missile configurations. Five configurations with rectangular wings and tails of various spans were tested; each of the configurations had two locations of the wing relative to the tail.

"The proportional-plus-flicker automatic pilot operates by a nonlinear principle whereby a fast-acting flicker servomotor response is combined with a low-speed proportional servomotor response for the purpose of obtaining supersonic stability and control. Essentially, the autopilot maintains a zero reference about which the output is proportional to the input. However, a flicker response overrides this proportional response at a fixed angle of gimbal displacement on either side of the zero gyroscope reference" (p. 1).

From Introduction: "The effect of flame-holder and fuel-system design on the burner performance and the effect of altitude and flight Mach number on over-all performance with a fixed-area exhaust nozzle are reported in reference 1 to 4. Altitude performance characteristics of a tail-pipe burner having a converging conical burner section are presented in this report. Tail-pipe burner performance at several flight conditions is given in both tabular and graphical forms and compared with performance of the standard engine and of the tail-pipe burner reported in reference 2."

Abstract: "This is the preliminary report of a radiological-ecological survey of the invertebrate fauna that inhabit the Columbia River within the confines of Hanford Works and downstream to the site of McNary Dam. The survey was carried out during the period of October, 1948 through February, 1950. Materials and methods are discussed and the results of extensive radioassays, qualitative and quantitative biological determinations, and hydrographic studies are given and analyzed. Twelve figures and twenty-three tables are included. All aquatic invertebrates were found to be concentrating radioactivity from the river water. A maximum activity density of 4.4-10-(-3) μc/g wet weight was found in the larvae of midges (Hydrobaeninae) collected near Hanford during September, 1949. Radioactive wastes were not found to be causing any apparent deleterious effects to the natural invertebrate fauna. Existing population variations are caused by biological and hydrographic conditions."

"Flight measurements of the aerodynamic wing and tail loads have been made on the Douglas D-558-II airplane from which the distribution of the aerodynamic load among the wing, fuselage, and horizontal tail has been determined at Mach numbers up to 0.87. These measurements indicate that, for normal-force coefficients less than 0.7, the distribution of air load among the airplane components does not change appreciably with Mach number at Mach number up to 0.87. The measurements also indicate that, for all flight configurations, the increase in airplane normal-force coefficient above the angle of attack at which the wing reaches its maximum normal-force coefficient is due principally to the contribution of the fuselage to the airplane normal-force coefficient" (p. 1).

Report presenting an experimental investigation to determine the force and pressure characteristics of a typical nose inlet ramjet configuration. It consisted of a conical spike all-external compression inlet attached to an annular subsonic diffuser. Results regarding external-flow characteristics and internal-flow characteristics are provided.

Report presenting a flight investigation of a ground-launched supersonic twin ram-jet test vehicle using short flame-length burners. Results were obtained for a range of Mach numbers, altitudes, and fuel-air-ratios. Engine performance, gross thrust, fuel rate, total impulse, values of combustion efficiency and impulse, and overall combustion efficiency are also included.

Report documenting the suitability of Georgia for plant locations to produce synthetic liquid fuels, based on raw materials such as coal, natural gas, oil shales, and oil-impregnated strippable deposits.

From Introduction: "The results of the aforementioned study are presented in this report together with the method of analysis employed. The net stability change is shown together with the individual contributions due to flexibility of wing, tail, and fuselage, both including and neglecting the effect of inertial loads."

Buffet boundaries, buffeting-load increments for the stabilizers and elevators, and buffeting bending-moment increments for the stabilizers and wings as measured in gradual maneuvers for a jet-powered bomber airplane are presented. The buffeting-load increments were determined from strain-gage measurements at the roots or hinge supports of the various surfaces considered. The Mach numbers of the tests ranged from 0.19 to 0.78 at altitudes close to 30,000 feet. The predominant buffet frequencies were close to the natural frequencies of the structural components. The buffeting-load data, when extrapolated to low-altitude conditions, indicated loads on the elevators and stabilizers near the design limit loads. When the airplane was held in buffeting, the load increments were larger than when recovery was made immediately.

A comparative evaluation was made for all-movable delta and flap-type controls on several wing plan forms. Comparison of these experimental results from various test facilities shows the effectiveness on various wing plan forms and an evaluation of hinge-moment characteristics of all-movable delta controls, swept trailing-edge flap, and straight trailing-edge flap-type controls.

From Introduction: "This report is concerned with the derivation of expressions for the velocity potential and associated forces and moments for oscillating triangular wings in supersonic flow. The purpose of the present report is to make use of the expanded form of the velocity potential to obtain the forces and moments, based on the first terms of this potential, for a rigid triangular wing performing vertical and pitching sinusoidal oscillations in mixed supersonic flow."

Abstract: Yazzie Mesa was examined in May 1951, by the writer, assisted by R. C. Cutter. The mesa shows one main channel deposit and three minor channels. The main channel appears to be a northern extension of a channel deposit being worked by the Vanadium Corporation of America at their Monument No. 2 mine. Two samples taken on the south outcrop of the main channel assayed 0.16% U308 over 4.5 feet and 0.80% U308 over 1 foot. The area is recommended for 10,000 feet of exploration drilling. It is not intended to recommend this footage as a separate contract unit as this report covers only a small part of an area in which drilling will be recommended in forthcoming reports.

Technical report presenting a consideration of the characteristics of fused salt-ThF4 solutions suitable for use in homogeneous reactors. Presented in tandem with a brief survey of the literature pertaining to such solutions and a summary of the experimental work accomplished. [From Abstract]

Report presenting an investigation in the 19-foot pressure tunnel to determine the effects of a fuselage and a horizontal tail located at various vertical positions on the low-speed longitudinal characteristics of a circular-arc 52 degree sweptback wing. Results regarding the effect of fuselage on longitudinal characteristics of the wing, effect of tail position on stability and tail effectiveness, and air-flow characteristics are provided.

Memorandum presenting a study of the effect of prestrain in tension upon the stress-strain characteristics in compression for copper and brass. The residual stress phenomenon known as the Bauschinger effect is of primary importance in cyclic loading, inasmuch as it serves to reduce the yield strength of plastically strained metal to deformation of the opposite sign.

Report discussing changes in parameters regarding Sutton's diffusion hypothesis, which is used in calculations of plant stacks' atmospheric pollutant distribution. An explanation of the computation and results are given.